DE102016009384B4 - Method for dropping a guided missile from a flying platform - Google Patents

Abstract

A method for launching a guided missile (2) from a flying platform (4), wherein the missile (2) is dropped from the flying platform (4) and controls at least one movable rudder (12) to roll about its longitudinal axis, characterized in that the rudder (12) is blocked from being dropped by a mechanical blocking element (24), the rudder (12) is partially unlocked in the course of a dropping process by a movement of the blocking element (24), so that the rudder (12) is only partially connected ( 42) of its rudder deflection area (44) is movable, and the blocking element (24) after reaching a predetermined flight phase of the missile (2) the rudder (12) completely unlocked, so that it is movable over its entire rudder deflection area (44).

Description

The invention relates to a method for dropping a missile from a platform, in which the missile is dropped from the flying platform and using at least one movable rudder controls a rolling motion about its longitudinal axis.

When dropping a missile from a flying platform, such as a helicopter or an aircraft, there is a risk that the missile collides with the ejection by uncontrolled movements of the platform and this damage.

It is therefore an object of the present invention to provide a safe method for launching a missile.

This object is achieved by a method of the type mentioned, in which according to the invention the rudder is blocked from being dropped by a mechanical blocking element, the rudder is partially unlocked in the course of a discharge process by a movement of the blocking element, so that the rudder is movable only over part of its rudder deflection range is and the blocking element after reaching a predetermined flight phase of the missile completely unlocks the rudder, so that it is movable over its entire rudder deflection range.

The invention is based on the consideration that prevail at the moment of dropping the missile complex aerodynamic conditions to the missile. During the flight, the flying platform is surrounded by air, so that especially under the pylon to which the missile hangs, strong side winds can occur. The configuration of this winch also depends on the current flying maneuver of the flying platform.

The guided missile includes guided wings, which are provided with movable rudders for influencing the attitude. The rudders are connected to a drive so that a control unit can control the attitude of the missile by controlling the drive or drives. Especially with the complex aerodynamic conditions when dropping it may happen that a control error leads to the just discarded and, for example, not yet driven missile takes a trajectory that brings him on a collision course with the abwerfenden platform. Impacting the missile on the platform can severely damage both units.

One solution to this problem is that the missile receives no steering authority over the rudders when dropped until it reaches a safe distance from the platform. These can be blocked by a blocking element, so that the faulty control of a collision-causing maneuver is mechanically prevented.

Here, however, there is the problem that the thus passivated missile can still abut directly on the movable platform after dropping. This is due to the fact that the flow around a wing carrying the missile of the flying platform can cause a cross flow located under the wing, which acts on the missile. Such a transverse flow can be disturbed by the pylon in such a way that a flow field is formed which flows asymmetrically against the guided missile. As a result, a rolling moment is exerted on the missile, by which the missile is biased in its still attached to the platform position with a torque. Immediately after unlatching, the flow-related roll rate can increase in such a way that a wing or rudder of the guided missile strikes against the pylon. The guided missile may be damaged and may no longer be manoeuvrable.

The invention is based on the further consideration that the rudders can be controlled via a mixer in order to generate pitch, yaw and roll moments for the implementation of flight control specifications. This has the respective flight commands as input and generates from this the rudder deflections to be produced. This results in the law that differential, ie nonuniform or opposite deflections of the rudder are necessary for the pitching and yawing moments. In contrast, only in the same direction deflections lead to a pure rolling motion. As a result, significantly smaller rudder deflections are required for a pure rolling movement than for a similarly strong pitching or yawing maneuver. In addition, its guided missile has greatly differing moments of inertia due to its typical shape. The moment of inertia about the roll axis is considerably smaller than the moment of inertia about the pitch and yaw axis.

As a result, a roll rate can be increased or decreased significantly less than rates around the other axes. In order to control a rolling of the missile, therefore, much smaller rudder deflections are necessary, as in an equally strong control of a pitch or yaw. When dropped, it is therefore sufficient if the rudders only slightly deflect to compensate for the aerodynamically caused rolling forces. Will the oars on such a deflection limited, it can be sufficiently counteracted by a rolling impact and an undesirable collision course to the platform by a faulty pitching maneuver of the missile at dropping effectively prevented.

