DE2618644A1 - Rocket launched reusable space shuttle - has aerodynamic form and variable geometry thrust to allow vertical takeoff - Google Patents

Abstract

The re-usable space shuttle has different shapes depending on the use and the payload. It is launched using variable geometry thrust rockets which provide greater steering control in the atmosphere and in space. The design of the craft is such that it provides maximum comfort and safety for the occupants. In the event of thrust failure the craft can glide through the atmosphere. Partial failure in space can be counteracted by varying the thrust geometry. The craft has the variable geometry rocket motors arranged at the wings and tail to allow vertical takeoff and landing.

Description

Description Transport and defense system for manned spacecraft for space travel.

The invention relates to a manned transport and defense system Spacecraft for space travel, designed to carry a transport bridge from Manned spacecraft to form in interplanetary space to create Space stations in space or on the moon, with appropriately designed rawn missiles serving to maintain peace and to secure interests in the interplanetary Space or on the moon.

In such undertakings it is necessary to use a system can be built that has a high efficiency at a ratio portable cost accounting and its efficiency an optimal level of security for the crews of the spacecraft or space stations.

This will be achieved when spacecraft are created that support the Requirements met.

It is known that unmanned and manned spacecraft primarily be brought into interplanetary space with so-called launch rockets. Included it is necessary, however, that a high potential of thrust is required in order to achieve the high Moving the weight of a launch rocket, also known as a launcher. This weight in turn, is due to the high volume of fuel that is carried has to bring a manned spaceship into space. (Arthur C. Clarke book "Man and Space" TIYE-IIFE International 'Nederland' N.V. Year 1970, pages 44 to 47). As is well known, undertakings of this kind are very costly.

The invention is based on the object of undertaking such activities to make it more flexible in relation to the efficiency.

This object is achieved according to the invention in that a Transport- and defense system consists of spacecraft, each of which has different basic versions can be derived, whereby it is given that a spacecraft for a particular Task area can be created and thereby achieve optimal functionality The spacecraft are shown in terms of their construction in FIGS. 12 to 65, they are designed so that they take advantage of the natural laws of the earth's atmosphere can work, due to their design features, the spacecraft have via optimal evasive systems, the airworthiness of the spacecraft in the event of danger in space or in the earth's atmosphere.

In order to achieve a further optimal functioning of the spacecraft, are according to a further embodiment of the invention, the structures of the spacecraft designed so that the self-propelled, spaceflight manned spacecraft which are shown in terms of construction in the h'ig.12 to Fig.65, by a certain or illustrated arrangement of the pivotable rocket engines to each other, all be able to perform required flight maneuvers in interplanetary space as in a scheme to illustrate the construction principle for possible flight maneuvers of the spacecraft is shown in interplanetary space in Figures 1 to 11.

The advantages achieved with the invention consist in particular: that with the transport and defense system, that from the spacecraft in terms of construction shown in Figs. 12 to 65 or Fig. 66 to Fig. 87 and Fig. 93 to Fig. 95 exists, various possibilities are given, such as the fulfillment of research tasks in interplanetary space, the creation of space stations in interplanetary space, the creation of facilities and functional buildings or the settlement of people for (ir Activities on the moon, the formation of a defense system consisting of so-called tactical space interceptors to secure interests in interplanetary space and on the moon.

So the spacecraft can be used for passenger transport as transporter, for the transport of objects as a load carrier, as a container transporter, be designed as a flying observatory or as a tactical space interceptor. Other designs are possible, such as a transporter for transporting fuel, or a transporter for the transport of breathable air, etc., a transporter for transport of fuel or breathing air is not shown.

The spacecraft can be divided into two groups for oversight will.

The first group can be the Earth-Space spacecraft.

These are the spacecraft with pivoting rocket engines and are designed with turbine jet engines.

The earth-space spacecraft take off and land mainly on the planet earth. They are characterized by optimal security, as they each via jet propulsion with turbine jet engines and via rocket propulsion with swiveling beacon engines.

For example, if the jet propulsion system fails in the earth's atmosphere the flight can be continued with the rocket propulsion system or vice versa. That is important or advantageous for take-offs and landings on planet earth. It there are various options, e.g. for a landing on planet earth at.

An Earth-space spacecraft can land a conventional aircraft run with turbine jet engines in cooperation with elevator and rudder.

An Earth-spacecraft can make a VTOL landing using rocket engines (VTOL = Vertical TakeOff and Landing = vertical takeoff and landing, James J. Haggerty book "The Flight" TIME-LIFE International 'Nederlanl' N.V. Born in 1970, Page 152).

An Earth-space spacecraft can land a conventional aircraft perform with rocket engines in cooperation with edhen and rudder.

An earth-space spacecraft can launch at sufficient speed slide the runway, similar to the plane designed as a glider "HL-10" or "M-2" by the American company Northrop (James J. Haggerty's book "The Flight" TIME-LIFE International 'Xederland' N.V. Year 1970, page 169).

The earth-space spacecraft can each according to the design of the individual Spacecraft from the planet earth the various transports such as people or Supplies and the like for stationary units in interplanetary space or carry to the moon.

The Earth-Space spacecraft are designed to be used e.g.

fly to the moon, land there or start again and to the planet Earth can fly back. They can be refueled in interplanetary space or they can be reused after use. Depending on the design the interior structure of the individual spacecraft can be the earth-space spacecraft be used for the transport or defense system.

The second group can form the space-moon spacecraft.

These are the spacecraft designed only with rocket engines are. The space-moon spacecraft work primarily in interplanetary space and can land and take off on the moon. The spacecraft lend themselves to each designed with six rocket engines.

This ensures that in the event of a rocket engine failure. the failure of two rocket engines when distributed on the spacecraft a landing or take-off on the moon is still possible. This is a optimal safety for landings and take-offs on the lond.

The Baum-kond spacecraft are designed to be used e.g.

fly to planet earth, land there or start again and in can fly back to planetary space or to the moon. Bb offer different ones Opportunities e.g. for a landing on planet earth.

A space-moon spacecraft can land a conventional aircraft perform with rocket engines in cooperation with elevator and rudder.

A space-moon spacecraft can make a VTOL landing using rocket engines carry out.

A space-moon spacecraft can slide back to planet earth, with the generation of counter-thrust by rocket engines due to the resulting frictional heat upon re-entry into the Earth's atmosphere, similar to that as a glider designed aircraft "HL-10" or "M-2" from the American company Northrop.

The space-moon spacecraft can be refueled in interplanetary space can be reused after use. Depending on the design the interior structure of the individual spacecraft can be the space-moon spacecraft be used for the transport or defense system.

Various possible combinations between earth-space spacecraft and space-moon spacecraft are given.

For example, an earth-space spacecraft Fig. 63 to Fig. 65 of the as The personnel carrier Fig. 66 to Fig. 69 is designed to start on planet earth and into interplanetary space or

fly to the moon, where he is with a space moon spacecraft Fig. 30 to Fig. 32, which is also laid out as a crew transporter, Fig. 66 to Fig. 69 is waiting near the mouth on a moon parking orbit, similar to the spaceship Columbia executed in the American space company "Apollo 11" (Arthur C. Clarke book "Man and Space" TIME-LIFE International Nederland 'N.V. vintage 1970, p137).

The crew, except for two pilots, of the earth-space spacecraft are rising in interplanetary space into the space-moon-raunifugkörper, which then makes a moon landing executes and a later launch from the moon, or can the space-moon spacecraft stay close as a safety margin when the Earth-space spacecraft is on lands on the moon and takes off again later.

Or, for example, an earth-space spacecraft Fig. 63 to Fig. 65 of the is designed as a container transporter Fig.85 to Fig.87, on planet earth start and fly into interplanetary space or to the moon, where he meets with a Space-moon spacecraft Fig. 30 to Fig. 32 hits, which is also used as a container transporter Fig. 85 to Fig. 87 is designed and in the vicinity of the moon on a moon park orbit waiting.

The space-moon spacecraft takes over the container of the earth-space rocket missile in interplanetary space and lands on the moon where he deposits the container. To a later launch from the moon, the Earth-Raua-Rau others Take containers from the Space Eond spacecraft and fly back to planet Earth.

The spacecraft for the transport and defense system offer themselves from a manufacturing point of view. So the spacecraft Fig.12 to Fig.20 have the same cell structure, i.e. the same basic structure. The same goes for the spacecraft Fig. 21 to Fig. 29, as well as the spacecraft Fig. 30 to Fig. 65. That matters when a so-called production line for the construction of the spacecraft is created.

From the spacecraft shown in FIG. 12 to FIG. 65, various Spacecraft are selected or determined, which the transport or defense system The spacecraft Fig. 30 to Fig. 65 can be chosen according to your choice and Construction features with the internal structures Fig. 66 to Fig. 87 or

Fig. 93 to Fig. 95 can be interpreted.

An embodiment of the invention is shown in the drawing and is described in more detail below.

FIGS. 1 to 11 show a diagram to illustrate the tone construction principle for possible flight maneuvers of the spacecraft shown in Fig. 12 to Fig. 65 and Ein-Mhnn-Fluggerät Fig. 132 to Fig. 134 in interplanetary space.

Thus, FIG. 1 shows a side view, FIG. 2 shows a plan view, and FIG. 3 is a front view of a schematically illustrated for the scheme serving spacecraft. The body 1 containing the pilots can be pivoted with the attached rocket engines 2,3,4 connected.

The rocket engines 2,3,4 are each attached so that they through Pivoting can change their thrust direction or ejection direction. That Triangle 5 symbolizes the direction in which the rocket engines are ejected. The arrow 6 shows the resulting flight direction.

The side view Fig.1 and top view Fig.2 show a. rectilinear Direction of flight of the spacecraft. There are three rocket engines working 2, 3, 4. at the straight flight course can only work the rocket engine 9, the rocket engines 2,4, are switched off. Two rocket engines 2 »4 can also work that Rocket engine 3 is switched off.

The side view Fig.4 shows the possible positions of the rocket engines 2,3,4 with their ejection directions, which in turn are symbolically represented by the triangles 5 are.

It can be a straight flight direction or acceleration of a spacecraft, as shown in the side view Fig.1 and top view Fig.2, thereby canceled when the rocket engines 2 and 4 are swiveled in the opposite direction and then a Counter thrust is generated, as shown in the plan view Fig.5. The rocket engine 3 is switched off at this point.

Flying a curve or changing from a certain one Direction of flight in another direction of flight is achieved by changing the thrust direction another attitude of the spacecraft is reached.

Ea show the Fig.6, Fig.8, Fig.10 a side view, the Fig.7, Fig.9, Fig.11 a front view of the spacecraft shown schematically as he behaves with a corresponding change of flight direction.

If a spacecraft is in a straight flight direction, the Side view Fig. 6 and front view Fig. 7 show a straight flight direction, it is achieved that when changing the direction of thrust of the rocket engine 4 a Change of the spacecraft to its transverse axis takes place. This shows the side view Fig. 8 and front view Fig. 9. At the same time, the rocket engine works by pivoting 3, it changes the direction of thrust and creates a thrust that causes the spacecraft changed its position to its longitudinal axis. This shows the side view Fig.10 and Front view Fig. 11.

To an overturning of the spacecraft, due to the weightlessness in interplanetary space, can avoid the respective rocket engines after they have given a thrust to change their position, generate a counter-thrust in order to to stabilize the spacecraft's new lodge. That only happens when a Counter thrust is required.

When landing or taking off on the moon, they behave similarly designed spacecraft.

A landing or take-off on the moon occurs when the rocket engines 90 be waved that given XTOL properties are. That can be done according to the design of the spacecraft with three rocket engines, four rocket engines or six rocket engines.

There show the Fig. 126 to Fig. 131 a diagram for the representation of the Launch of a spacecraft on the moon. The failure process is in six Phases shown.

Fig. 126 shows phase one. The spacecraft takes off. It work two rocket engines 374 and one rocket engine 375.

Fig. 127 shows phase two. The spacecraft has the landing legs retracted. Two beacon engines 374 and one rocket engine 375 operate.

Fig. 128 shows phase three. The two rocket engines 374 and a rocket engine 375 pivot to its home position.

Fig. 129 shows the phase Uier. The two rocket engines 374 and a rocket engine 375 continues to pivot to its home position. The spacecraft moves forward.

Fig. 130 shows phase five. The two itacket engines 374 and a rocket engine 375 continues to pivot to its home position, the spacecraft moves forward. The two rocket engines 376, if any, can be fired be used to accelerate the spacecraft.

Fig. 131 shows phase six. The two rocket engines 374 and the rocket engine 375 have assumed their starting position. The spacecraft accelerates further.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 12 shows a side view, FIG. 13 a top view, and FIG. 14 is a front view of a spacecraft.

The spacecraft is designed as a tactical thumb interceptor but can also be designed for other tasks. This spacecraft can form part of the said defense system.

The scale @ 18 allows a dimensioning that of course deviates can.

This spacecraft is designed to be quick execution of flight maneuvers in interplanetary space.

He can from a carrier aircraft in the earth's atmosphere in great height be dropped from where the flight into interplanetary space begins, similarly like the American rocket plane SX-15 "that at high altitude from a jet plane "B-52" was dropped (James J. Haggerty book wDer Flug "TIME-LIFE International 'Nederland' N.V. Year t970, pages 34 and 190) The wings 14 are stronger designed to achieve an optimal tank volume in the wings.

The additional tanks 12, which are carried along, represent a further tank volume Warren systems, e.g. rockets, can also be carried in their place will.

The rocket engines 11 are pivotally mounted. The landing line 15,16,17 which is shown in the top view Fig. 13 in the retracted state, however, in the front view Fig. 14 and side view Fig. 12 in the extended state are shown, serve a possible landing on the moon. The principle of operation the landing legs are dealt with in the constructions Fig. 117 to Fig. 125. Through the The cockpit hood 13 gives the pilot 13a an optional field of vision. A possible swivel Rocket engine suspension is shown in the constructions Fig. 135 to Fig. 142. The spacecraft can be designed with a landing gear, long stay in interplanetary space offers itself.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 15 shows a side view, FIG. 16 a top view, and FIG. 17 is a front view of a spacecraft.

The spacecraft is designed as a tactical space interceptor but can also be designed for other tasks. This spacecraft can form part of the said defense system.

The scale 29 allows a dimensioning that of course deviate can.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and there can carry out quick Elugnanver or quick changes of direction. Of the Take-off from planet earth takes place with two turbine jet engines 21.

A turbine jet engine generates its thrust through the Output of expanding gases. The air sucked in at the front is first compressed, then pushed back into the combustion chamber and mixed with fuel. The inflammation this mixture creates a rearward surge of expanding gases that carry the Propel the flying object or spacecraft forward and the compressor turbine at the same time drive (James J. Haggerty's book Wider Flug "TIME-LIFE International 'Nederland' N.V. Year 1970, page 84).

The two turbine jet engines z1 are supposed to take the spacecraft from Bring the soil into the uppermost air layers of the earth's atmosphere. That can go through possible so-called intermediate refueling in the air can be achieved.

The wings 25 are made stronger in order to provide an optimal tank volume in the wings.

The additional tanks 2C, which are carried along, represent a further tank volume weapons systems, e.g. rockets, can also be carried in their place will.

Three pivoting rocket engines are attached to the spacecraft Rocket engine mainly consists of a combustion chamber with e.g. turbine pumps, that transport the fuel or the oxidizing agent in the Arthur C. Clarke book "Man and space "TIME-LIFE International 'Nederland' .V.

Born in 1970, pages 40 and 41).

On the three swiveling rocket engines 19, 19a, which focus on act in interplanetary space, the wings 22,23 are attached. The wings 22,23 are used to control the spacecraft in the earth's atmosphere, they change their position when the rocket engines are turned. It work in execution during a turn in the earth's atmosphere, the wings 22 each act as aileron, when the rocket engines 19 are turned (James J. Saggerty book "Der Flug" TIME-LIFE International Nederland 'N.V. Year 1970, page, 70 to 71).

The wings 23 act as elevators, they are through the shaft 23a firmly connected to the rocket engine 19a. The wings 23 can also pivotally mounted on the spacecraft independently of the rocket engine 19a will.

Another possibility is for a turn in the earth's atmosphere given. A wing 22 is moved so that the spacecraft moves to its transverse axis changes. At the same time the wings 23 are moved so that the spacecraft changed tail-heavy to its longitudinal axis. So it is possible the spacecraft in the earth's atmosphere in a transverse position and thus a change of direction or curve.

The spacecraft behaves similarly to a change of flight direction in interplanetary space, with the difference that not the pivoting rocket engines cause a different flight direction, but the air masses on the different provided wings and act on the underside of the spacecraft In the construction principle, a conventional rudder can be dispensed with.

The rocket engines 19, 19a are switched off in the earth's atmosphere, they can also contribute to support. A possible pivoting rocket engine mount is shown in the constructions Fig. 135 to Fig. 142.

The pilot 24a has an optimal field of vision through the lance hood 24.