The blocking element according to the invention allows the rudder to be partially unlocked, so that the rudder is movable only over a part of its rudder deflection. As a result, an undesired pitching motion can be effectively prevented. After reaching the predetermined flight phase, for example, when reaching a predetermined distance of the missile to the platform, the rudder is fully released, so that the missile can be freely controlled to its predetermined destination to be controlled. As a result of a simple mechanical measure, both a collision due to incorrect control and because of a transverse flow-related rolling movement after being dropped off can be avoided.

The flying platform is, for example, an aircraft or a rotorcraft, under the wing of the missile hangs during a flight. The missile has expediently four wings in the X position, wherein during a flight in particular two of the wings are directed obliquely downwards and two obliquely upwards.

The missile may include a propulsion engine including a rocket engine or an air-breathing engine, such as a turbine. The discharge may be a notching and down throwing the missile or starting at a ramp forward. The discharge process expediently comprises the entire process associated with a discharge, such as a discharge preparation and the discharge itself, and in particular also a flight control phase due to the discharge in the immediate vicinity of the platform. The ejection preparation can be initiated, for example, by an operator of the flying platform, who releases the missile for ejection. Controlling a rolling movement after ejection expediently also includes the countersteering against an externally applied rolling moment, so that the resultant is an at least substantially vanishing roll rate.

The mechanical blocking element blocks the rudder before the departure of the guided missile. The rudder is thereby expediently at least substantially immobile, so fixed to the fuselage of the missile. During partial unlocking, the rudder is movable over part of its rudder travel range. The rudder deflection area expediently comprises the deflection area, which can be achieved by the steering control during a regular control operation of the guided missile. In the case of partial unlocking, the area is expediently limited to less than 30% of the total rudder deflection range, in particular to a maximum of 20%.

If the missile has left the vicinity of the flying platform, it enters the predetermined flight phase, in which the rudder is completely unlocked. The predetermined flight phase can begin when the missile has flown or fallen, for example, a minimum distance from the platform or a minimum time after the dropping or unlatching.

In general, the blocking element is expediently connected to a drive which moves it along a predetermined path. The movement of the blocking element is expediently controlled by a control unit which controls the drive.

Conveniently, all present in the same axial position of the missile rudder, in an X-position so all four rudders, equipped with a blocking element according to the invention, so that a partial release according to the invention is made possible for all oars. The partial release can be equally effective for all rudders, so that the currently possible rudder deflection range for all rudders of a group, ie all rudders in the same axial position on the guided missile, is the same.

In an advantageous embodiment of the invention, the blocking element engages in the rudder and is moved out of the rudder for unlocking. Instead of or in addition to an intervention, the blocking element can be applied from the outside to the rudder, for example at a trailing edge of the rudder. For partial or complete unlocking, the blocking element may be removed radially inward, in the tangential direction, in the axial direction or in a combination of two or more directional components from the rudder. It is also possible that the blocking element is guided around the rear edge of the rudder and is removed for unlocking to the rear, ie in the axial direction of the missile from the trailing edge. When the blocking element is removed from the rudder, at least part of the blocking element moves away from the rudder, for example, the blocking element moves wholly or partly out of the rudder.

If the blocking element engages in the rudder to block this in whole or in part, there is the possibility that it engages from radially inside, ie in the radial direction of the missile from the inside out. To unlock the blocking element can now be moved out of the rudder at least predominantly in the radial direction inwards. Depending on the application, it can also be beneficial be that the blocking element for unlocking at least predominantly in the axial direction is moved out of the rudder.

A further advantageous embodiment of the invention provides that a form-fitting backdrop of blocking element and rudder is stepped at least twice. The step may be formed by a step in the blocking element and / or by a step in the rudder. The blocking element is now expediently moved discretely from a blocking position into a partially unlocked position and from there into a release position. It is expedient if the blocking element remains stationary in the partially unlocked position until it is then moved, expediently, in the release position. In this way, a partial release, ie a release of a defined part of the entire rudder deflection range, can be defined. A movement from one stage to the next expediently takes less than one third of the time in which the blocking element remains stationary in the partially unlocked position. The movement of the blocking element from position to position expediently takes place so far, for example within less than 0.5 seconds.

In a rapid movement of the blocking element, there is the possibility that the blocking element is moved by a faulty control too quickly in its release position. The rudder is fully unlocked and mismanagement, for example on a collision course with the launching platform, is possible. To avoid this, it is advantageous if the drive of the blocking element is designed so that it moves the blocking element only slowly from the blocking position on the partially unlocked position to the release position, for example, a total of a period of at least two seconds, in particular at least five seconds , The drive is expediently designed so that a faster unlocking movement is not possible. Too fast unlocking and thus the risk of a collision course is thus prevented.

In particular, in a continuous movement of the blocking element, it is advantageous if the blocking element releases the rudder continuously by a removal from the rudder from the blocked position to the full position again. The part of the rudder deflection range over which the rudder is movable thus becomes continuously larger over time, at least substantially linearly continuously larger. To achieve this, it is expedient to provide a continuous form-fitting backdrop of blocking element and rudder to one another.

In the wing flight and the moment of the ejection of the missile is usually flowed asymmetrically from the side, so acting on him a roll moment. Even if this rolling moment can be dependent on a flight maneuver currently being flown by the flying platform, ie is variable in its size, it will as a rule only be directed in one direction. It is therefore sufficient in many cases in a drop, counteract the rolling moment in one direction only. To achieve this, it is advantageous if the rudder is released asymmetrically in the partially unlocked position, so that the maximum released rudder deflection in one direction is greater than in the other direction. Directional, the rudder deflection can be viewed from a center position.

The invention is also directed to a method for controlling a missile, in which a rudder of the missile is moved by a steering mechanism in a steering manner and the flight of the missile is thereby controlled.

Conveniently, the rudder is placed in a rudder hard position, in which the rudder is thus aligned in a maximum deflection, for example, abuts against a stop. The rudder can now stay there. A Ruderhartlage can be useful if the missile is to be braked hard or defined to crash should be, for example, a maneuver abort.

During a flight of a guided missile, it may happen that the flight of the missile should be stopped or slowed down considerably. For example, the missile should not leave a predetermined safety zone in a test shot. Or a signal connection between flying platform and guided missile breaks off or is disturbed, so that a misdirection of the missile is to be feared. Or the guided missile is placed on a wrong target and an attack should be stopped as soon as possible. In principle, such a maneuver termination can also be initiated by the control unit which controls the regular flight of the guided missile. However, it may happen that the control unit is defective, unreachable, or unable to act quickly enough, for example, when the missile is on a wrong destination and would take a while to "understand". It is therefore advantageous to have a system with which a flight termination can be achieved with simple means.

This object is achieved by a method for controlling a guided missile as described above, wherein according to the invention, the rudder is pressed by an additional blocking element to the control mechanism in the Ruderhartlage and / or held in the Ruderhartlage. This can a control by the control unit may be overridden, so that the rudder remains in its rudder hard position. Depending on the force effectiveness and control algorithms, a maneuver abort may also be obtained contrary to the commands of the regular control unit.

The blocking element can advantageously have a double function: It can unlock the rudder in the ejection process, whereby a partial unlocking is performed as an intermediate step, and it can bring the rudder into the rudder hard position and / or hold there. In this respect, advantageously, all the details of the method for dropping a guided missile from a flying platform can also be combined with the method for controlling a guided missile and vice versa.

In an advantageous embodiment of the invention, the blocking element moves by its movement into a hard-position position, the rudder in a Ruderhartlage. As a result, for example, a control operation of the regular control unit can be overridden and a reliable braking or crashes of the missile can be achieved. Advantageously, the movement of the blocking element to its hard position is controlled by an algorithm which is in addition to a regular steering control algorithm of the guided missile. The movement of the blocking element to its hard position may be triggered by a special signal, for example a signal cancellation from or to a higher-level control system, such as the flying platform. However, the special signal can also be sent specifically to achieve a quick maneuver abort.

Further, it is advantageous if the blocking element passes through a backdrop during its movement into a hard position, by which the movement of the blocking element is converted into a rudder movement in the rudder hard position of the rudder. The Ruderhartlage can be reliably achieved in this way on simple mechanical means.

A maneuver abort is expediently only after a certain flight of the missile. It is advantageous in that the blocking element is moved from its release position to its hard position and there holds the rudder in the Ruderhartlage. In this case, the blocking element when moving from the release position to the hard position can pass through the blocking position, which is thus between the release position and the hard position. It is also possible that the hard position of the blocking element is in relation to a release position against a blocking position. In this case, therefore, the release position would lie between a blocking position and a hard position.