When flying back to planet earth or when re-entering the earth's atmosphere the rocket engines 19 can be pivoted 180 degrees in the opposite direction to possibly create a counter-stroke to slow the spacecraft down or perform corrective shocks to stabilize the position of the spacecraft.

The landing gear26,27,28 is used to take off or land on the planet Earth, it is shown in the extended state. In essence, it's a similar one Landing gear as in the construction Fig. 27 to Fig. 29, where the landing gear is also retracted State is shown.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 8 shows a side view, FIG. 19 shows a plan view, and FIG. 20 is a front view of a spacecraft.

The spacecraft is designed as a tactical space interceptor he But k * n can also be designed for other tasks. This spacecraft can be a Form part of the said defense system.

The scale 41 allows a dimensioning that of course deviate can.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and can carry out quick flight maneuvers or quick changes of direction there. The takeoff from planet earth is done with two turbine jet engines 32, them should take the spacecraft from the ground to the uppermost layers of the earth's atmosphere bring. This can be achieved by possible so-called intermediate refueling in the air will.

In the earth's atmosphere the spacecraft is equipped with elevator and rudder controlled.

The rudder 33,) 5 are mounted on the wings 34, the Elevators 36,37 are attached to the rear fuselage. The wings 34 are stronger designed to achieve an optimal tank volume in the wings. Another one Tank volumes represent the additional tanks 31, which can be carried along, it can in their place also weapon systems e.g.

Missiles can be launched.

Three pivoting rocket engines 30 are attached to the spacecraft, which work primarily in interplanetary space. The rocket engines 30 are turned off in the earth's atmosphere, they can also contribute to support.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The canopy 42 provides the pilot 42a with an optimal field of vision.

When flying back to planet earth or when re-entering the earth's atmosphere can the two rocket engines 30 attached to the wings 34, be swiveled 180 degrees in the opposite direction to possibly generate a counter-thrust, which can reduce the speed of the spacecraft. The rocket engines 30 can perform corrective shocks to stabilize the spacecraft's attitude.

The landing gear 38,39,40 is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is a similar chassis as in the construction Fig. 27 to Fig. 29, where the landing gear is shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 21 shows a side view, FIG. 22 a top view, and FIG. 23 is a front view of a spacecraft.

The spacecraft is designed as a tactical space interceptor but can also be designed for other tasks. This spacecraft can form part of the said defense system.

The Y-bar 51 allows dimensions that differ naturally can.

This spacecraft is designed to cover a larger radius of action to be able to form in interplanetary space with a «appropriately designed tank volume and a possible optimal acceleration and execution of fast flight maneuvers in interplanetary space.

The spacecraft can be launched from a carrier aircraft in the earth's atmosphere be dropped at high altitudes, from where he made flight into interplanetary space begins, similar to the American rocket plane "X-15", at high altitude was dropped from a jet plane "B-52".

The wings 46 are made thicker to provide an optimal tank volume in the wings. The additional tanks provide another tank volume 44, which can be carried along; weapon systems can also be used in their place e.g.

Missiles or a combination of additional tanks and weapons systems carried along will.

The spacecraft is designed with three pivoting rocket engines 431 which serve the control or the execution of flight maneuvers ii interpianetarian space and designed with two built-in rocket engines 45 which are used for acceleration.

With the larger sized rocket engines 45 ii can cooperate with the three rocket engines 43 an optimal acceleration can be carried out. A possible swiveling rocket engine suspension is in the constructions Fig. 135 to Fig. 142. Through the pulpit hood 50 the Pilot 50a an optimal field of vision.

The landing legs 47,48,49 which in the top view Fig. 22 in the retracted State shown, however in the front view Fig. 25 and side view Fig. 21 are shown in the extended state, serve a possible landing on the Fund. The functional principle of the landing legs is shown in the constructions Fig. 117 to Fig. 125 treated. The spacecraft can be designed with a landing gear, a longer stay in interplanetary space is advisable.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 24 shows a plan view, FIG. 25 shows a side view, and FIG. 26 is a front view of a spacecraft.

The spacecraft is designed as a tactical space interceptor but can also be designed for other tasks. This spacecraft can form part of the said defense system.

The scale 63 enables a dimensioning that of course deviates can.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The launch from planet earth is carried out with two turbine jet engines 56, they are supposed to take the spacecraft from the ground to the uppermost layers of the air bring the earth's atmosphere. This can be done by possible so-called intermediate refueling in of the air.

The wings 57 are made thicker in order to provide an optimal tank volume in the wings. The additional tanks provide another tank volume 55 represent, which can be carried, there can also be weapon systems in their place e.g.

Missiles are carried.

The spacecraft is designed with three rocket engines 53,53a, the focus on the control or the execution of flight maneuvers in the interplanetary Serve space and designed with two built-in rocket engines 58, the focus serve to accelerate in interplanetary space.

With the larger dimensioned rocket engines 58 can act together with the three rocket engines 53,53a an optimal acceleration can be carried out. A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The wings are on the three pivoting rocket engines 53, 53a 54.59 attached. The wings 54, 59 are used to control the spacecraft in the earth's atmosphere, they change their position when the rocket engines 53,53a be swiveled. They work when performing a turn in the earth's atmosphere the wings 54 each act as aileron when the rocket engines 53 pivoted will.

The wings 59 act as elevators, they are through the shaft 59a firmly connected to the rocket engine 53a. The wings 59 can also pivotally mounted on the spacecraft independently of the rocket engine 53a will.

Another possibility is for a turn in the earth's atmosphere given. A wing 54 is moved so that the spacecraft see its Transverse axis changed. At the same time the wings 59 are moved so that the spacecraft changes tail-heavy to its longitudinal axis. So it is possible to bring the spacecraft into a bank position in the earth's atmosphere and thus a To bring about a change of direction or curve.

The spacecraft behaves similarly to a change of flight direction in interplanetary space, with the difference that not the swiveling rocket engines cause a different flight direction, but the air masses on the different provided wings and act on the underside of the spacecraft. In which In the construction principle, a manual rudder can be dispensed with.

The rocket engines 53,53s are switched off in the earth's atmosphere, they can also contribute to support.

The pilot 52a has an optimal field of vision through the canopy 52.

On the return flight to planet earth or upon re-entry into the earth's atmosphere the rocket engines 53 can be pivoted 180 degrees in the opposite direction to possibly to produce a counter-thrust that will reduce the speed of the spacecraft can. The rocket engines 53,53a can perform corrective shocks to the position of the Stabilize spacecraft.

The londebeine 60,61,62 which in the plan view Fig. 24 in the retracted State are shown, serve a possible landing on the moon. There are analogous Similar landing legs as in the construction Fig.12 to Fig.14, where the landing legs are also shown in the extended state. The principle of operation of the landing legs is treated in the constructions Fig. 117 to Fig. 125.

The landing gear 64,65,66 is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is analogously the same undercarriage as in the construction in Fig. 27 to Fig. 29, where the chassis is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 27 shows a side view, FIG. 28 a top view, and FIG. 29 is a front view of a spacecraft.

The spacecraft is designed as a tactical space interceptor but can also be designed for other tasks. This spacecraft can form part of the said defense system.

The scale 76 enables a dimensioning that of course deviates can.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space a larger radius of action with corresponding tonk volumes cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The launch from planet earth is carried out with two turbine jet engines 70, they are supposed to take the spacecraft from the ground to the uppermost layers of the air bring the earth's atmosphere. That can through possible so-called Intermediate refueling in the air can be achieved.

In the earth's atmosphere the spacecraft is equipped with elevator and rudder controlled. The rudders 72, 74 are mounted on the wings 71, the rudders 75 are attached to the rear fuselage.

The support surfaces 71 are made stronger in order to provide an optimal tank volume in the wings. The additional tanks provide another tank volume 69, which can be carried along, but weapon systems can also be used in their place e.g. rockets are carried.

The spacecraft is designed with three rocket engines 68 which focus on the control or the execution of flight maneuvers in the interplanetary Serve space and designed with two built-in rocket engines 79, the focus serve to accelerate in interplanetary space.

Xit the larger-sized rocket engines 73 can work together with the three rocket engines 68 an optimal acceleration can be carried out. A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The rocket engines 68 are switched off in the earth's atmosphere, they can also contribute to support.

The canopy 67 provides the pilot 67a with an optimal field of vision.

On the return flight to planet earth or on re-entry into the earth's atmosphere can the two rocket engines 68, which are attached to the wings 71, be swiveled 180 degrees in the opposite direction to possibly generate a counter-thrust, which can reduce the speed of the missile. The rocket engines 68 can perform corrective shocks to stabilize the spacecraft's attitude.

The landing legs 77,78,79 which in the top view Fig. 28 in the retracted State are shown, serve a possible landing on the moon. There are analogous Similar landing legs as in the construction Fig.12 to Fig.14, where the landing legs are also shown in the extended state. The principle of operation of the lands legs is treated in the constructions Fig. 117 to Fig. 125.

Landing leg flaps are attached to the wings 71; they are aerodynamic conditional. The landing leg flaps 87, 88, 89, 91 are shown in the retracted state, on the other hand, the landing leg flaps 90, 92 are shown in the extended state position of the landing leg flaps is analogously representative of all shown Spacecraft designed with landing legs.

The landing gear 80,81,82 is used for take-off or landing on the Planet earth, it is shown in the top view Fig. 28 in the retracted state, however, shown in the front view Fig. 29 in the extended state.

On the wings 71 are attached undercarriage flaps, they are aerodynamic conditional. The landing gear flaps 85,85,86 ii are shown in the retracted state, however, the landing gear flap 84 is shown in the extended state. The representation the landing gear flaps is analogously representative of all spacecraft shown, which are designed with trolleys.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 30 shows a top view, FIG. 31 a front view, and FIG. 52 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 101 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and shown separately.

This space missile is designed to cover a larger radius of action to be able to form in interplanetary space with an appropriately designed tank volume and a possible optimal acceleration and execution of fast flight maneuvers in interplanetary space.

The spacecraft can be launched from a carrier aircraft in the earth's atmosphere be dropped at a high altitude, from where the flight into interplanetary space begins, similar to the American one Rocket aircraft zX-15 "that in large High was dropped from a jet aircraft "B-52".

Another possibility is the spacecraft from the ground to start off and with possible so-called intermediate inks in the air the interpltnetaren To reach Haum.

The spacecraft is designed so that the underside of the cell body 93 can act as a wing in the earth's atmosphere.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are six pivotable rocket engines 95 on the spacecraft attached, each connected to a shaft in the bearing 100. The engine cowling 96 is connected to the rocket engine 9S, it tet due to aerodynamics. One possible swiveling rocket engine suspension is shown in the constructions Fig. 135 to Fig. 142.

Due to the visible surfaces 94, the pilots have an optimal elick field. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 95, each of which is attached to the engine cowling 96 is attached, can be swiveled 180 degrees in the opposite direction by possibly one To generate counter-thrust that can reduce the speed of the spacecraft. The two rocket engines 95, which are located on the underside, can be used for support participate. The rocket engines 95 can also perform corrective thrusts to stabilize the position of the spacecraft.

The landing legs 97,98,99 which in the top view Fig. 30 in the retracted State shown, however in the front view Fig.31 and side view Fig.32 are shown in the extended state, serve a possible landing on the Moon. The functional principle of the landing legs is shown in the sound instructions Fig. 117 to Fig. 125 treated. The spacecraft can be designed with a landing gear, a longer stay in interplanetary space is advisable.

Another embodiment of the invention is shown in FIG drawing and is described in more detail below.

FIG. 33 shows a top view, FIG. 34 a front view, and FIG. 35 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 108 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to cover a larger radius of action to be able to form in interplanetary space, with an appropriately designed tank volume and a possible optimal acceleration and execution of fast flight maneuvers in interplanetary space.

The spacecraft can be launched from a carrier aircraft in the earth's atmosphere be dropped at a high altitude, from where the flight into interplanetary space begins, similar to the American rocket plane "X-15" that at a high altitude of one Jet plane "B-52" was dropped.

Another quick option is to get the spacecraft off the ground to start off and with possible so-called intermediate refueling in the air the interplanetary To reach space.

The spacecraft is designed so that the underside of the cell body 102 can act as a wing in the earth's atmosphere.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are six pivotable rocket engines 105 on the spacecraft attached, each connected to a shaft in the bearing 107. The trieuwork cladding 104 is connected to the rocket engine 105, it is a.rodjyyiisch conditioned.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The pilots have an optimal field of vision through the viewing surfaces 103. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

The wings tO6 are used to control the spacecraft in the Earth's atmosphere 'they are pivotably mounted in the bearings 112 and can be independent be pivoted from each other.

For an establishment in the earth's atmosphere, a wing is first used 106 moves, this changes the Ratrlugkörper to its transverse axis. Immediately then the second wing 106 is pivoted in the same direction, which causes that the spacecraft changes its position tail-heavy to its longitudinal axis. It The air masses now act on the pivoted wings 106 and on the underside of the spacecraft.

So it is possible in a spacecraft in the earth's atmosphere To bring transverse position and thus to bring about a change of direction or curve. the Dashed and dotted lines 106a show the wings 106 in a possible pivoted way State. After the change in direction, the wings 10 are back in their illustrated Swiveled starting position. The principle of construction can be based on a conventional one Rudder is omitted.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 105, each of which is attached to the engine cowling 104 is attached to be swiveled 180 degrees in the opposite direction, possibly by one To generate counter-thrust that can reduce the speed of the spacecraft. The rocket engines 105 can also perform corrective thrusts for attitude to stabilize the spacecraft.

The landing legs 109,110,111 which in the top view Fig. 33 in the retracted State shown, however in the front view Fig. 34 and side view Fig. 35 are shown in the extended state, serve a possible landing on the Moon. The functional principle of the landing legs is shown in the constructions Fig. 117 to Fig. 125 treated.

The landing gear 109a, 110a is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is analogously the same undercarriage as in the construction Fig. 36 bit Fig. 38, where the landing gear is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing dargeatellt and is described in more detail below.

FIG. 36 shows a top view, FIG. 37 a front view, and FIG. 38 is a side view of a spacecraft.

This Raumilugkörper can for the said transport system and for the said defense system can be designed. The scale 122 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This space missile is designed to cover a larger radius of action to be able to form in interplanetary space, with an appropriately designed tank volume and a possible optimal acceleration and execution of fast flight maneuvers in interplanetary space.

The spacecraft can be launched from a carrier aircraft in the earth's atmosphere be dropped at a high altitude, from where the flight into interplanetary space begins, similar to the American rocket plane "X-15" that at a high altitude of one Jet plane "B-52" was dropped.

Another possibility is the spacecraft from the ground to start off and with possible so-called intermediate banks in the air the interplanetary To reach space.

The spacecraft is designed so that the underside of the cell body 113 i'n the earth's atmosphere can act as a wing.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are six pivotable rocket engines 115 on the spacecraft attached, each connected to a shaft in the bearing 116. The engine cowling 114 is connected to the rocket engine 115, it is aerodynamically determined.

A possible pivoting rocket engine mount is shown in the Constructions Fig. 135 to Fig. 142 shown.

The viewing areas 123 give the pilots an optimal field of vision. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

In the earth's atmosphere the spacecraft has two rudders 118 and controlled by four elevators 117, the one at the bottom of the cell body 113 attached elevator 117 can also act as landing flaps.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 115, each of which is attached to the engine cowling 114 is attached, can be swiveled 180 degrees in the opposite direction by possibly one To generate counter-thrust that can reduce the speed of the spacecraft. The two rocket engines 115, which are located on the underside, can be used for support participate. The rocket engines 115 can also perform corrective thrusts to stabilize the position of the spacecraft.

The landing legs 119,120,121 which in the top view Fig. 36 in the retracted State shown, however in the front view Fig. 37 and side view Fig. 38 are shown in the extended state, serve a possible landing on the Moon. The principle of functioning of the landing legs is shown in the constructions Fig. 117 to Fig. 125 treated.

The landing gear 124,125 is used for take-off or landing on the Planet earth, it is shown in the top view Fig. 36 in the retracted state, however, in the front view Fig.37 and side view Fig.38 in the extended state shown.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 39 shows a top view, FIG. 40 a front view, and FIG. 41 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 133 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to cover a larger radius of action to be able to form in interplanetary space, with one corresponding applied tank volume and a possible optimal beach acceleration and execution of rapid flight maneuvers il interplanetary space.

The spacecraft can be from a carrier aircraft in the earth's atmosphere be thrown at a great height, from where the flight into the interpianetarian space begins, similar to the American rocket plane "X-15" that at a high altitude of one Jet plane "E, 52" was dropped.

Another possibility is the spacecraft from the ground to start off and with possible so-called intermediate refueling in the air the interplanetary To reach space.

The spacecraft is designed so that the underside of the Zsllenkörper 126 can act as a wing in the earth's atmosphere.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are six pivotable rocket engines 128 on the spacecraft attached, each connected to a shaft in the bearing 159. The engine cowling 127 is connected to the rocket engine 128, it is aerodynamically determined.