It may be that the rudder is already worn out at the time of a maneuver crash. Optionally, then a backdrop control of the rudder in its hard position is not possible. In this respect, it is also advantageous if the blocking element presses the rudder from the outside in the Ruderhartlage when moving into the hard position.

Further, the invention is directed to a rudder position for a discharge missile comprising a static system for fixation in the missile and a static system movable rudder.

It is proposed that the static system according to the invention comprises a blocking element and a drive for moving the blocking element, wherein the blocking element and the rudder are arranged to each other, that the blocking element mechanically fixes the rudder and teilentriegelt the rudder after moving the blocking element by the drive is and is movable only over part of its rudder range.

It is expedient if the rudder is completely unlocked after a further movement of the blocking element, so that it is movable over its entire rudder deflection range. An ejection missile may in this case be a missile that is dropped by a flying platform, for example, down or at an independent start to the front.

The description given herein of advantageous embodiments of the invention includes numerous features, some of which are set forth in several of the appended claims. However, the features may conveniently be considered individually and grouped together into meaningful further combinations, in particular when reclaiming claims so that a single feature of a dependent claim can be combined with a single, several or all features of another dependent claim. In addition, these features can be combined individually and in any suitable combination both with the inventive method and with the device according to the invention according to the independent claims. Thus, process features can also be formulated formally as properties of the corresponding device unit and functional device features also as corresponding process features.

The above-described characteristics, features and advantages of this invention and the The manner in which these are achieved will become clearer and more clearly understood in connection with the following description of the exemplary embodiments, which are explained in more detail in connection with the drawings. The embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, not even with respect to functional features. In addition, suitable features of each embodiment may also be explicitly considered isolated, removed from one embodiment, incorporated into another embodiment to supplement it, and / or combined with any of the claims.

• 1 einen Lenkflugkörper unter einem Flügel einer fliegenden Plattform,
• 2 den Lenkflugkörper in einer schematischen Ansicht von vorne,
• 3 einen Flügel des Lenkflugkörpers mit einem Ruder,
• 4 die Hinterkante eines Ruders mit einem dahinter und um die Ruderkante angeordneten Blockierelement,
• 5 ein schematisch angedeutetes Ruder mit einem von radial innen in das Ruder eingreifenden Blockierelement,
• 6 ein hinsichtlich der ermöglichten Ruderausschläge asymmetrisches Blockierelement,
• 7 ein gestuftes Blockierelement,
• 8 ein Blockierelement in einer gestuften Ausnehmung eines Ruders,
• 9 ein asymmetrisch einseitig gestuftes Blockierelement,
• 10 die Hinterkante eines Ruders eines Lenkflugkörpers mit einer Kulisse, in die ein Blockierelement von radial innen eingreift,
• 11 das Ruder in einer Ruderhartlage, durch die es vom Blockierelement in der Kulisse gedrückt wird,
• 12 das Ruder mit einem Ruderausschlag, der es vom Blockierelement weg bewegt,
• 13 das Ruder, das vom außerhalb des Ruders abgeordneten Blockierelement in seiner Ruderhartlage gedrückt wird,
• 14 ein Ruder mit einer Kulisse, in der eine Hartlagenposition eines Blockierelements gegenüber einer Blockierstellung des Blockierelements liegt,
• 15 das Ruder in seiner Hartlagenposition,
• 16 ein Ruder, das von einem Blockierelement wie aus 4 von außen in eine Ruderhartlage gedrückt wird, und
• 17 ein Ruder, das von einem Blockierelement ähnlich zu 5 von außen in eine Ruderhartlage gedrückt wird.

Show it:

• 1 a guided missile under a wing of a flying platform,
• 2 the guided missile in a schematic view from the front,
• 3 a wing of the guided missile with a rudder,
• 4 the trailing edge of a rudder with a blocking element behind and around the rudder edge,
• 5 a schematically indicated rudder with a radially inwardly engaging in the rudder blocking element,
• 6 an asymmetrical blocking element with regard to the permitted rudder deflections,
• 7 a stepped blocking element,
• 8th a blocking element in a stepped recess of a rudder,
• 9 an asymmetrically one-sided stepped blocking element,
• 10 the trailing edge of a rudder of a guided missile with a gate into which a blocking element engages from radially inside,
• 11 the rudder in a rudder hard position, by which it is pressed by the blocking element in the scenery,
• 12 the rudder with a rudder stroke that moves it away from the blocking element,
• 13 the rudder, which is pressed in its rudder hard position by the blocking element which is separated from outside the rudder,
• 14 a rudder with a link in which a hard-ply position of a blocking element lies opposite a blocking position of the blocking element,
• 15 the rudder in its hard position,
• 16 a rudder that looks like a blocking element 4 pressed from the outside in a Ruderhartlage, and
• 17 a rudder similar to that of a blocking element 5 pressed from the outside in a Ruderhartlage.

1 shows a guided missile 2 standing under a wing of a flying platform 4 during a flying platform flight 4 hangs. The guided missile 2 is with a coupling unit 6 on a pylon 8th the flying platform 4 attached and can by releasing the coupling unit 6 be dropped. When the missile is dropped 2 If it falls down, it starts its own engine 10 and flies - by oars 12 controlled - towards an aimed goal too. The oars 12 are on the helm 14 attached and can by a corresponding movement a rolling motion, a pitching motion and / or a yaw motion on the guided missile 2 exercise. Alternatively to a drop down the missile can 2 in another embodiment, start forward by using his engine 10 Feed provides and the coupling unit 6 in a rail of the pylon 8th is guided forward until the missile 2 the pylon 8th leaves. When dropped down, the engine can 10 be an air-breathing engine, for example in the form of a turbine, when dropped forward it is expediently a rocket engine.

2 shows the guided missile 2 hanging on the pylon 8th the flying platform 4 in a schematic representation from the front. You can see his four wings 14 flying in X-position in flight under platform 4 are arranged. During the flight the guided missile becomes 2 not only from the front streamed by air. Through the hull of the flying platform 4 , which is for example an airplane or a rotorcraft, arise through the hull of the platform 4 crosscurrents 16 , in the 2 are indicated by a plurality of straight dashed arrows. Due to air resistance near the wing, these transverse winds increase with increasing distance from the wing, as in 2 is indicated by the length of the straight arrows. This will affect the missile 2 a rolling moment 18 applied that in 2 indicated by the curved arrow. This rolling moment 18 arises in particular by attacking the cross flow 16 on the steering wings 14 , but also on the front wings 20 and on the hull 22 of the guided missile 2 , As a result, the missile hangs 2 already biased during the flight on the pylon 8th ,

At a drop of the missile 2 from the flying platform 4 causes the rolling moment 18 a roll acceleration on the guided missile 2 that can lead to the missile 2 on the pylon 8th strikes, especially with a steering wings 14 in particular, a damage of a rudder 12 and thus an impairment of the maneuverability of the guided missile 2 threatening. To counteract such damage, the guided missile performs 2 expediently already during the ejection process before the discharge or notching out of the pylon 8th a steering movement with his oars 12 that the rolling moment 18 counteract.

Is a control of the rudder positions of the missile 2 if dropped by any action, it would cause a pitching moment on the missile 2 up to its collision with the platform 4 to lead. To counteract such a fault control is every oar 12 a blocking element 24 ( 3 ) associated with a strong steering rudder of the rudder 12 blocked.

3 shows the blocking element 24 at the helm 12 one of the steering wings 14 of the guided missile 2 , In 3 is the blocking element 24 indicated only schematically and shown only for a better understanding will in a bolt shape. There are many different shapes and positions of the blocking element 24 some of which are exemplified in the following figures.

In the exemplary embodiments, substantially identical components are numbered with the same reference numerals. For ease of understanding, moreover, like components in different embodiments are designated by the same reference numerals and other reference characters, and may be identical to each other or with slight differences from each other, for example, in size, shape, position, and / or function. If the reference number alone is mentioned without a reference letter, then the corresponding components of all embodiments are addressed.

In 3 is a rudder system 26 of the guided missile 2 hinted that in addition to the four wings 14 with the associated oars 12 actuators 30 and a control unit 28 for the output of control signals to actuators 30 the helm 12 having. The control unit 28 comprises a mixer, not shown, which converts steering signals into rudder deflections and corresponding control signals to the four actuators 30 the four oars 12 outputs. Next is available for each rudder 12 a blocking element 24 with an associated drive 32 with which the blocking element 24 in the radial direction 34 inwardly or outwardly, as indicated by the double arrow, or in the axial direction 36 forward or backward, as indicated by the two horizontal arrows in 3 is indicated, lets move. A tangential component of motion is also conceivable. The drive 32 is also controlled by the control unit 28 controlled with the appropriate control signals. The control unit 28 is with the drive 32 and the blocking element 24 Part of a static system 38 that on or in the hull 22 of the guided missile 2 is fixed. The blocking element 24 and parts of the actuator 30 are of course relative to the hull 22 movable.