A possible pivoting rocket engine suspension is in the sound structures Fig. 135 to Fig. 142 are shown.

The pilots have an optimal field of vision through the viewing surfaces 132. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

On the two rocket engines 128 with the engine cowlings 127 the wings 129 are attached, they change their position when the respective Rocket engines 128 are pivoted. The wings 129 act when there is a change their position as elevator, they can also function as ailerons take over. In the interaction of the elevator resp.

Wings 129 with rudder 131 can move the spacecraft into the earth's atmosphere can be controlled, the rear wings 130 are firmly aebaut.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 128, each of which is attached to the engine cowling 127 and the wing 129 attached. is to be swiveled 180 degrees in the opposite direction about possible wise to create a counter-stroke that increases the speed of the spacecraft can decrease. The rocket engines 128 can also Perform corrective shocks to stabilize the spacecraft's attitude.

The landing legs 134,135,136 which in the top view Fig. 39 in the retracted State shown, however in the front view Zig 40 and side view Fig. 41 are shown in the extended state, serve a possible landing on the Moon. The functional principle of the landing legs is shown in the constructions Fig. 117 to Fig. 125 treated.

The landing gear 137,138 is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is analogously the same undercarriage as in the construction Fig. 36 to Fig. 38, where the chassis is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 42 shows a top view, FIG. 43 a front view, and FIG. 44 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 146 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal construction, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth with its own drive the interplanetary lukewarm: can reach and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution can perform plugi overtures.

The take-off from planet earth is carried out with two dual-circuit engines 14. The two dual-circuit engines 145 are designed for a thrust deflection, thereby VTOL properties are given.

The dual-circuit engine was derived from the turbine jet engine. at a dual-circuit engine that is designed for thrust deflection, the jet of the host Dual-circuit engine not passed through a single pipe at the end, but through two nozzles on each side of the twin-circuit engine. The nozzles can be swiveled within a short time. The English fighter aircraft wP-1127 " is designed with a dual-circuit engine for thrust deflection (James J. Haggerty Book "Der Flug" TIKE-LIFE International '§ederland' N.V. Born in 1970, pages 84 and 153>.

The two twin-circle engines 145 are supposed to lift the spacecraft off the ground bring them to the uppermost parts of the earth's atmosphere. That can by possible so-called intermediate refueling in the air can be achieved.

The spacecraft is designed so that the underside of the cell body 140 can act as a wing in the earth's atmosphere.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that will be carried are not shown.

There are four pivotable rocket engines 142 on the spacecraft attached, each connected to a shaft in the bearing 143. The engine cover 141 is connected to the rocket engine 142, it is aerodynamically determined. One possible swiveling rake tentri ebwerka suspension is shown in the constructions Fig. 13 to 142 shown.

The rocket engines 142 are switched off in the earth's atmosphere, they can also contribute to support.

The pilots have an optimal field of vision through the viewing surfaces 144. The pilot situation is reflected in the respective interior structure or

shown in the construction Fig. 66 to Fig. 69.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 142, each of which is attached to the engine cowling 141 is attached to be swiveled 180 degrees in the opposite direction, possibly by one To generate counter-thrust that can reduce the speed of the spacecraft. The rocket engines 142 can also perform corrective thrusts for attitude to stabilize the spacecraft.

The landing legs 147,148,149 which in the top view Fig. 42 in the retracted State shown, however in the front view Fig. 43 and side view Fig. 44 shown in the extended state are, serve a possible Landing on the moon. The principle of operation of the landing legs is in the constructions Fig. 117 to Fig. 125 treated.

The landing gear 130,151 is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is a similar chassis as in the construction Fig. 36 to Fig. 38, where the chassis is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 45 shows a top view, FIG. 46 a front view, and FIG. 47 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 159 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth n; can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The launch from planet earth is carried out with two turbine jet engines 157, they are supposed to take the spacecraft from the ground to the uppermost layers of the air bring the earth's atmosphere. This can be done by possible so-called intermediate refueling in of the air.

The spacecraft is designed so that the underside of the cell body 152 can act as a wing in the earth's atmosphere.

The wings 158 are used to control the spacecraft in the Earth's atmosphere, they are pivotably mounted in the bearings 160 and can be independent be pivoted from each other.

For a turn in the earth's atmosphere, a wing is needed first 158 moves, as a result of which the spacecraft changes to its transverse axis. Immediately then the second wing 158 is pivoted in the same direction, which causes that the spacecraft changes its position tail-heavy to its longitudinal axis. It The air masses now act on the pivoted wings 158 and on the underside of the spacecraft.

So it is possible in a spacecraft in the earth's atmosphere To bring transverse position and thus to bring about a change of direction or curve. the Dashed and dotted lines show the wings 158 in a possible pivoted way State. After the change in direction, the wings 158 are again in their illustrated Swiveled starting position. The construction principle can be based on a conventional Rudder can be dispensed with, but the spacecraft can be used for support a rudder 166 can be laid out.

Due to the shape of the Rsumflu8törpers an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are six pivotable rocket engines 154 on the spacecraft attached, each connected to a shaft in the bearing 155. The engine clothing 153 is connected to the rocket engine 154, it is aerodynamically determined.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The rocket engines 154 are switched off in the earth's atmosphere, they can also contribute to support.

The pilots have an optimal field of vision through the viewing surfaces 156. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

When flying back to planet earth or when re-entering the earth's atmosphere can include the two rocket engines 154, each of which is attached to the engine cowling 153 is attached, can be swiveled 180 degrees in the opposite direction by possibly one To generate counter-thrust that can reduce the speed of the spacecraft. The rocket engines can also perform corrective thrusts to correct the position of the Stabilize spacecraft.

The landing legs 161,162,163 which in the top view Fig. 45 in the retracted State shown, but in the front view Fig. 46 and side view Fig. 47 are shown in the extended state, serve a possible landing on the moon. The construction principle of the landing legs is used in the constructions Fig. 117 to Fig. 125 treated.

The landing gear 164,165 is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is a similar chassis as in the construction lig.36 bia Fig. 38, where the landing gear is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 48 shows a top view, FIG. 49 a front view, and FIG. 50 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 173 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal construction, of which the constructions Fig66 to Fig.87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The take-off from planet earth is done with three hinged ones Turbine jet engines 172, they are supposed to drive the spacecraft from the ground to in bring the uppermost layers of air to the earth's atmosphere. That can by possible so-called Intermediate refueling in the air can be achieved.

The Rauiflugkörper is designed so that the underside of the cell body 167 can act as a wing in the earth's atmosphere.

Due to the arrangement of the three swiveling turbine jet engines 172 to each other can when thrust generation of the three turbine jet engines 172 one Change of direction of the spacecraft by panning in the earth's atmosphere can be achieved. A change of direction with the turbine jet engines 172 will occur has a similar effect as the interaction of three rocket engines for a change of direction in the interplanetary space which is shown in the scheme Fig.6 to Fig.11.

If the spacecraft reaches through during a flight in the earth's atmosphere Pivoting the turbine jet engines 172 and thus changing the thrust direction Position as shown in the side view Fig. 10 and the front view Fig. 11 are effective the air masses on the underside of the cell body 16l. The spacecraft reacts to the resistance of the air masses like a conventional airplane, it swings in another attitude or bank angle.

The process is favored because the turbine jet engines 172 move the spacecraft with its thrust, thereby accelerating the flight maneuver can be reached. So it is possible the spacecraft in the earth's atmosphere to bring into a transverse position and thus to bring about a change of direction or curve.

Through the pivotably mounted turbine jet engines 172 are Given VTOL properties. He can by the arrangement of the three turbine jet engines 172 landed exactly to each other or

to be started.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are four pivoting rocket engines 169 on the spacecraft attached, each connected to a shaft in dci bearing 170. The drive The fairing 168 is connected to the rocket engine 169, it is aerodynamic conditional.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The rocket engines 169 are switched off in the earth's atmosphere, they can also contribute to support.

The pilots have an optimal field of vision through the visible surfaces 171. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 169, each of which is attached to the engine cowling 168 is attached to 180 degrees may be swung in the opposite direction to produce a counter-thrust that will reduce the speed of the spacecraft can. The rocket engines 169 can also perform corrective thrusts around the Stabilize the spacecraft's position.

The landing legs 174, 175, 176 which are retracted in the plan view of FIG State shown, however in the front view rig.49 and side view Fig.5O are shown in the extended state, denoting a possible landing on the Moon or on planet earth. The design principle of the landing legs is shown in the constructions Fig. 117 to Fig. 125 treated.

A smaller wheel can be attached to each landing leg. So can three wheels act as landing gear to keep the spacecraft on the floor of the planet Earth can be moved, possible wheels are not shown.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 51 shows a top view, FIG. 52 a front view, and FIG. 53 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 189 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options possibilities for the interior construction, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The start from planet earth is done with a turbine jet engine 183 that the spacecraft from the earth to the uppermost layers of the earth's atmosphere should bring. This can be achieved by possible so-called intermediate refueling in the air will.

The Maum missile is designed so that the underside of the cell body 177 can act as a wing in the earth's atmosphere.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are six pivoting rocket engines 179 on the spacecraft attached, which are each connected to a shaft in the bearing 180. The engine cowling 178 is connected to the rocket engine 179, it is aerodynamically conditioned.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The pilots have an optimal field of vision through the viewing surfaces 186. The pilot situation is in the respective interior structure or in the construction Fig. 66 to Fig. 69 are shown.

On the two rocket engines 179 with the engine cowlings 178 the wings 181 are attached, they change their position when the respective Rocket engines 179 are pivoted. The wings 181 act when there is a change their position as elevator, they can also function as ailerons take over. In the interaction of the elevator resp.

Wings 181 with rudder 185 can move the spacecraft into the earth's atmosphere can be controlled, the rear wings 182 are permanently attached. The small elevator 184 is used for support or flight corrections.

The rocket engines 179 are switched off in the earth's atmosphere, they can also contribute to support.

When flying back to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 179, each of which is attached to the engine cowling 178 and the wing 181 is attached, can be pivoted 180 degrees to possibly generate a counter-thrust that would reduce the speed of the spacecraft can decrease. The rocket engines 179 are also capable of corrective thrusts to stabilize the position of the rocket missile.

The landing legs 190,191,192 which in the top view Fig. 51 in the retracted State shown, however in the front view Fig. 52 and side view Fig. 53 are shown in the extended state, serve a possible landing on the Moon. That Ion construction principle of the landing legs is used in the constructions Fig. 117 to Fig. 125 treated.

The landing gear 187> 188 is used for take-off or landing on there Planet earth, it is shown in the extended state.

It is analogously the same undercarriage as in the construction Fig. 36 to Fig. 38, where the chassis is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 54 shows a top view, FIG. 55 a front view, and FIG. 56 shows a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 203 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 99 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The launch from planet earth is carried out with two turbine jet engines 197, they are supposed to take the spacecraft from the ground to the uppermost layers of the air bring the earth's atmosphere. This can be done by possible so-called intermediate refueling in of the air.

The Ramflugkdrper is designed so that the underside of the cell body 199 can act as a wing in the earth's atmosphere.

The wings 198 are each rigid on the turbine jet engine 197 attached. The wings 200 can act as elevators, they are pivotable mounted in bearings 207.

Is the interaction of the elevators or wings 200 with the rudders 199 can control the spacecraft in the earth's atmosphere will. The shape of the spacecraft ensures an optimal tank volume, also in the outdoor areas, possible. Possible additional tanks that can be carried along, are not shown.

There are four pivoting rocket engines 194 on the Reum missile attached, each connected to a shaft in the bearing 195. The rocket engines 194 are switched off in the earth's atmosphere, they can also contribute to support.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The pilots have an optimal field of vision through the viewing surfaces 196. The pilot situation is reflected in the respective interior structure or

shown in the construction Fig. 66 to Fig. 69.

When flying back to planet earth or when re-entering the earth's atmosphere the two turbine jet engines 197 can generate a so-called thrust reversal, to possibly reduce the speed of the spacecraft. At a Thrust reversal, the full force of the jet is directed forward and thereby the speed decreased (James J. Haggerty's book "The Flight" TIME-LIFE International 'Nederland' N.V. Year 1970, page 116).

Two or four rocket engines 194 can also be pivoted in this way that they are at an angle of approximately 90 degrees, based on the longitudinal axis of the spacecraft, opposite to the flight direction can generate a counter-thrust to possibly reduce the speed of the spacecraft. The rocket engines 194 can also perform corrective shocks to stabilize the spacecraft's attitude.

tie landing legs 204,205,206 which in the top view Fig. 54 in the retracted State shown, however in the front view Fig. 55 and side view Fig. 56 are shown in the extended state, serve a possible landing on the Moon. The construction principle of the landing legs is shown in the contractions in Fig. 117 treated to Fig. 125.

The landing gear 201, 202 is used for takeoff or landing aut .tm Planet earth, it is shown in the extended state. It is analogously that same undercarriage as in the construction Fig. 36 to ring.38, where the undercarriage also is shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 57 shows a plan view, FIG. 58 shows a front view, and FIG. 59 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 221 enables dimensioning which of course can differ.

The shape of the rocket missile offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The take-off from planet earth is carried out with two dual-circuit engines 213. The two dual-circuit engines 213 are designed for a thrust deflection, thereby If VTOL properties are given, they should take the spacecraft from the ground up bring them to the uppermost layers of the earth's atmosphere. That can by possible so-called intermediate refueling in the air can be achieved.

The spacecraft is designed so that the underside of the cell body 208 can act as a wing in the earth's atmosphere.

In the earth's atmosphere, the spacecraft has a rudder 217 and controlled with four elevator 214,214a, with the elevator 214a in addition can act as landing flaps.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are four pivotable rocket engines 210 on the spacecraft attached, each connected to a shaft in the bearing 211. The engine cowling 209 is connected to the rocket engine 210, it is aerodynamically determined. the Rocket engines 210 are switched off in the earth's atmosphere, they can also be used for Contribute support.

A possible pivoting rocket engine mount is included in the constructions Fig. 135 to Fig. 142 are shown.

The pilots have an optimal field of vision through the viewing surfaces 212. The pilot situation is reflected in the respective interior structure or

shown in the construction Fig. 66 to Fig. 69.

When iAckSlug to planet earth or when re-entering the earth's atmosphere can use the two rocket engines 210, each of which is attached to the engine cowling 209 is attached, can be swiveled 180 degrees in the opposite direction by possibly one To generate counter-thrust that can reduce the speed of the spacecraft. The rocket engines 210 can also perform corrective thrusts for attitude to stabilize the spacecraft.

The landing legs 2t8,219,220 which in the top view Fig. 57 in the retracted State shown, however in the front view Fig. 58 and side view Fig. 59 are shown in the extended state, serve a possible landing on the Moon. The construction principle of the landing legs is shown in the constructions Fig. 117 treated to Fig. 125.

The landing gear 215,216 is used for take-off or landing on the Planet earth, it is shown in the extended state.

It is a similar chassis as in the tonstruktion Fig. 36 to Fig. 38, where the chassis is also shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 60 shows a plan view, FIG. 61 shows a front view, and FIG. 62 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The scale 229 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 99 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth with its own drive the interplanetary space can reach and in interplanetary space with a corresponding tank volume Cover a larger radius of action, achieve optimal acceleration and a can carry out rapid execution of flight maneuvers.

The take-off from planet earth is done with three hinged ones Turbine jet engines 227, they are supposed to drive the spacecraft from the ground to in bring the uppermost layers of air to the earth's atmosphere. That can by possible so-called Intermediate refueling in the air can be achieved.

The spacecraft is designed so that the underside of the cell body 222 can act as a wing in the earth's atmosphere.

In the earth's atmosphere, the spacecraft has two rudders 228 and controlled with four elevators 23C, 2.0a, with the elevator 230a in addition can act as landing flaps.

The spacecraft can also only use three turbine jet engines 227 can be controlled in the earth's atmosphere. Due to the arrangement of the three turbine jet engines 227 to each other, when the three turbine jet engines 227 generate thrust, a Change of direction of the spacecraft can be achieved by pivoting. A change of direction with the turbine jet engines 227 is effected similarly to the interaction of three rocket engines for a change of direction in interplanetary space that is shown in the scheme Fig.6 to Fig.11. Reached the spacecraft at a flight in the earth's atmosphere by pivoting the turbine jet engines 227 and thus the thrust direction change the situation as in the side view Fig.10 and front view 11, the air masses act on the underside of the cell body 222. The spacecraft reacts to the resistance of the air masses like a conventional one Airplane, it turns into a different flight position or bank position.

The process is favored because the turbine jet engines 227 move the spacecraft with its thrust, thereby accelerating the flight maneuver can be reached. So it is possible the spacecraft in the earth's atmosphere to bring into a transverse position and thus to bring about a change of direction or curve.