4 shows an embodiment 24a of the blocking element 24 that from the outside the trailing edge 40 of the rudder 12 embraces. Shown is a section through the rudder 12 , wherein the direction of view in the radial direction to the missile 2 is directed. The view is from outside on the blocking element 24a as a sheet near the fuselage 22 lies and in the axial direction 36 of the hull 22 is mobile. It encompasses the helm 12 bifurcated from behind, so this - as in the left illustration 4 can be seen - is blocked in his rowing motion. The left position of the blocking element 24a shows the blocking position in which the blocking element 24a during the flight and before the missile is dropped 2 from the platform 4 is positioned. A rudder movement of the rudder 12 is completely stopped, which provides the advantage that during the flight on the rudder 12 acting aerodynamic forces on the blocking element 24a act and the actuator 30 is mechanically protected.

Before, during or after the release, ie the release of the missile from the pylon 8th , expediently during a discharge process and in particular before discharge, moves the drive 32 the blocking element 24a axially to the rear in a discharge position, in the middle representation of 4 is shown. In this discharge position is the rudder 12 partially unlocked, so it over part 42 his entire rudder area 44 is mobile, for example 15%. The agility is due to a stroke of the rudder 12 at the blocking element 24a stopped or limited. As a result, there is a certain controllability of the missile 2 , which is however limited to weak steering movements. A strong pitching upwards by a faulty control is not possible. It is possible, however, by a same-row rudder deflection of all four rudders 12 a rolling moment through which the prevailing roll moment 18 is balanced, so the missile 2 can be dropped harmlessly.

In the middle view off 4 can be seen that the available part 42 the total rudder area in its size depending on the position of the blocking element 24a is. The further the blocking element 24a from the trailing edge 40 of the rudder 12 is removed, the larger is the passable part 42 of the entire rudder area 44 of the rudder 12 , for example includes the passable part 42 maximum 25% of the total rudder range.

To control the positions of the blocking element 24 There are generally different possibilities.

In a first possibility becomes the blocking element 24 moved into a discharge position, which releases a sufficient rudder deflection, a collision-free ejection of the missile 2 to guarantee. During the discharge and a subsequent subsequent discharge phase, the blocking element remains 24 in this discharge position. Has the guided missile 2 reaches a predetermined flight phase, for example, a sufficient distance from the platform 4 , so by a further movement of the blocking element 24 the rudder 12 fully released, as exemplified in the right figure of 4 is shown. In this release position is the blocking element 24 so arranged that the rudder 12 with double-sided full rudder deflection the blocking element 24 not touched anymore. Discharge position and release position are expediently approached discreetly. The blocking element 24 rests in the discharge position until the guided missile 2 has reached the predetermined flight phase.

Another possibility is that the rudder deflection is released continuously. During the ejection process of the missile thus far increases the part 42 continuously on. This can be achieved by a continuous movement of the blocking element 24 This is a steadily growing part of this 42 releases, as exemplarily from the middle representation 4 can be seen. This method has the advantage of being a slower drive 32 can be used, allowing a high moving speed of the blocking element 24 insofar prevented. A complete release of the rudder 12 still too close to the guided missile 2 from the platform 4 This also causes a control error of the control unit 28 to the drive 32 reliably avoided. This allows greater security against collision of the missile 2 at the platform 4 be achieved.

At the in 5 illustrated embodiment is the rudder 12 shown in a sectional view, in which the sectional plane perpendicular to the tangential direction of the missile 2 is aligned. You can see the axis of rotation 46 to the rudder 12 is rotatable. From the hull 22 protrudes a blocking element 24b radially outward and penetrates from the inside into a recess 48 of the rudder 12 one. In the left display off 5 is the blocking element 24b shown in its blocking position, in which a rudder deflection movement of the rudder 12 is completely blocked. In the middle illustration is the discharge position of the blocking element 24b shown in the only part of the rudder area 44 is released. Again, as in the previous embodiment, a continuously increasing partial release or Teilentriegelung the rudder 12 by a continuous movement of the blocking element 24b possible. The right representation off 5 shows the blocking element 24b in its release position, in which the oar 12 over its entire rudder area 44 is released or completely unlocked.