The turbine jet propulsion units 227 are mounted so that they can be swiveled Given VTOL properties. He can by the arrangement of the three turbine jet engines 227 landed exactly to each other or

to be started. A conventional landing or take-off is also possible given.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are four pivotable rocket engines 224 on the spacecraft attached, each connected to a shaft in the bearing 225. The engine cowling 229 is connected to the rocket engine 224, it is aerodynamically determined. the Rocket engines 224 are switched off in the earth's atmosphere, they can also be used for Contribute support.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

By rotating the viewing surfaces 226, the pilots have an optimal field of view. The pilot situation is reflected in the respective interior structure or

shown in the construction Fig. 66 to Fig. 69.

When flying back to planet earth or when re-entering the earth's atmosphere can include the two rocket engines 224, each attached to the engine cowling 229 is attached, can be swiveled 180 degrees by possibly one To generate counter-thrust that can reduce the speed of the spacecraft. The rocket engines 224 can also perform corrective thrusts for attitude to stabilize the spacecraft.

The landing legs 233,234,235 which in the top view Fig. 60 in the retracted State shown, however in the front view Fig. 61 and side view Fig. 62 are shown in the extended state, serve a possible landing on the Moon. The tone construction principle of the landing legs is shown in the constructions Fig. 117 treated to Fig. 125.

The landing gear 231,232 is used for take-off or landing on DEX Planet earth, it is shown in the extended state. It is analogously a Similar undercarriage as in the construction Fig. 36 to Fig. 38, where the undercarriage is also is shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 63 shows a top view, FIG. 64 a front view, as FIG. 65 is a side view of a spacecraft.

This spacecraft can be used for the said transport system and for the said defense system can be designed. The measuring rod 246 enables dimensioning which of course can differ.

The shape of the spacecraft offers various options Possibilities for the internal structure, of which the constructions Fig. 66 to Fig. 87 and FIGS. 93 to 95 are intended to be representative and are shown separately.

This spacecraft is designed to be taken from an airfield on planet earth can reach interplanetary space with its own drive and in interplanetary space, with the appropriate tank volume, a larger radius of action cover, achieve an optimal acceleration and a fast execution of flight maneuvers.

The launch from planet earth is carried out with two turbine jet engines 240, they are supposed to take the spacecraft from the ground to the uppermost layers of the air bring the earth's atmosphere. This can be done by possible so-called intermediate refueling in of the air.

The spacecraft is designed so that the underside of the cell body 236 can act as a wing in the earth's atmosphere.

The wings 242 can act as elevators, they are pivotable mounted in bearings 249. In the interaction of the elevators or wings 242 with the rudders 241 can steer the spacecraft in the earth's atmosphere will.

The shape of the spacecraft ensures an optimal tank volume, also possible in the outdoor areas. Possible additional tanks that are carried are not shown.

There are four pivotable rocket engines 237 on the spacecraft attached, each connected to a shaft in the bearing 238. The rocket engines 297 are switched off in the earth's atmosphere, they can also contribute to support.

A possible pivoting rocket engine mount is included in the designs Fig. 135 to Fig. 142 are shown.

The pilots have an optimal field of vision through the visible surfaces 299. The pilot situation is reflected in the respective interior structure or

shown in the construction Fig. 66 to Fig. 69.

When flying back to planet earth or when re-entering the earth's atmosphere the two turbine jet engines 240 can produce a so-called thrust reversal, to possibly reduce the speed of the spacecraft. At a Thrust reversal, the full force of the jet is directed forward and thereby the speed decreased.

Two or four rocket engines can also be pivoted 237 80 that they are at an angle of approximately 30 degrees, based on the longitudinal axis of the spacecraft, opposite to the flight direction can generate a counter-thrust to possibly reduce the speed of the spacecraft. The rocket engines 297 can also perform corrective shocks to stabilize the spacecraft's attitude.

The landing legs 247,248,249 which in the top view Fig. 63 in the retracted State shown, however in the front view Fig. 64 and side view Fig. 65 are shown in the extended state, serve a possible landing the moon. The construction principle of the landing legs is shown in the constructions Fig. 117 treated to Fig. 125.

The landing gear 244,245 is used for take-off or landing on the Planet earth, it is shown in the extended state. It is analogously a Similar undercarriage as in the construction Fig. 36 to Fig. 38, where the undercarriage is also is shown in the retracted state.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 66 and FIG. 67 show cross sections, FIG. 68 a longitudinal section, and FIG. 69 shows a plan view of an interior structure for spacecraft like them 30 to 65 are shown structurally in the constructions.

This interior structure is designed for the transport of people.

With the interior structure shown, the spacecraft Fig. 30 to Fig. 65 can be designed depending on your choice. The scale 268 enables dimensioning which of course can differ.

In the cell core 250 for the spacecraft is the breeding ground 251. On the intermediate floor 251 there are three bulges 252 for the landing legs and the pilot chair 253 for two pilots. Through the visible surfaces the two pilots have an optimal field of vision. The viewing angles 255,256,257 show the field of view to be seen through the viewing surfaces from the pilot's point of view 254 in a pilot's chair 253.

The elevator 258 forms the main entrance to the spacecraft, with ihi can persons b £ w. Astronauts in space suits reach the lunar floor or leave the spacecraft in interplanetary space, objects can also be moved (-spacesuits- Arthur C. Clarke book "Man and Space" TIME-LIFE International Nederland 'N.V. Year 1970, pages 138 to 139).

There is always fresh in the cell core 250 of the spacecraft or treated breathing air. For processing used air, air pressure etc. a system similar to that used in the American aerospace company is used "Mereury" was applied (-Preparation of the breath- Arthur C. Clarke book "Mensch and space "TIME-LIFE International 'Nederland' N.V. Volume 197C, pages 81 and 91).

To prevent breathing air from escaping when leaving or entering the Avoiding spacecraft in interplanetary space or on the moon is in of the airlock 259, a pressure equalization has been carried out beforehand (-function airlock- Lynn Poole book "Die Reise ins Weltall" Boje-Verlag Stuttgart, born 1957, pages 130 to 132) The opening located near the engine room 22a 261 can be used as an emergency exit in an emergency with a retractable ladder 260 otherwise it is hermetically sealed with a flap to prevent it from escaping to avoid the air.

The opening 261 located in the vicinity of the pilot's seat 253 Can also be used in an emergency with a retractable ladder 260 as an emergency exit otherwise it is hermetically sealed with a flap around a To prevent the air from escaping, it can also be used as an entrance or exit on the Serving planet earth.

The crew cabins each contain two beds 265 and two storage compartments 264, the door 265 can be hermetically sealed. A bench 266 is used for possible gatherings of the crew, a possible one Table is not shown. A cabinet 267 holds various items.

The engine room 262a can be the system for pivoting the rear Rocket engines take up. The cell core 250 can be laid out with further partition walls that can be provided with hermetically sealable doors, sanitary facilities are not shown.

The two spaces 262 located next to the cell core 250 can Include a possible landing gear, which in the spacecraft Fig.36 to Fig.38 in retracted or extended state is shown. The two rooms 262 can Fuel tanks contain and equipment that is required to function to enable the spacecraft to function properly.

A spacecraft designed with the interior structure shown can be used as a personnel carrier for people or astronomers from planet earth to a future possible space station or to the moon or to pick it up.

For the construction of future space stations in interplanetary space or on the moon, this internal structure can be used in conjunction with a spacecraft of the constructions Fig. 30 to Fig. 65, as accommodation for people in the interplanetary Space or on the moon.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 70 and FIG. 71 show cross sections, FIG. 72 a longitudinal section, and FIG. 73 shows a plan view of an interior structure for spacecraft like them in the constructions Fig. 30 to Fig. 65 are shown structurally.

This internal structure is designed for the transport of loads or devices. With the interior structure shown, the spacecraft Fig. 30 to Fig. 65 can each be laid out at your discretion. The scale 279 allows dimensioning the can of course differ.

The intermediate floor is located in the cell core 269 for the spacecraft 270. On the intermediate floor 270 there are three bulges for the landing legs and the pilot seat 271 for two pilots. Because of the visible surfaces, the two have Pilots each get an optimal field of vision from the pilot's seat 271.

The pilot's chair 271, the elevator 272, the air lock 273, the Emergency exit 274, as well as a system for used breathing air, air pressure etc, are analogously the same facilities as they are in the construction Fig.66 to Fig. 69 are shown and described in detail. Emergency exit 274 can also as input or

Serving output on planet earth, sanitary facilities are not shown. Fresh air is always in the cell core 269.

The internal structure is designed as a cargo hold. All loads or

oUrate with which the cargo hold is loaded are for the transport attached in the hold.

On planet earth, the cargo hold can be accessed with a freight elevator 277 through the smaller cargo opening with cargo flaps 276 and for larger loads and load or unload devices through the larger cargo opening with cargo flaps 275. be unloaded.

In interplanetary space, the cargo space can be opened through the larger cargo opening can be unloaded or loaded with the freight flaps 275, it can also be loaded through the smaller one Freight opening hit the freight flaps 276 to be unloaded or loaded.

On the moon, the cargo hold can be accessed by the 277 freight elevator Unload or unload smaller cargo openings with cargo flaps 276.

be loaded.

The cross section Fig. 71 and the longitudinal section Fig. 72 show the smaller one The cargo opening with the cargo flaps 276 and the larger cargo opening with the cargo flaps 275 in the open state, as well as the goods elevator 277 in the extended state. The Qrundries Fig. 73 shows the two cargo openings in the closed state. Of the Cross-section Fig. 70 shows the relationship with a representation of the visible surfaces with the intermediate floor 270.

The two spaces 278 located next to the cell core 269 can Include a possible landing gear, which in the spacecraft Fig.36 to Fig.38 in retracted or extended state is shown. The two rooms 278 can Fuel tanks contain as well as systems that are required to ensure proper functioning of the spacecraft. The engine room 278a can pivot the system the rear rocket engines.

A space missile designed with the interior structure shown is, as a load transporter, loads or devices from planet earth to a future possible space station or transport to the moon or pick up.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 74 and FIG. 75 show cross sections, FIG. 76 a longitudinal section, and FIG. 77 shows a plan view of an interior structure for spacecraft like them in the constructions Fig. 30 to Fig. 65 are shown structurally.

This interior structure is for observing the stars or the universe, designed as an observatory. With the interior structure shown, one or more Spacecraft of the constructions Fig. 30 to Fig. 65, depending on your choice, can be designed. The scale 295 enables a dimensioning that can of course differ.

The intermediate floor is located in the cell core 280 for the spacecraft 281. On the intermediate floor 281 there are three bulges for the landing legs and the pilot seats 282 for two pilots. Because of the visible surfaces, the two have Pilots each get an optimal field of view from the pilot's chair 282.

The pilot seats 282, the elevator 283, the airlock 284, the emergency exits 283a, as well as a system for used breathing air, air pressure, etc., are analogous the same facilities as detailed in the construction Fig. 66 to Fig. 69 can be represented and described. The one near the pilot's seat 282 located emergency exit 28pa, can also be used as an entrance or exit on the planet Serving earth, sanitary facilities are not shown.

A rotatable and height-adjustable telescope 285 allows through a face 286 corresponding to the various requirements, the stars or the universe can be observed in illterplanetsren space. The viewing surface 286 can also be designed so that they can be covered with protective flaps, the protective flaps act similarly as shown in the construction Fig. 88 to Fig. 90. At a possible covering of the visible surface 286, the protective flaps are designed so that that they drained aerodynamically with the surface of the spacecraft they are closed. Fresh breathable air is always in the cell core 280.

The telescope 285 can be designed as a reflector or as a refractor be, it can also consist of a combination of reflector and refractor ( David Bergamini book "Das Weltall" TIME-LIFE International 'Nederland' N.V. vintage 1970, pages 36 to 98).

It's like that on planet earth the telescopes flicker through a Earth's atmosphere are disturbed (David Bergamini's book Das Weltall "TIME-LIFE International 'Nederl9nd' N.V. Year 1970, page 184).

An interior structure with a radio telescope can also be designed, an internal structure with a radio telescope is not shown. On the planet Earth telescopes are affected by interference and noise. the Methods of radio astronomy have already revealed much about the optical telescopes remains hidden or has remained hidden. About the many hidden sources of energy To determine in space began to use new types of telescopes over the Sending the earth's atmosphere out into space. About the many sky lights To determine and map one, one undoubtedly becomes a manned observatory outside the earth's atmosphere need (David Bergamini book HDas Weltall "TIME-LIFE International 'Nederland' N.V.

Year 1970, pages 39 and 40).

The chair 285a includes an astronomer shown in phantom is. Information is collected in the two memory banks 287. The calculation bank 288 can contain an electronic computer or computer for evaluating recorded data and can be useful for astrometry.

A cabin with two berths 299 can be accessed through a door 292 hermetically sealed. The multipurpose cabinet 291, a work table 289 and two armchairs 290 allow the astronauts or astronomers to stay longer in interplanetary space or on the Mbnd. In the cross section of Fig.75 is the telescope 285 shown offset by 90 degrees. The cross section Fig. 74 shows with a representation of the visible surfaces the connection with the intermediate floor 281.

The two spaces 294 located next to the cell core 280 can Include a possible landing gear, which in the spacecraft Fig.36 to Fig.38 in retracted or extended state is shown. The two rooms 294 can Fuel tanks contain as well as equipment that is required to function to enable the spacecraft to function properly. The engine room 294a can the Include system for pivoting the rear rocket engines.

A spacecraft designed with the interior structure shown is, can be used as a moving or location-changing observatory in the interplanetary Space or on the moon. The telescope 285 can operate without flickering the Earth's atmosphere or

without atmospheric disturbances such as smoke and fog in the interplanetary In space or on the moon.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 78 and FIG. 79 show cross sections, FIG. 80 shows a longitudinal section, and FIG. 81 shows a plan view of an interior structure for spacecraft like them in the constructions Fig. 30 to Fig. 65 are shown structurally.

This internal structure is for safeguarding interests in the interplanetary Space and on the bdond laid out with combat missiles for possible combat can serve an opponent. With the inner structure shown, the spacecraft Fig. 30 to Fig. 65 can be designed according to your choice. The 307 scale enables one Dimensioning that can of course vary.

The intermediate floor is located in the cell core 296 for the spacecraft 297. On the intermediate floor 297 there are three bulges for the landing legs and the pilot chair 298 for two pilots. Because of the visible surfaces, the two have Pilots each get an optimal field of vision from the pilot's seat 298.

The pilot seats 298, the elevator 299, the airlock 300, the emergency exit 301, as well as a system for used breathing air, air pressure, etc., are analogously the same facilities, as detailed in the construction Fig. 66 to Fig. 69 represented and described. The emergency exit 301 can also be used as an entrance or

Serving output on planet earth, sanitary facilities are not shown. Fresh air is always in the cell core 296.

There are ten combat missiles 302 and ten combat missiles in the internal structure 303

The cross-section of FIG. 79 shows five combat missiles 302 and a cover 305 and a partition wall 304 in the extended state. Take the 303 combat missiles in the extended state the same position as the combat missiles 302, which are shown in the cross-section of Fig. 79 in the extended state.

The longitudinal section Fig. 80 shows the position of the combat missiles 302 and the combat missile 303 in the extended or ready-to-fire state, as well as two covers 305 and two partitions 304 in the extended state.

Initially, five combat missiles 302 can be deployed and disengaged will. With an appropriately designed lifting mechanism, it is possible to do ten Combat missiles 302 extended or

can be shot down. After the combat missiles 302 shut down were, the brackets for the combat missiles 302 are retracted and thereby likewise a cover 305 and a partition wall 304 are brought into their starting position or retracted again.

After the combat missiles 302 have been fired, five combat missiles can initially be released 303 can be extended and shot down. With an appropriately designed lifting mechanism it is possible that ten combat missiles 303 can be deployed or shot down ..

After the combat missiles are shot down, the mounts retracted again for the combat missiles 303 and thus also a cover 305 and a partition 304 brought into their starting position or retracted again.

The cross-section in Fig. 78 shows a representation of the visible surfaces the connection with the intermediate floor 297.

The two spaces 306 located next to the cell core 296 can Include a possible landing gear, which in the spacecraft Fig.36 to Fig.38 in retracted or extended state is shown. The two rooms 306 can Fuel tanks contain as well as systems that are required to ensure proper functioning of the spacecraft. The engine room 306a can pivot the system the rear rocket engines.

A spacecraft with the interior structure shown is, can be used to protect plants and to maintain peace or tam peace Counteracting hostile forces, ia interplanetary space and on the moon be used as a tactical space interceptor.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 82 shows a cross section, FIG. 83 a longitudinal one cut, and FIG. 84 a plan view of an interior structure for spacecraft such as this in the constructions Fig. 30 to Fig. 65 are shown structurally.

This internal structure is for safeguarding interests in the interplanetary Space and on the moon with combat missiles designed for possible combat can serve an opponent. With the interior structure shown, the spacecraft Fig. 30 to Fig. 6 can be designed according to your choice. The 318 scale enables one Dimensioning that can of course vary.

The swish floor is located in the cell core 308 for the spacecraft 309. Three cutouts for the combat missiles 315 are made on the intermediate floor 309 and the pilot seats 310 for two pilots. Because of the visible surfaces, the two have Pilots each get an optimal field of vision from the pilot's seat 310.

The pilot seats 310, the elevator 311a, the airlock 311, the Emergency exit 312, as well as a system for used breathing air, air pressure, etc., are analogous the same devices as detailed in the construction Fig. 66 to Fig. 69 represented and described. The emergency exit 312 can also be used as an entrance or

Serving output on planet earth, sanitary facilities are not shown. Fresh breath air is always in the cell core 308.

In order to achieve further usable space for the interior construction see the possibility of the landing legs, which serve a possible landing on the moon, to be attached outside of the cell core 308. It can be a spacecraft with four Landing legs 313 are laid out, which are located in two container-like bulges 314 are located.

The four landing legs 913 are shown in the floor plan in FIG. 84 and longitudinal section FIG. 83 shown in the retracted state, but in the cross-section of FIG. 82 and longitudinal section Fig.83 shown in the extended state. The landing legs 313 are analogously similar to the landing legs in the spacecraft Figw5O bis Fig. 65 are shown. The construction principle of the landing legs is in clay structures Fig. 117 to Fig. 125 treated.

There are nine combat missiles 31 in the internal structure. The cross-section FIG. 82 and the longitudinal section in FIG. 83 show three Kimpfrockets 315 in the extended position or ready-to-launch state. With an appropriately designed With the lifting mechanism it is possible that nine combat missiles 315 are deployed or fired can be.

After the Kanipfraketen 315 have been shot down, the mounts retracted for the combat missiles and thereby the partitions 316 back into their starting position brought or retracted. The flaps 316a serve to close the opening for the combat missiles 315.

In terms of space, there is also the opportunity for the displayed Copper missiles to use research missiles, analogously similar American projectiles of the type "Arcas", "Nike-Smoke", "Xike-Cajun" or 2'Black-Brant III "(Arthur C. Clarke Book "Man and Space TIME-LIFE International 'Nederland' N.V. 1970, Pages 42 to 43) etc., which are deployed or deployed in interplanetary space come and equip them with measuring instruments, take on various research tasks, and can be sent to the neighboring planets.

The two spaces 317 located next to the cell core 308 can Contain fuel tanks as well as systems that are required to ensure proper functioning of the spacecraft.

The engine room 317a can be the system for pivoting the rear Record rocket engines.

The interior structure shown offers accommodation for a possible landing gear outside of the cell core 308, on the underside of the cell body from the particular spacecraft chosen. The accommodation or the installation of a chassis and results from the design features of the various Spacecraft Fig. 30 to Fig. 65, which are designed with the internal structure shown can be.

A spacecraft designed with the interior structure shown is, can be used to protect plants and to maintain peace or to keep peace To counteract hostile forces, in interplanetary space and on the Moon can be used as a tactical space interceptor.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 85 shows a cross section, FIG. 86 a longitudinal section, and FIG. 87 shows a floor plan of an interior structure for spacecraft, as shown in the constructions Fig. 30 to Fig. 65 in terms of construction.

Dieter's interior is designed for the transport of large containers or

Container designed. 1Container 'is the general one in freight transport Term for large container '. With the interior structure shown, the spacecraft Fig. 30 to Fig. 65 can be designed according to your choice. The scale 329 enables one Dimensioning that can of course vary.

The intermediate floor is located in the cell core 319 for the spacecraft 320. The pilot seats 321 for two pilots are located on the intermediate floor 320. The two pilots each have 321 out of the pilot's chair through the visuals an optimal field of vision.

The pilot seats 321, the elevator 322, the airlock 323, the emergency exit 324, as well as a system for used breathing air, air pressure, etc., are analogously the same facilities as detailed in the construction Fig. 66 to Fig. 69 represented and described. The emergency exit 324 can also be used as an entrance or

Serving output on planet earth, sanitary facilities are not shown. Fresh air is always in the cell core 319.

In order to achieve further usable space for the interior construction the possibility to use the landing legs, which are used for a possible landing on the moon, to be attached outside of the cell core 319. It can be a spacecraft with four Landing legs 325 are laid out, which are located in two container-like bulges 326 are located.

The four landing legs 325 are retracted in the floor plan in FIG State shown, however in the cross section Fig. 85 and longitudinal section Fig. 86 in the extended State shown. The landing legs 325 are analogously similar to the landing legs which are shown in the spacecraft Fig. 30 to Fig. 65. The construction principle the landing legs is dealt with in the constructions Fig. 117 to Fig. 125.

The interior structure shown offers accommodation for a possible landing gear outside of the cell core 319, on the underside of the cell body from the respective chosen spacecraft. The accommodation or the installation recruited from a textbook and results from the design features the various spacecraft Fig. 30 to Fig. 65, with the internal structure shown can be interpreted.

The internal structure is designed to accommodate the container 330 or the internal structure includes the container 330.

The container 330 can e.g. on the moon after a landing of the Spacecraft, deposited on the moon with an appropriately designed device will. At a later point in time, the spacecraft can be above the container 390 land and pick up the container 33C again with said device. By doing In longitudinal section FIG. 86, the container 330 is shown in the detached state. By the container 330 can reach or enter a hermetically sealable door 323a will.

X offers the possibility of depositing a container 330 and then mine to pick up another container 330, etc.

The construction principle and the various possible uses of the container 330 are shown in the construction Fig.88 to Fig.9O and described.

The Raui 327 can accommodate the device required to set down the container 330 or to pick it up again. The wall 327a is aerodynamic conditional. If the spacecraft flies in the earth's atmosphere without a container 330, the occurring air masses can slide along the wall 327a.

The two spaces 328 located next to the cell core 319 can Contain fuel tanks as well as systems that are required to ensure proper functioning of the spacecraft.

The engine room 328a can be the system for pivoting the rear Record rocket engines.

A spacecraft designed with the interior structure shown can be used as a container transporter. The container transporter can containers 330, which are designed as a space station section, for construction from space stations or moon stations to interplanetary space or to the moon promote.

He can exchange container 330 as well as empty or defective containers 3.0 promote.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 88 shows a side view, FIG. 89 a cross-section 1 and FIG. 90 is a plan view of the container 330 used for the spacecraft interior structure Fig. 85 to Fig. 87 is designed.

The illustrated construction of the container 930 represents the basic structure but none of possible different interior arrangements. The 396 scale allows a dimensioning that can of course differ.

There are two hermetically sealable ones on the container 330 Doors 331. With a transparent one that meets the various requirements The visible surface 332 is natural or light due to the environment. The two umbrella-like plates 333 serve for the transparent visible surface 332 as Protection against jet engine radiation when the respective spacecraft takes off, after a container 330 was deposited e.g. on the moon. The umbrella-like plates 333 can be extended or folded over with an appropriate mechanism. the Inner sides of the umbrella-like plates 333 can be formed with solar cells, which are brought into position, store solar batteries and thereby self-sufficiency of the container 330 can serve with electrical energy. The supply of electrical Energy is similar to the seismometer installed forever on the moon, whose large umbrella-like solar batteries supply the device with electrical energy. The seismometer was carried out on the first moon landing, as part of the American Space company "Apollo 11", set up (Arthur C. Clarke book man and Space "TIME-LIFE International 'Nederland' N.V. Year 1970, pages 123 and 140).

When the container 330 is removed from a spacecraft or

Container transporters to be included will be the umbrella-like Plates 333 folded or placed over the visible surface 332.

The cross section Fig. 89 and the top view Fig. 90 show the container 330 with extended or folded umbrella-like plates 333. The top view Fig. 90 shows the umbrella-like plates 333 with a representation of the possible solar cells on the inside. The intermediate space 33 is provided by the intermediate floor 334. Energy stores can be located in the intermediate space 335; it can be used for insulation lit serve the lunar soil.

The containers 330 are used according to the respective purpose equipped with an interior. They are made on planet earth and can each be flown into interplanetary space with a container transporter, or be set down on the moon. Possible interior fittings are not shown.

The container 330 can be used as a living container to train who can be set down individually on the moon, and astronauts or People who perform a function or activity on the moon as accommodation to serve. A possible arrangement or set-up of container 330, which is used as a residential container 91 shows the top view. The interior for a container 330, which is designed as a living container, consists mainly of one Air lock for pressure equalization, a system for air renewal, air pressure, etc., its own energy supply, a place to eat, a place to sleep, as well as from a sanitary facility. Individually set up residential containers can be opened at any time be moved to another location.

There is also the possibility of the container 330 as a space station section or lunar station section to train. In this way, several containers 330, which can be used as Space station section or

Moon station section are formed, i-teinznder connected a Rauistation or moon station result. A possible space station or moon station is shown in the plan view Fig.92 and consists of six containers 330, each the container 330 is designed for a specific task area. E.g. a Conta in er 330 contain the energy supply or heat supply.

Bin 330 contains an air renewal system, air pressure etc. A container 330 contains an air lock for manufacture for pressure equalization or a reserve air lock, as well as oxygen supplies e.g. in bottles of the Reserve and a radio station or radar station for location-related matters and radio traffic. A container 330 contains dining facilities and sanitary facilities.

Two containers 330 contain sleeping accommodations and living space for Astronauts or people who perform a function or activity. Fresh air to breathe is always in each container 330.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

Pig. 93 shows a cross section, FIG. 94 a longitudinal section, and FIG. 95 shows a floor plan of an internal structure for spacecraft such as this in the constructions Fig. 30 to Fig. 65 are shown structurally.

This interior structure is designed for the transport of containers.

With the interior structure shown, the spacecraft Fig. 30 to Fig. 65 can be designed depending on your choice. The scale 354 enables dimensioning which of course can differ.

The intermediate floor is located in the cell core 337 for the spacecraft 338. The pilot's seats 339 for two pilots are located on the intermediate floor 338. Through the visible surfaces, the two pilots each have the pilot's seat 339 an optimal field of vision.

The pilot seats 339, the elevator 340, the airlock 341, the emergency exit 342, as well as a system for used breathing air, air pressure, etc. are analogously the same facilities as detailed in the construction Fig. 66 to Fig. 69 represented and described. The emergency exit 342 can also be used as an entrance or

Serving output on planet earth, sanitary facilities are not shown. Fresh breath air is always in the cell core 337.

In order to achieve further usable space for the interior construction the possibility to use the landing legs, which are used for a possible landing on the moon, to be attached outside of the cell core 337. It can be a spacecraft with four Landing legs 344 are laid out, which are in two container-like bulges 345 are located.

The four landing legs 344 are retracted in the floor plan of FIG State shown, however in cross section Fig. 93 and longitudinal section Fig. 94 in the extended State shown. The landing legs 344 are analogously similar to the landing legs which are shown in the spacecraft Fig. 30 to Fig. 65. The construction principle the landing legs is dealt with in the constructions Fig. 117 to Fig. 125.

The interior structure shown offers accommodation for a possible landing gear outside of the cell core 337, on the underside of the cell body of the chosen one Spacecraft. The shelter or the installation of a chassis is recruited and results from the design features of the various spacecraft Fig. 30 to Fig. 65, which have the internal structure shown can be placed.

The internal structure is designed to accommodate the container 355 or the internal structure contains the container 355.

For example, the container 355 can be in interplanetary space from the spacecraft be deposited or with an appropriately designed device in the interplanetary Space to be placed. It is also possible to set the container 355 down on the moon or to resume on the moon and in interplanetary space. In the cross section 93 shows the container 355 in the detached state. Through a hermetic lockable door 343, the container 355 can be reached or entered. It there is the possibility of depositing a container 355 and then another To pick up container 355, etc.

The construction principle and the various possible uses for the segment-like container 355 are in the construction Fig. 98 to Fig. 99 shown and described.

The bottom flaps 353, which are primarily aerodynamically determined, are opened when a container 355 or similar container is set down or picked up they will be closed for the flight. The cross section of Fig. 93 shows two Bottom flaps 353 in the open state and in the closed state.

A multi-purpose cabin contains a bench seat 346 and two beds 347. In the air lock 348, a pressure equalization can be used to exit or enter of the spacecraft in interplanetary space or on the moon.

A ladder 350 can pass through the opening through the ladder shaft 949 351 the spacecraft can be left or entered.

The opening 351 can be hermetically closed with a flap.

the. In the multi-purpose cabin, for example, people can fly with Assembly of the container to a space station or lunar station, ii interplanetary Space or on the moon.

People can be promoted in exchange. In the multi-purpose cubicle I also constantly have fresh air to breathe. The space under the multipurpose cubicle can pick up the device required to set the container 355 down or to resume. Due to its design features containers of various shapes can be transported in the interior structure shown such as cuboid, spherical, cylindrical, etc.

For example, containers can be used as oxygen tanks, fuel tanks, water tanks etc. are trained.

The two spaces 352 located next to the cell core 337 can Contain fuel tanks as well as systems that are required to ensure proper functioning of the spacecraft.

The engine room 352a can be the system for pivoting the rear Record rocket engines.

A spacecraft designed with the interior structure shown can be used as a container transporter. The container transporter can container 355, which are designed as a space station section, for construction of space stations or

Move lunar stations to interplanetary space or to the moon. It is also possible to transport similar containers.

He can transport container 355, or similar containers, in exchange, as well as transporting empty or defective containers.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 96 shows a top view, FIG. 97 a side view, and FIG. 98 shows a cross section of a space station.

The scale 358 enables the dimensions shown to be dimensioned Space station, which of course can vary.

The space station shown consists of segment-like containers 355 and segment-like containers 356. The containers 355 and the containers 356 are each designed for the spacecraft interior structure Fig. 93 to Fig. 95.

FIG. 99 shows a top view of the container 355 and of the Container 356, as it is in the spacecraft interior structure Kon construction Fig.93 up to Fig. 95 in terms of space. The dash-dotted line 357 represents the room which contains the respective container 355 or container 356. The container 356 is shown in mirror image for a better overview. The Fig. 98 shows a Cross-section of the container 355 and of the container 356, they form the cross-section the space station shown.

Containers 355 form the outer ring of the space station. A container 355 includes two hermetically sealable doors 355a.

Containers 356 form the inner ring of the space station. A container 356 includes two hermetically sealable doors 356a.

A container 356 is similar in construction, but has smaller dimensions as a container 355.

The illustrated construction of the container 355 and of the container 356 represent the basic structure, but none of the possible different interior fittings. Also possible windows or visible surfaces and the like are not shown, they result from the design of the various interior fittings for the Container.

The container 355 and the container 356 are mainly used for Creation of space stations in interplanetary space. According to the task and size of one Each container 355 and container 356 become a space station as a part of the building educated. The container 355 and container 356 are each for a particular Purpose made on planet earth. With a spacecraft or Container transporters they are flown or transported into the interplanetary space, where they are connected to each other and can result in a space station.

The assembly of the space station shown takes place in the interplanetary Space, the assembly consists mainly of the assembly of the various Containers with each other, which achieves a minimum of assembly in interplanetary space will. The containers are dimensioned so that they are relatively easy to assemble are to be moved or placed in interplanetary space. laugh at the interpretation of the The space station shown, the container 355 and container 356 each as RallmRtation parts are manufactured e.g. as: Power plant for energy supply for building gtation, air lock with system for producing pressure equalization, Sanitary facilities, reprocessing system for breathing air, emergency system system for energy supply, emergency system for the preparation of breathing air, radio station for message transmission, measuring station for determining one's own location, locating station for detecting approaching objects, etc., connecting piece with side openings, Connection piece with floor openings or ceiling openings.

Accommodation or sleeping accommodation for the crew members, Lounge or dining room for the crew members, leisure room or entertainment room for the crew, living quarters or sleeping accommodation for crews of stationed persons Spacecraft, accommodation for visitors to the space station, medicine supply station, Catering depot.

Oxygen tanks for the space station, oxygen tanks for supply of stationed spacecraft, fuel tanks for supplying stationed ones Spacecraft, laboratory for various purposes or investigations, observatory with optical telescope, observatory with radio telescope, hangar with one-man aircraft of the construction Fig. 132 to Fig. 134, spare parts store, replenishment depot for stationed people Spacecraft, operations center or control center for the space station, office for administrative tasks or correspondence.

Of course, several containers of the same design or interior can be used used and assembled. For example, the outer ring of the space station, which consists of containers 355, the various technical systems consist of the are required to enable the space station to function. It can e.g.

the inner ring of the space station, which consists of containers 356, focus on residential accommodation or the facilities that the Crew of the space station are useful.

In the space station there is always fresh or processed Breathing air. For processing used air, air pressure, etc.

serves a similar system to that implemented in the American Space company "KercuryH was dedicated.

One advantage is that each container is hermetically sealed by two doors can be. So in case of danger, e.g. by a meteor or a collision with a spacecraft, an outflow of breathable air from the space station on a Be reduced to a minimum.

Designed according to task and size, other cross-sectional shapes are also possible for a space station with containers 355 and containers 356 possible, Fig. 100 to Fig. 102 show e.g. other possible cross-sectional shapes. Figure 103 shows e.g. a partial view of a possible top view of the space station.

Another advantage is that it includes the space station to can be expanded at a later point in time. A possible The container 355 and container shown in dash-dotted lines show an extension, for example 356 in the cross section of FIG. 100. The space station can be used at any time without interrupting operations can be expanded without changing the existing system. The one shown Space station can be designed with larger or smaller dimensions in its diameter accordingly would be the dimensioning of the container 355 and container 356, it can also be created e.g. on the moon.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 104 shows a top view, FIG. 105 a side view, and FIG. 106 shows a cross section of a space station.

The scale 362 enables the dimensions shown to be dimensioned Space station, which of course can vary.

The space station shown consists of segment-like containers 359 and segment-like containers 560. The containers 359 and the containers 360 are respectively for the spacecraft internal structure construction Fig. 93 to Fig. 95 designed.

107 shows a top view of the container 359 'and of the Container 360, as it is in the spacecraft inner structure construction Fig. 93 up to Fig. 95 in terms of space. The dash-dotted line 361 represents the room which contains the respective container 359 or container 960. The container 360 is shown in mirror image for a better overview. The Fig.106 shows a Cross-section of the container 359 and of the container 360, they form the cross-section the depicted rium station.

Containers 359 form the outer ring of the space station. A container 359 includes two hermetically sealable doors 359a.

Containers 360 form the inner ring of the space station. A container 360 includes two hermetically sealable doors 360a.

A container 360 is similar in construction, but has smaller dimensions as a container 359.

The illustrated construction of the container 359 and of the container 360 represent the basic structure, but none of the possible different Interiors. Also possible windows or visible surfaces and the like are not shown, they result from the layout of the various interior fittings for the container.

The container 359 and the container 360 are mainly used for Creation of space stations in interplanetary space. According to the task and size of one Each container 359 becomes a space station and each container 360 becomes a space station section educated. The container 359 and container 360 are each for a particular Purpose made on planet earth. With a spacecraft or Container transporters they are flown or transported into the interplanetary space, where they are connected to each other and can result in a space station.

The assembly of the space station shown takes place in the interplanetary Space, the assembly consists mainly of the assembly of the various Containers with each other, which achieves a minimum of assembly in the interplanetary order will. The containers are dimensioned so that they are relatively easy to assemble are to be moved or placed in interplanetary space. According to the interpretation of The space station shown can be the container 959 and container 360 each as Space station sections can be manufactured, e.g. in the space station construction Fig. 96 to Fig. 98 was listed or described in more detail.

Of course, several containers of the same design or interior can be used used and assembled. For example, the outer ring of the space station, which consists of containers 359, the various technical systems consist of the are required to enable the space station to function. It can e.g.

the inner ring of the space station, which consists of containers 960, focus on residential accommodation or the facilities that the Crew of the space station are useful.

In the space station there is always fresh or processed Breathing air. For processing used air, air pressure usi.

serves a similar system to that implemented in the American Space company "Mercury" was applied.

One advantage is that each container is hermetically sealed by two doors can be. In case of danger, e.g. by a meter or a collision with a spacecraft, an outflow the air we breathe from the space station be reduced to a minimum.

Designed according to task and size, other cross-sectional shapes are also possible for a space station with containers 359 and containers 360 possible, Fig. 108 to Fig. 110 show e.g. other possible cross-sectional shapes. Fig. 111 shows e.g. a partial view of a possible top view of the space station.

Another advantage is that the space station is also included can be expanded at a later point in time. A possible The container 359 and container shown in dash-dotted lines show an extension, for example 360 in the cross section of Fig. 108. The space station can be used at any time without interrupting operations can be expanded without changing the existing system.

The space station shown can be larger or larger in diameter be designed with smaller dimensions, the dimensioning would be accordingly the container 959 and container 960 can also be changed e.g. on the moon to be created.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 112 is a plan view, FIG. 113 is a side view. and FIG. 114 a cross section of a space station.

The scale 365 enables the depicted to be dimensioned Space station, which of course can vary.

The space station shown consists of segment-like containers 363. The container 365 is for the spacecraft interior structure 93 to 95 are laid out.

116 shows a plan view of the container 363 as it is Fig. 93 to Fig. 95 in terms of space in the spacecraft interior structure construction. The dash-dotted line 364 represents the space that the respective container 363 includes. Fig. 115 shows a side view of the container 363. The Fig. 114 shows a cross section of containers 363, they form the cross section of the illustrated space station.

A container 363 contains two hermetically sealable doors 36Da. The illustrated construction of the container 363 represents the basic construction but none of possible different interior arrangements. Also possible Windows or visible surfaces and the like are not shown, they result from the design of the various interior fittings for the Container.

The containers 363 are mainly used to create space stations in interplanetary space. Each container becomes a container according to the task and size of a space station 363 designed as a space station section. The containers 363 are each for manufactured for a specific purpose on planet earth. With a room missiles or container transporters are flown into interplanetary space or transported, where they are connected to each other and a space station can result.

The assembly of the space station shown takes place in the interplanetary Space, the assembly consists mainly of the assembly of the various Containers with each other, which achieves a minimum of assembly in interplanetary space will. The containers are dimensioned so that they are relatively easy to assemble are to be moved or placed in interplanetary space. According to the interpretation of The space station shown can each have the container 363 as a space station section are manufactured as e.g. listed in the space station construction Fig. 96 to Fig. 98 or was described in more detail.

Of course, several containers of the same design or interior can be used used and assembled. For example, the upper ring of the space station can focus the living quarters or the facilities that the crew of the space station are useful. For example, the lower ring of the space station can be made up of the various Technical investors exist that are necessary for the functioning of the To enable space station.

In the space station there is always fresh or processed Breathing air. A similar one is used for processing used air, air pressure, etc. System used in the American space company "Mercury" became.

One advantage is that each container is hermetically sealed by two doors can be. So can in case of danger, e.g. by a leteor or a collision with a rocket, an outflow of breathable air from the space station on Minimum h. Be deducted.

Another advantage is that the space station is also included can be expanded at a later point in time can. A possible extension, for example, is shown by the containers shown in dash-dotted lines 363 in the Q @ section Fig. 114 or in the side view Fig. 113. The space station can be expanded at any time without interrupting operations without changing the existing plant.

The space station shown can be larger or larger in diameter be designed with smaller dimensions, correspondingly the dimensioning would be from the container 363, it can also t.B. to be created on the moon.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 117 shows a side view, FIG. 118 a front view, and FIG. 119 a plan view of a landing leg. It is representative for the landing legs of the spacecraft Fig. 30 to Fig. 65 or Fig. 12 to Fig. 29.

The illustrated views Fig. 117 to Fig. 119 correspond to the position of the landing leg in the retracted state, the longitudinal section Fig. 120 shows the position from the landing leg in the retracted state. The dash-dotted representation of the landing leg corresponds to the position in the extended state.

The spacecraft shown mainly include dr.i Landing legs that are required, for example, for a moon landing. Will be the landing leg e.g. extended for a landing, the landing plate 368 describes the path 370a.

The landing plate 368 on which the spacecraft stands is equipped with a Holm 366 connected. The spar 366 is located in a twirungsrohr 367, where he is elastically mounted. In this way it is possible to absorb impacts that occur during landings can arise.

Vibrations or shocks can, for example, be carried out with an appropriately designed Spring 370 or the like are caught, the spring 370 is compressed accordingly. So that the spar 366 and thereby the landing plate 368 not its position, based on the landing leg, can change, a groove 366a is made in the spar 366 the associated wedge 369 is located. The wedge 369 is fixed in the guide tube 367. fitted and prevents displacement of the spar 366. An enlargement or the detail wZw shows Fig. 121. The landing leg can, for example, be hydraulic or be moved similarly.

FIG. 123 shows a front view, FIG. 124 a side view, and FIG. 125 is a plan view of a landing leg suspension. The cross section Fig. 122 shows the position of the landing leg suspension shown, an enlargement or the detail WV "shows the front view Fig. 123. The illustration is representative for all landing leg suspensions of the spacecraft Fig. 30 to Fig. 65 or Fig. 12 to Fig. 29.

In a cross brace 371, below the intermediate floor in the a housing 372 is located in the respective interior structure of the spacecraft.

In the housing 372 is the guide tube 367 of the one shown Landing leg movably mounted. In the guide tube 367 there is an elongated hole 367a. The elongated hole 367a ensures that the guide tube and thus the Landing leg, directly forms a pressure against housing 372. Through a bolt 373 the guide tube 367 with its plate-like shape, and thus the landing leg, guided or held in the housing 372.

The landing leg is movably mounted in the landing leg suspension.

The landing leg suspension can cause loads during landings such as absorbing vibrations and shocks.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

Ea shows FIG. 132 a front view, FIG. 133 a side view, and FIG. 134 is a plan view of a one-man aircraft.

The one-man aircraft is for use in interplanetary space as well as designed for activities e.g. on the moon. The 392 scale makes it possible a dimensioning that can of course differ.

The one-man aircraft is primarily used as a rescue device.

designed, it can also be used for other tasks. It can bswiYonetationen in the spacecraft and space stations shown be carried. In the event of danger, a spacecraft or a space station or Yondstation can be left with the one-man aircraft. The one-man aircraft can also be used, for example, as a ferry between a spacecraft and a space station can be used. With the one-man aircraft, companies can also e.g. run on the moon e.g. the descent or ascent in a lunar crater.

Three pivotable rocket engines 380 are attached to a housing 377. Two rocket engines 380 are each located on a bracket 978 in which a shaft 379 is supported. The shaft 379 is fixed to the rocket engine 380 in each case tied together.

An electric motor 381 moves one shaft 379 at a time a rocket engine 380 can be pivoted. A rocket engine 380 is located located between two consoles 378a and can be pivoted by an electric motor 381 will.

A battery 382 contains the power for three electric motors 381.

Three fuel tanks 383 hold the fuel for three rocket engines 380

The one-man aircraft shown is flown or operated when an astronaut or a person in a space suit lying down in a stretched position is located on the intermediate floor 384. The dash-dotted line 387 shows the outline by an astronaut or

by a person in a spacesuit.

The arms are put through two retaining brackets 388 and the hands can two handles 386 enclose. With the bracket 388, the arms have enough Freedom of movement so that it is possible to operate the switchgear 385.

The legs are put through a bracket 389. At the foot of the can various recesses can be made to give the feet a further hold. Depending on the size of the astronauts or the person in the spacesuit, different Au recesses are attached, corresponding recesses are not shown.

The two retaining brackets 388 and the retaining bracket 389 prevent that the astronaut or a person in a spacesuit from the intermediate floor 384, e.g. interplanetary space is being drifted away.

Two transparent visible surfaces 391 provide a optimal field of vision given.

On two handle-like holders 390 and two handle-like holders 39oz, the one-man aircraft can e.g. in the spacecraft shown and shown Space stations are attached. With the handle-like holders 390, 3901 the one-man aircraft can be moved or is it possible to use the one-man aircraft to be brought into the correct position before take-off or take-off.

Another embodiment of the invention is shown in the drawing and is described in more detail below.

FIG. 135 shows a floor plan and FIG. 136 shows a side view from a rocket engine mount as in the spacecraft shown can be used. With the rocket engine suspension shown, a Rocket engine can be pivoted optimally. The rocket engine locking is on supported two sides by the rocket engine.

The pivotable rocket engine 393 is fixed with a shaft 400 tied together. The shaft 400 rests in the bearings 399 in the respective spacecraft are appropriate.

A pipe 397 and a pipe run through the shaft 400 398. The pipe 397 contains liquid fuel carried by the turbo pump 395 is conveyed into the combustion chamber 394.

The conduit 398 contains an oxidant which is passed through the Turbopump 396 is conveyed into the combustion chamber 394. In the focal point D94 the liquid fuel and the oxidizing agent are brought together, whereby the so-called thrust is generated.

For example, a liquid fuel is a Kerosene-like hydrocarbon, which as an oxidizing agent is liquid oxygen needs (Arthur C. Clarke book Man and Space "TIME-LIFE International 'Nederland' N.V. Year 1970, page 45).

The rocket engine 393 can be moved or pivoted e.g.

by a so-called angle drive. A nechanical movably attached Rack 401 moves a gear 402 that is fixedly connected to shaft 400. Since the shaft 400 is also firmly connected to the rocket engine 393, can rocket engine 393 is thus pivoted.

FIG. 137 shows a floor plan and FIG. 138 shows a side view from a double rocket engine mount or

a rocket engine mount for two rocket engines like her 30 to 65 can be used in the spacecraft shown. With The rocket engine suspension shown can have two rocket engines at the same time be swiveled optimally. The rocket engine mount is on two sides of each rocket engine stored.

The slewable rocket engine 403 and the slewable rocket engine 404 are firmly connected to a shaft 407. The shaft 407 rests in the bearings 410,411, which are mounted in the respective spacecraft.

Through the shaft 407 leads from the rocket engine 403 and the rocket engine 404 in each case a pipe 405 and a pipe 406. One pipe in each case 405 contains liquid fuel that is fed through the turbo pump 409 into the respective Combustion chamber 403a or combustion chamber 404a is conveyed.

Each pipeline 406 contains an oxidizing agent that through the turbo pump 408 into the respective combustion chamber 403a or

404a is promoted. In the combustion chamber 403a and combustion chamber 404a the liquid fuel and the oxidizing agent are brought together, whereby the thrust is generated.

The rocket engine 403 and the rocket engine 404 can be moved or are pivoted, for example, by two angled drives or the like. In the arrangement two angled drives provide optimum safety for the pivoting process, In the event of a defect, an angular drive or the rocket engines can still act sway.

A movable rack 413, which by a corresponding attachment can be moved, each moves a gear 412. The two Zehririder 412 are each firmly connected to the shaft 407.

Since now the shaft 407 also with the rocket engine 403 and the Rocket engine 404 is firmly connected, the pivoting process can thus take place.

FIG. 139 shows a floor plan and FIG. 140 shows a sectional view along the line 1-1 in Fig. 139 from a beacon engine mount as shown in the spacecraft shown can be used. With the rocket engine mount shown a rocket engine can be swiveled 180 degrees. The rocket engine mount is mounted on one side of the rocket engine.

The pivotable rocket engine 414 is fixed with a ring gear 420 tied together. The ring gear 420 is made up of two rollers 421 and one gear-like Roller 421 rotatably held in position. The ring gear 420 runs at Pivoting the rocket engines 414 on six rollers 422, which are in the respective Skin missiles are attached. The ring gear 420 can be driven from the drive side e.g. Be moved via a worm drive or the like.

In the arrangement of a worm drive, a shaft 423 is with the gear-like roller 421 and a worm wheel 426 are firmly connected. Of the Drive takes place via a drive shaft which is mounted in the bearing 428 and a Screw 427 moves.

The worm 427 moves a worm wheel 426, it thereby becomes the Shaft 423 lit the gear wheel-like roller 421 moves. Thus the teeth grip on the gear-like roller 421 in the ring gear 420 which in turn is the rocket engine 414 moves or

pivots.

The two shafts 423a are each firmly connected to a roller 421a. The two shafts 423a and one shaft 429 are supported in the bearings 429, respectively.

The wall 431 entapricht the spacecraft that is used in the constructions Fig. 30 to Fig. 65 are shown. The wall 431 serves as an example and is representative for the rocket missiles shown. The aerodynamic engine cowling 430 is fixedly connected to the rocket engine 414.

The conduit 418 contains liquid fuel that passes through the Turbopump 416 is conveyed into the combustion chamber 415. The pipe 419 includes an oxidizing agent which is conveyed into the combustion chamber 415 by the turbo pump 417 will. In the combustion chamber 415, the liquid fuel and the oxidizing agent merged, creating the thrust.

The two pipes 418,419 change their position when the rocket engine 414 is pivoted.

An enlargement or the detail "W" shows the plan view Fig. 141. The top view Fig. 142 shows the situation or a change in position of the two pipelines 418,419 after the rocket engine 414 has turned 180 degrees.

Due to a change in position, there is in the pipeline 418 a compensating piece 425 and a flexible intermediate piece 418a with the not movable pipeline 418b is connected. In the pipeline 419 is located an equal piece 425 and a flexible intermediate piece 419a the lit of the non-movable Pipeline 419b is connected.

A compensation piece 425 consists of the casing 425c, the sleeve piece 425a, as well as the sealing ring 425b.

The casing 425c is firmly connected to the straight line Pipe section 419 or pipe section 418. The sleeve section 425a is firmly connected in each case with the curved pipe section 419 or pipe section 418.

The jacket 425c surrounds the socket piece 425a so that the socket piece 425a is guided and can be easily moved or rotated in the casing 425c. The sealing ring 425b serves to seal off the respective pipeline 419 or pipeline 418

The top view Fig. 141 and the top view Fig. 142 show the respective Changes from flexible adapter 418a and flexible adapter 419a when rocket engine 414 is turned 180 degrees. It is natural other swivel angles possible.

The pipeline routing in the top view Fig. 141 and in the top view Fig. 142 is representative of the rocket engine mountings Fig. 135 to Fig. 140. The pipeline routing in the rocket engine mountings Fig.135 to Fig.138 is analogously similar to the pipeline routing in the plan view Fig. 141 and in the plan view Fig. 142.

L e r s e i t e

Claims (32)

Claims 0 Transport and defense system for manned spacecraft for space travel, designed to be a transport bridge for manned spacecraft to form in interplanetary space to create space stations in space or on the moon, with appropriately designed spacecraft serving for conservation of peace and to secure interests in interplanetary space or on the Moon, characterized in that a transport and defense system from spacecraft which can be derived from different basic versions, whereby it is given that a spacecraft is created for a specific task area can be achieved and thereby an optimal expediency is achieved, the spacecraft are shown structurally in Fig. 12 to Fig. 65, they are designed in such a way that that they can work using the natural laws of the earth's atmosphere, Due to their design features, the spacecraft have optimal Evasive systems that ensure the airworthiness of the spacecraft in space in the event of danger or can be preserved in the earth's atmosphere. 2. Transport and defense system according to claim 1, characterized in that that the self-propelled, spaceflight manned spacecraft the in the Fig.12 bia Fig.65 are shown constructionally, by a certain respectively. the arrangement of the pivotable rocket engines to one another, be able to perform all required flight maneuvers in interplanetary space as in one Scheme to illustrate the construction principle for possible flight maneuvers of the spacecraft is shown in interplanetary space in Figures 1 to 11. 3. Transport and defense system according to claim 1 or 2, characterized in that that in the interaction between tonotruktion and aerodynamic design resp. the shape of spacecraft can be created, as shown in FIGS Fig. 65 are shown structurally, which achieve an optimal degree of efficiency der 'the greatest possible degree of security for the respective astronauts or persons contains. 4. Transport and defense system according to claim 1, 2 or 3, characterized indicates that in the interaction between construction and aerodynamic Design or the shaping for spacecraft in terms of construction in FIGS. 30 to 65 are shown, an optimal use of the space volume in relation to the Dimensioning is given, such as. B in the different versions for one possible interior structure as shown in the constructions Fig. 66 to Fig. 87 and construction 93 to 95 is shown structurally. 5. transport and defense system according to claim 1, 2, 3 or 4, characterized characterized in that the containers in the constructions Fig. 88 to Fig. 90, Fig. 98 to Fig. 99, Fig. 106 to Fig. 107 and Fig. 115 to Fig. 116 in terms of construction are shown, in cooperation with the various embodiments of a possible interior structure for the spacecraft shown as a container transporter, as they are structurally in the constructions Fig. 85 to Fig. 87 and Fig. 93 to Fig. 95 are shown, a creation of different space stations in the interplanetary Space or e.g. on the moon is possible, such as space stations that can be produced with containers those in the tone instructions Fig. 91 to Fig. 92, Fig. 96 to Fig. 97, Fig. 104 to Fig. 105 and Fig. 112 to Fig. 113 are shown structurally. 6. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized that with a so-called landing leg that in the construction Fig.117 up to Fig. 121 is shown structurally, vibrations are absorbed or can be included that arise when a spacecraft after a flight on the ground or subsurface, and in cooperation with a so-called Landing leg suspension, which is structurally in the construction Fig. 122 to Fig. 125 is shown, the landing leg pivotable or retractable or extendable in the spacecraft shown is arranged. 7. Transport and defense system according to claim 1 or 2, characterized in that that with a so-called one-man aircraft, which in the construction Fig. 132 to Fig. 134 by design is shown becoming an astronaut or a person in a spacesuit can move, e.g. in interplanetary space, or all necessary flight maneuvers for changes of direction and the like can perform with the illustrated one-man aircraft. 8. transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that by the so-called rocket engine suspensions, which are in the Constructions Fig. 135 to Fig. 140 are shown structurally, the respective Rocket engines are movably or pivotably mounted, and in cooperation with a certain arrangement of the respective pipelines in the constructions Fig. 141 to Fig. 142 are shown structurally, the respective rocket engines the spacecraft shown with liquid propellant or oxidizing agent in every position or phase of the swiveling process, which can be up to 180 degrees, can be supplied. 9. Transport and defense system according to claim 8, characterized in that that the rocket engine (414) is firmly connected to the ring gear (420), so that the ring gear (420) by a gear-like roller (421) with a shaft (423) is firmly connected, and by two rollers (421a) each with a Shaft (423a) are connected, rotatably held in position and e.g. huber a worm drive or Worm (427) and worm wheel (426) or the like. Can be moved by inserting the teeth of the gear-like roller (421) into the ring gear (420) grip and the ring gear (420) is moved, whereby the rocket engine (414) can be swiveled. 10. Transport and defense system according to claim 8, characterized in that that a compensation piece (425) is arranged in each of the two pipes (418, 419) and through the position or arrangement of the pipelines (418, 419) i interact each with a compensating piece (425), a casing (425c) being a socket piece (425a) and a sealing ring (425b) is used for sealing, a change in position of the two pipes (418, 419) are compensated accordingly during the pivoting process can. 11. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that the spacecraft shown are called earth-space spacecraft can be divided into pivoting rocket engines and turbine jet engines are designed and in the constructions Fig.15 to Fig.20, Fig.24 to Fig.29 and Fig. 42 to Fig. 65 are shown structurally by their design features to be able to reach interplanetary space with its own drive, for example, and in each case have two different propulsion systems or a jet propulsion with turbine jet engines and a rocket engine with pivoting rocket engines, creating in the earth's atmosphere two drive systems can act and e.g. in the earth's atmosphere in the event of failure of the jet propulsion system, the flight with the rocket propulsion system can be continued can or vice versa. 12. Transport and defense system according to claim 11, characterized in that that an earth-space spacecraft made a conventional aircraft landing with turbine jet engines ii can interact with elevator and rudder, perform a VTOL landing or Vertical takeoff and landing can be performed using a conventional aircraft landing Can perform rocket engines in cooperation with elevator and rudder and can slide onto the runway at sufficient speed, similar to the aforementioned American aircraft "HI, 10" or "X-2". 13. Transport and defense system according to claim 1, 2, 9, 4 or 5, characterized characterized in that the spacecraft shown are called space-moon spacecraft can be divided, with several arranged swiveling rocket engines are designed and in the constructions Fig.12 to Fig.14, Fig.21 to Fig.23 and Fig. 30 to Fig. 41 are shown structurally by their design features conditionally able to move with their own propulsion, so that e.g. the spacecraft the in the constructions Fig. SO to Fig. 41 shown in terms of construction and each are designed with six pivoting rocket engines in the event of failure from one rocket engine or failure of two rocket engines when they are on the spacecraft are distributed, a landing or a take-off e.g. on the moon is still possible, so that an optimal safety for landings or take-offs e.g. is given on the moon. 14. Transport and defense system according to claim 13, characterized in that that a space-moon spacecraft is a conventional aircraft landing with rocket engines can perform a VTOL landing or rudder in conjunction with the elevator and rudder. Vertical takeoff and landing and glide back to planet Earth can with possible generation of counter-thrust, which can be caused by possible Frictional heat when re-entering the earth's atosphere, caused by pivoting rocket engines and has an electrical conductivity similar to that of the American aircraft mentioned "HL-10" or "M-2". 15. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that the spacecraft in the constructions Fig. 30 to Fig. 65 are shown by construction, are designed so that the underside of the spacecraft can act as a wing, whereby e.g. a sliding back of the respective spacecraft particularly favored and from interplanetary space back to planet earth is made possible and thus liquid fuel and oxidizing agents are saved can. 16. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that the spacecraft in the constructions Fig.12 to Fig.20 are shown structurally, have the same basic structure or cell structure have, the spacecraft, which in the constructions Fig.21 to Fig.29 structurally are shown, have the same basic structure or Have cell structure, as well as the spacecraft used in the constructions Fig. 30 to Fig. 65 are shown structurally, have the same basic structure or have a cell structure, which is of importance in terms of production technology if, for example, a so-called production line for the construction of the spacecraft shown will. 17. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that in a preferred embodiment of the spacecraft, the in the construction Fig.48 to Fig.50 is shown constructionally, with three pivotable turbine jet engines (172) arranged in a relative relationship to one another are appropriate and conditioned by the design features and Design of the spacecraft, all flight maneuvers necessary for guiding the spacecraft Required in the earth's atmosphere can be performed and by the three swiveling turbine jet engines (172) VTOL properties or vertical take-off and landing is possible. 18. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that in a preferred embodiment of the spacecraft, the in the construction Fig.33 to Fig.35 is shown constructionally by the arrangement of two pivotable wings (106) and due to the design features and design of the spacecraft that unites the spacecraft in the earth's atmosphere Can perform turns or can be brought into a bank position so the one Change of direction or Curve is possible. 19. Transport and defense system according to claim 1 or 2, characterized in that that with the design principle that is shown in Figures 1 to 11, with E.g. three swivel mounted rocket engines, which are correspondingly attached to one Spacecraft are arranged, all necessary flight maneuvers in the interplanetary Space can be carried out such as changes of direction, control and guidance of the spacecraft in interplanetary space, as well as vertical take-off and landing of the spacecraft e.g. on the moon. 20. Transport and defense system according to claim 1, 2, 9, 4 or 5, characterized characterized that with the spacecraft in the constructions Fig.30 to Fig. 65 are shown structurally, in each case space or space for internal structures is given, so that the internal structures can be created in the constructions Fig. 66 to Fig. 84 are shown structurally, and in the constructions Fig. 85 to Fig. 87 and Fig. 93 to Fig. 95 are each given space or space for containers is that in the constructions Fig. 88 to Fig. 90, Fig. 98 to Fig. 99, Fig. 106 to Fig. 107 and Fig. 115 to Fig. 116 are shown in terms of construction, so that the mentioned container can be designed as space station sections and what can be manufactured on planet earth, what manufacturing technology advantageous and then flew into interplanetary space where they can be placed and assembled with a minimum of assembly a space station, e.g. in interplanetary space, can be created at any time or can be expanded through later planned construction stages without interrupting operations or without changing the existing system, and in the event of danger, e.g. by a collision with a meteor or the like, an outflow the breathing air from the space station or moon station can be reduced to a minimum can because every container or each space station section is hermetically sealed by two doors can be, which means that there are many partition walls for the containers the space station or moon station is given, which is favorable in terms of stability or is advantageous and has an optimal effect in terms of safety, because the individual space station parts, can be hermetically sealed due to their design features, and, for example, when carrying out a planned expansion, such as the topping-up a space station e.g. on the moon or an extension of a space station in interplanetary space, the stability problems can be solved satisfactorily or by the design features of the container shown, e.g. the addition a space station e.g. on the moon or the expansion of a space station in the interplanetary Space is possible. 21. Transport and defense system according to claim 20, characterized in that that space stations are created in interplanetary space or e.g. on the moon can be used in the constructions Fig. 91 to Fig. 92, Fig. 96 to Fig. 97, Fig. 104 to Fig. 105 and Fig. 112 to Fig. 113 are shown structurally and in other forms of construction such as plan view Fig. 103 and plan view Fig. 111 in terms of construction are shown, and in each case optionally according to the function or area of responsibility of the respective Space station can be designed with possible cross-sectional shapes1 in the Cross-sections Fig. 100 to Fig. 102 and cross-sections Fig. 108 to Fig. 110 in terms of correlation are shown, so there are a variety of possible shapes for the ones shown Space stations is possible and the Raumatationen without interrupting the operation of the existing Plant can be expanded. 22. Transport and defense system according to claim 1, 2, 9, 4 or 5, characterized characterized in that in the spacecraft or earth-space spacecraft and space-moon spacecraft which are shown structurally in the constructions Fig. 30 to Fig. 65, an interior structure can be designed as a crew transporter like him in the construction Fig. 66 to Fig. 69 is shown constructionally, so that the respective spacecraft for passenger transport as a crew carrier can be interpreted. 23. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that in the spacecraft or earth-space spacecraft and space-moon spacecraft which are shown structurally in the constructions Fig. 30 to Fig. 65, an interior structure can be designed as a load transporter, as shown in the construction Fig.70 to Fig.73 is shown structurally, so that the respective spacecraft for the transport of loads or devices as load transporters can be interpreted. 24. Transport and defense system according to claim 1, 2, 9, 4 or 5, characterized characterized in that in the spacecraft or earth-space spacecraft and space-moon spacecraft which are shown structurally in the constructions Fig. 30 to Fig. 65, each formed an internal structure with an optical telescope or a radio telescope can be as it is shown structurally in the construction Fig. 74 to Fig. 77 is, so that the respective spacecraft is a moving or changing location Can form observatory. 25. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that in the spacecraft or earth-space spacecraft and space-moon spacecraft which are shown structurally in the constructions Fig. 30 to Fig. 65, an internal structure with combat missiles can be formed in each case, as in the construction Fig. 78 to Fig. 81 is shown structurally, so that the respective spacecraft can be deployed as a tactical interceptor. 26. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that in the spacecraft or earth-space spacecraft and space-cond spacecraft which are shown structurally in the constructions Fig. 30 to Fig. 65, an internal structure with combat missiles can be formed in each case, or not Forex rockets are trained as spell, as shown in the construction Fig. 82 bis Fig. 84 is shown constructionally, so that the respective spacecraft as tactical space interceptor can be designed or designed with research missiles can be. 27. Transport and defense system according to claim 1, 2 or 3, characterized characterized that a spacecraft with pivotable rocket engine (11) all necessary flight maneuvers in interplanetary rough. and in the earth's atmosphere and which serve as a drive, whereby ait the landing legs (15, 16, 17 ) a vertical take-off or landing e.g. B. executed on your moon or the planet earth can be and the spacecraft forms with @erodynamic wings (14 @ usg @ did, ao that a flight in the earth's atmosphere is itself and the fuel and oxidizing agents can accommodate, additional tanks (12) can also be carried. 28. Transport and defense system according to claim 1, 2 or 3, characterized characterized in that a spacecraft is designed with turbine jet engines (21) is that enable propulsion and flight in the earth's atmosphere @ and can be swiveled with attached rocket engines (19, 19a) are designed to drive the interplan @ tare Enabling space and, thanks to the movable arrangement, all necessary flight maneuvers can be carried in interplanar space and in the earth's atmosphere, whereby the wings (22, 23) are used for control in the earth's atmosphere and the landing gear (26, 27, 28) is used for takeoff and landing on planet Earth and the spacecraft The propellant and oxidant are designed with aerodynamic rragflachen (25) can accommodate, additional tanks (20) can also be carried 29. Transport and defense system according to Claim 1, 2 or 3, characterized in that a spacecraft with turbine jet triptychs (32) is designed which is the propulsion system and enable flight in the Erdatmos @ hire and with pivoting rockets engines (30) is formed, which enable the drive in the intarpianetaren space and all necessary flight maneuvers in the interplanet @ ren due to the movable arrangement Council and can be carried out in the earth's atmosphere .. the rudder (33, 35) and elevator (36, 37) for control in the earth's atmosphere and the landing gear (38, 39, 40) for take-off and landing on planet earth and the spacecraft with @erodynamic Airfoils (34) are designed to hold fuel and oxidizing agents know, whereby additional tanks (31) can be carried along. 30. Transport and defense system according to claim 1, 2 or 3, characterized characterized1 that a spacecraft with pivotably mounted rocket engines (43) all necessary flight maneuvers in the interplanetary Raui and in the earth's atmosphere can perform and serve as a drive, with larger-sized rocket engines (45) also serve as a drive and with the landing legs (47, 48, 49) a vertical movement o'ä.r landing z. B. can be carried out on the moon or planet earth and the spacecraft is designed with @erodynamic wings (46) so that a flight in the earth's atmosphere is possible and the fuel and oxidants can accommodate, additional tanks (44) can also be carried. 31. Transport and defense system according to claim 1, 2 or 3, characterized characterized in that a spacecraft is designed with turbine jet engines (56) is that enable propulsion and flight in the earth's atmosphere and can be pivoted with mounted rocket engines (53, 53a) is formed, which provide the drive in the interplanetary Allow space and all necessary flight maneuvers due to the movable arrangement can be carried out in interplanetary space and in the earth's atmosphere, whereby large-sized rocket engines (58) also serve as a drive and with the landing legs (60, 61, 62) a vertical take-off or landing z. B. on the Moon or planet earth w @ can be carried out with the wings (54, 59) are used for control in the Erdatmesspär @ and the landing gear (64,65,66,) for Take-off and landing on the planet Earth is provided and the spacecraft with aerodynamic wings (57) is the fuel and oxidizer can accommodate, additional tanks (55) can also be carried 32. Transport-. and defense system according to claim 11 2 or 3, characterized in that that a spacecraft with turbine jet engines (70) is designed for the Enable propulsion and flight in the earth's atmosphere and are swivel-mounted Rocket engine (68) is designed, which drives the interplanar space @ r possible and all necessary flight maneuvers in the interplanetary space and the earth's atmosphere can be run, being large. sized rocket engines (73) also serve as propulsion and the rudder [72, 74) and elevator (75) to Control in the earth's atmosphere serve and the landing gear (80, 81, 82) for take-off and landing on d-i planet earth is provided and the spacecraft is designed with aerodynamic wings (11) is the fuel and can absorb oxidizing agents, with additional fuel tank (69) and a vertical take-off with the landing legs (77, 78, 79) or landing e.g. B. aur of the moon or the planet earth can be carried out. 33. Transport and defense system according to claim 1, 2, 3 or fl, thereby marked that a spacecraft with pivotably mounted rocket engines (96) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere and which serve as a drive, the underside of the cell body (93) can act as a wing in the earth's atmosphere and with the lumbar legs ( 97, 98, 99) a vertical take-off or landing e.g. B. on the moon or the planet Earth can run. 34. Transport and defense system according to claim 1, 2, 3, 4 or 18, characterized in that a spacecraft with pivotably mounted rocket engines (105) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere can perform and serve as a drive, the underside of the cell body (102) can act as a wing in the earth's atmosphere and the spacecraft with it the pivoting wings 1 106) can be controlled in the earth's atmosphere and since Fanrwe @ k (109a, 110a) intended for take-off and landing on planet earth is and with the landing legs (109, 110, 111) a vertical take-off or landing z. 8. 5, t 'the mand or the planet earth can be run. 35. Transport and defense system according to claim 1, 2, 3 or 4, characterized characterized that a spacecraft with pivoted rocket engines ( 115) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere can perform and serve as a drive, with the underside of the cell body C 113) can act as an aerofoil in the earth's atmosphere, whereby the rudder ( 118) and elevator (117) are used to control the earth's atmosphere and the landing gear (124, 125) is intended for launch and landing on planet earth and, rit the landing legs (119, 120, 121) a vertical take-off or landing z. 8. Can be performed on the mouth or the planet Ere. 36. Transport and defense system according to claim 1, 2, 3, or 4, thereby characterized in that a spacecraft with pivotably mounted rocket engines (128) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere can perform and serve as a drive, the bottom of the cell body (126) can act as a wing in the earth's atmosphere and the rudder (131. ) with the elevators or wings (lc9) in interaction with the tail wings (130) are used for control in the earth's atmosphere1 whereby the landing gear (139, 138 ) for take-off and landing on planet earth and with the landing legs (134, 135, 136) a vertical take-off or landing e.g. on the moon or the planet Earth can run. 37. Transport and defense system according to claim 1, 2, 3 or 4, characterized characterized in that a spacecraft with pivotably mounted rocket engines (142) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere can perform and serve as a drive and designed with dual-circuit engines (145) is which enable the propulsion and control in the earth's atmosphere, with the underside of the cell body (140) can act as an aerofoil in the earth's atmosphere and the landing gear (150, 151) is intended for take-off and landing on planet earth is and with the landing legs (147, 148, 149) a vertical takeoff or landing z. 8. Can be performed on the moon or planet earth. 38. Transport and defense system according to claim 1, 2, 3 or 4, characterized characterized in that a spacecraft with pivotably mounted rocket engines (154) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere and which serve as propulsion and with turbine jet engines (157 ) is designed to enable propulsion in the earth's atmosphere @, with the underside of the cell body (152) can act as an airfoil in the earth's atmosphere and the spacecraft with the pivotable. Wings (158) in the earth's atmosphere can be controlled, with an additional rudder (166) being attached can. 39. Transport and defense system according to claim 1, 2, 3, 4 or 17, characterized in that a spacecraft with pivotably mounted rocket truss @@@ werke (169) all necessary flight maneuvers in interplanetary space. and in the earth's atmosphere can perform and which serve as propulsion and with turbine jet engines (172 ) is designed that enable the drive and control in the earth's atmosphere, wherein the underside of the cell body (167) in the earth's atmosphere as a wing can act and with the landing legs (174, 175, 176) a vertical take-off or landing z. B. can be performed on the moon or planet earth. 40. Transport and defense system according to claim 1, 2, C or 4, characterized characterized in that a spacecraft with pivotably mounted rocket engines (179) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere can extend and serve as a drive and with the turbine jet engine ( 183) is designed to allow propulsion in the earth's atmosphere, with the underside From the cell body (172 3 can act as an aerofoil in the earth's atmosphere and through the movable wings t 181) which act as elevator and ailerons, as well as the rudder (185) and the elevator (194) of the spacecraft in the earth's atmosphere can be controlled, with the landing gear (187, 188) for take-off and landing on planet earth and a vertical take-off with the landing legs (190, 191, 192) or landing e.g. B. can be carried out on the moon or planet earth. 41. Transport and defense system according to claim 1, 2, 3 or 41 thereby characterized in that a spacecraft with pivotably attached rocket engines (194) all necessary flight maneuvers in interplanetary space and in the earth's atmosphere can perform and which serve as propulsion and with turbine jet engines (197 ) is designed to enable propulsion in the earth's atmosphere, with the underside from the cellular structure r (193) can act as an aerofoil in the earth's atmosphere and supported by the wings (198, 230), the pivotable Wings (200 1 can act as an elevator and with the rudders (199 ) the Rsurtlugkõrper in the earth's atmosphere can be controlled and the landing gear (201, 202) is intended for take-off and landing on planet earth and with the landing legs (204, 205, 206) a vertical takeoff or landing z. B. can be performed on the moon or planet earth. 42. Transport and defense system according to claim 1, 2, 3 or 4, characterized characterized1 that a spacecraft with pivotably mounted rocket engines (210) all necessary flight manavers in the interplanetary space and in the ercatnosphere can perform and serve as a drive and designed lit dual-circuit engines (213) is that enable the propulsion in the earth's atmosphere and also the control in the earth's atmosphere, the underside of the cell body (208 ) can act as a wing in the earth's atmosphere and the H (5henruder (214, 214a ) and the rudder (217) are used for steering in the earth's atmosphere, the Landing gear (215, 216) is provided for take-off and landing on planet earth and with the landing legs (218, 219, 220) a vertical take-off or landing z. 6th can be performed on the moon or planet earth. 43. Transport and defense system according to claim 1, 2, 3 or 4, characterized characterized in that a spacecraft with pivotably attached rocket engines (224) all necessary flight maneuvers in the interplanetary council and in the earth's atmosphere and which serve as propulsion and with turbine jet engines (227 ) is designed to enable propulsion in the earth's atmosphere, with the underside of the cell body (222) can act as a wing in the earth's atmosphere, wherein the rudder (228) and elevator (230, 230a) for control in the earth's atmosphere serve and the landing gear (231, 232) for take-off and landing on planet earth is provided and eit the country legs (233, 234, 236) a vertical takeoff or Landing z. B. can be performed on the moon or the planet earth. 44. Transport and defense system according to claim 1, 2, 3 or 4, characterized characterized that a spacecraft with @swenkbar mounted rocket engines (237) all necessary flight maneuvers in int planetary space and in the earth's atmosphere can perform and which serve as propulsion and with turbine jet engines (240 ) @@@ gsetzt is that enable the propulsion in the earth's atmosphere, whereby the underside of the cell body (235) can act as an aerofoil in the earth's atmosphere and by the s @ hwenkbaren wings (242) as elevator wheels works can and with the rudders (241) the @ umflu @körper in the earth's atmosphere controlled can be, with the landing gear (244, 245) for takeoff and landing on the planet Earth is provided and a vertical take-off with the landing legs (247, 248, 249) or landing e.g. B, can be carried out on the moon or planet earth. 45. Transport and defense system according to claim 1, 2, 3, 4 or 22, characterized in that in a preferred embodiment in the cell core (250) an intermediate floor (251) is arranged on which the pilot's chair is located (253) are located so that the pilots have a good field of vision or viewing angle (255, 256, 257) have1 being through the elevator (258) and air lock (259) as well with sheep opportunities (263), a bench (266) and a multi-purpose cupboard ( 267) an interior structure for the transport of people for a longer period of time, e.g. Tie interpianetarian space or to the moon is possible. P6. Transport and defense system according to claim 1, 8, 3, 4 or 23, characterized in that an intermediate base (270) is arranged in the cell core (69) is on which the pilot chairs (271) are and by a freight elevator (277) and the cargo flaps (275, 278) an internal structure for the transport of loads e.g. in interplanetary space or to the moon is possible. 47. Transport and defense system according to claim 1, 2, 3, 4 or 24, characterized in that an intermediate floor (281) in the cell core (280) is arranged on which the pilot's chair (282) are located and by a rotatable and height-adjustable optical telescope (285) and the viewing surfaces (286) or a radio telescope an interior structure as a movable or changing location Observatory is possible. 48. Transport and defense system according to claim 1, 2, 3, 4 or 25, characterized in that an intermediate floor (297) in the cell core (296) is arranged on as there are the pilot's seats (298) and deployable combat missiles (302, 303) are arranged which can be covered with covers (335) so that an interior structure for a tactical space interceptor is possible. 49. Transport and defense system according to claim 1, 2, 3, 4 or 26, characterized in that there is an intermediate floor in the cell core (308) ( 309) is arranged on which the pilot's chair (310) are located and extendable Combat missiles (315) are arranged so that an internal structure for a tactical Space interceptor is possible, whereby research missiles are also arranged can and the landing legs (313) are in container-like bulges (314). 50. Tranuport and defense system according to claim 1, 2, 3, 4 or 5 ,. characterized in that a container in the cell core (319) (3 @ 0) is arranged and with a device ii interplanetary space odut z. B. can be dropped or resumed on the moon. 51. Transport and defense system according to claim 1, 2, 3, 4, 5, 20 or 21, characterized in that a container (330) with folding umbrella-like Plates (333) on the inside with solar cells for energy supply serve and serve to protect against engine jets, as well as with hermetically sealable TOren (331), an intermediate floor (334) and the visible surface t 332) is so that the containers are assembled individually or as individual pieces Functional spatialatations or, for example, monstations that are connected to one another. 52. Transport and defense system according to claim 1, 2, 3, 4 or 5, characterized characterized in that a container (355) is arranged in the cell core (337) and can be closed with bottom flaps (353) so the most diverse containers Forms can be transported and the respective container with a device in the interpianetarian space or z. B. dropped or resumed on the moon can be. 53. Transport and defense system according to claim 1, 2, 3, 4, 5, 20 or 21, characterized in that with segment-like containers (386, 356) the interconnected as parts, space stations or z. B. various moon stations Shapes, cross-sections and sizes as well as created for a wide variety of purposes and everyone @@ nt @ iner (355, 356) with hermetically sealed doors (355., 356a) can be closed, so that a maximum of security for People can be reached and the respective advice station or z. B. Moon station e.g. with subsequent construction stages without operation interruption of the existing ones Plant can be expanded. 54. Transport and defense system according to claim 1, 2, 3, 4, 5, 20 or 211 characterized in that in a preferred embodiment with @egment-like @ontainern (359, 360) which are connected as parts, space stations or z. B. moon stations of various shapes, cross-sections and sizes as well as for various Usages can be created with each container (3 @ 9, 3 @ 0) a Space station section or e.g. lunar station section can form those on the planets Earth were made and each container (3 @ 9, 360) with hermetically sealable Doors (359a, 360a) can be locked, so that a high level of security for people to be reached and the respective space station or z. B. Moon station with e.g. subsequent construction stages ohm interruption of the already existing one System can be expanded. 55. Transport and defense system according to claim 1, 2, 3, 4, 5, 20 or 21, characterized in that with segment-like containers (363) as Parts connected to each other, space stations or z. B. various moon stations Shapes, cross-sections and sizes as well as for a wide variety of purposes will know and each container (363) with hermetically lockable doors ( 363a) can be locked, so that a maximum of security for people can be reached and the respective space station or z. B. moon station with e.g. Later the following construction stages without interrupting the operation of the existing plant can be expanded. 56. Transport and defense system according to claim 50, 51, 52, 53, 54 or 56, characterized in that the containers (330, 355, 356, 359, 360, 363 ) each a space station section or z. B. a lunar station section on you Planet earth can be manufactured e.g. for a Luttschleuse with a system for generating it of pressure equalization, power plant for energy supply, sanitary facilities, reprocessing plant the breathing air, emergency system for processing the breathing air, emergency system for Energy supply, radio station for message transmission, measure @ t @ tion for determination your own location, locating station for detecting approaching objects, etc., connecting piece with side openings, connecting piece with floor openings or ceiling openings, Accommodation or sleeping accommodation for the crew members, rest room or dining room for the crew members, leisure room or entertainment room for the crew, living quarters or sleeping accommodation for crews of stationed persons Spacecraft, residential accommodation for visitors to the space station or z. B. the moon station, Vedlzin supply station, catering depot, oxygen tanks for the space station or z. B. the moon station, oxygen tanks to supply stationed spacecraft, Laboratory for various purposes or investigations, observatory with radio telescope, Observatory with optical telescope, Ha.igar with one-man aircraft, spare parts warehouse, Supply depot for stationed spacecraft, operations center or control center for the space station or e.g. B. Moon station, collection point for administrative tasks etc., with several containers of the same design or interior used and can be mounted. 57. Transport and defense system according to claim 6, characterized in that that a landing leg absorbs shocks and vibrations from a landing spacecraft can, with a spar (366) in a guide tube (367) by a spring (370 ) or the like. is elastically mounted and @er wedge (369) a change in position of the landing plate (368) prevented, the landing plate (356) fixed to the spar (366) is connected and by the inclined arrangement of the loin bones to the vertical axis of the spacecraft, the landing plates are far apart and the spacecraft can land in an inclined position. 56. Transport and defense system according to claim 6, characterized in that that a landing leg pivotably retracted or extended with a landing leg suspension can be, wherein in a guide tube (367) sir. Long hole (367a) arranged and the guide tube (367) is movably held by the bolt (373), wherein the landing leg or guide tube (367) exerts direct pressure against the housing (372) forms that connected to a cross brace (371) in the spacecraft is. 59. Transport and defense system according to claim 7, characterized in that that in a one-man aircraft elk a person (387) in a space suit is lying on the intermediate floor (384) is connected to the housing (377), wherein on the housing (377) pivotable rocket engines (380) are arranged With Electric motors (381) or the like. Through the shafts (379) Brackets (378) and consoles (378a) are pivoted and know the functionality With fuel tanks (383) and the battery (382) is reached, the person (387) a hold in the space suit with handles (366) and handle bars (389) has to operate the switchgear (385), seeing through the visible surfaces (391) can, with the one-man aircraft attached to handle-like @ brackets (390, 390a) and can be brought into position and the handle-like brackets (390, 390a ) can be used for take-off and landing. 80. Transport and defense system according to claim 8, characterized in that that the @aketentriebwerk (39) is firmly connected to the hollow shaft (40Q) a gear (402) by a mounted rack 1 401) or Like. Is moved and the rocket engine (393) can be pivoted, wherein the turbo pumps (395, 396) through pipes (397, 398) fuel and oxidizer convey and the Hohlwell @ t [aoo; is movably mounted in the layers (399). 61. Transport and defense system according to claim B, characterized in that that two rocket engines (403, 404) are firmly connected to the shaft (407) on which two toothed wheels (412) by two movably attached toothed racks (413 ) or the like is moved whereby the two rocket engines (403, 404) pivoted can be where i the turbo pumps (40E, 409) or the like. By pipelines (405, 406) convey fuel and oxidizing agent and the shaft (4C7) in the bearings (410, 411) is movably mounted. 62. Transport and defense system na: h claim 1, 2, 3 or 4, thereby characterized in that a spacecraft or the body containing the pilot (1) in a certain arrangement with swiveling ang @@ right rocket engines (2, 3, 4) is connected, where e.g. B. when changing the thrust direction of the rocket engine (4) one Distortion takes place the spacecraft to its transverse axis and z. B. with simultaneous Changing the direction of thrust from the rocket engine (3) changes the Spacecraft @ follows its longitudinal axis, where s @@ it is a change in position or Change of direction of the spacecraft is possible and u an overturning £; it spacecraft is interplanetary Space to avoid a counter-thrust being generated can be used to stabilize the new legs of the spacecraft and to reduce speed to reach the rocket engines (2, 4! u 180 rsd gegeng @@ chwenkt and counter thrust can be generated whereby the rocket engines (2, 3, 4, ) be pivoted 90 degrees to the longitudinal axis of the spacecraft. 63. Transport and defense system according to claim 37, characterized in that that> a preferred embodiment of the spacecraft due to the arrangement and location of the dual-circuit engines (145) can be controlled relative to one another, wherein the adjustable nozzles for deflecting the thrust of the dual-circuit engines r 15) accordingly can be adjusted to each other and due to the structural features in the interaction with the underside of the cell body (140) a controller in the earth's atmosphere is possible, with the rocket engines (142) also being able to participate