The embodiment of 6 is similar to that 5 with the difference that the blocking element 24c asymmetrical in shape is that it is the rudder 12 in the partially unlocked position with respect to the possible rudder portion 42 asymmetrically releases. Starting from the blocking position shown in the left figure, the rudder is 12 in the partially unlocked position, shown in the middle figure, movable in one direction only. Alternatively, it is possible to allow a larger deflection in one direction than in the other direction. The asymmetry of the blocking element 24c would be designed accordingly. In this way, the rolling moment 18 be sufficiently counteracted without the rudder 12 to release to a large extent.

In the embodiments of the 7 to 9 are three different form-fitting backdrops 50a-c shown by a respective recess of the rudder 12 and the blocking element therein 24d-f are formed. The form-fitting backdrops 50a-c are each two-fold, to show the stepped principle. In the same way, more levels are possible.

In the embodiment of 7 be the two stages of the blocking element 24d formed, which has a stepped body. 7 shows the partially unlocked position of the blocking element 24d , Is the blocking element 24d extended a little further, it is in its blocking position, in which the radially inner and thicker part of the blocking element 24d a blocking step that forms the rudder 12 blocked. The radially outer and thinner part of the blocking element 24d holds the helm 12 in the partially blocked stage where it is partially unlocked. Due to the stepped form-fitting backdrop 50a can both the blocking position and the partially unlocked position of the blocking element 24d even with a less accurate positioning of the blocking element 24d can be set exactly without this affecting the released part of the rudder deflection range.

In the embodiment of 8th becomes the form-fitting backdrop 50b through a grading in the recess in the rudder 12 educated. The narrower part of the recess here forms the blocking stage, which in conjunction with the introduced blocking element 24e the rudder 12 blocked. The wider in Ruderausschlagrichtung part of the recess forms together with the blocking element 24e a partially unlocked area in which the rudder deflection of the rudder 12 partially released.

The embodiment of 9 is similar to that 7 , however, where the form-fitting backdrop 50c the rudder in a stepped manner only in one direction releases, so that an asymmetric Teilentriegelung the rudder 12 is reached. The grading may be from the blocking element 24f be formed or from a recess in the rudder 12 analogous to example 8th ,

In the embodiments of the 5 to 9 becomes the helm 12 unlocked by the relevant blocking element 24b-f for example in the radial direction 34 out of control 12 moves out. In the embodiment of 10 becomes the release position of the blocking element 24g achieved by its movement, which is substantially perpendicular to the radial direction 34 is. As in 5 is the helm 12 perpendicular to the radial direction 34 cut just inside its radially inner end, so close to the hull 22 , You can see that the hull 22 facing side of the rudder 12 with a backdrop 52a is provided. This forms a recess into which the blocking element 24g intervenes.

10 shows the blocking element 24g in three positions: one in 10 overhead blocking position, a middle teilentriegelnden position and a in 10 shown below release position. Dash-dotted is the axis of movement of the blocking element 24g shown running straight between these three positions. The movement axis extends, for example, in the axial direction of the missile 2 or more generally: parallel to the missile 22 of the guided missile 2 ,

The scenery 52 is designed to narrow the blocking position, so that the blocking element 24g when entering the rudder 12 this is always blocked. The scenery 52 forms an inner channel 54 , which is designed in its dimensions so that the blocking element 24g the rudder is in the canal 12 completely blocked. Towards the rear, ie towards the trailing edge 40 of the rudder 12 , the channel widens 54 so that in the middle, partially unlocked position the rudder 12 about a part 42 of the entire rudder area 44 is mobile. In the release position, the rudder 12 in both rudder directions completely over the blocking element 24g drive away, so this, even if it is still out of the fuselage 22 sticking out, the helm 12 no longer blocked but this is completely unlocked.

In principle, the channel can 54 where ends the blocking element 24g takes his blocking position. In the example off 10 However, the channel is still running. This allows the rudder 12 by a movement of the blocking element 24g be pressed into a rudder hard as in 11 is shown.

At the in 11 illustrated embodiment, the blocking element 24g be moved further beyond its blocking position. It thereby moves through the channel 54 the scenery 52 , By the leadership of the canal 54 becomes the helm 12 by the movement of the blocking element, for example in the axial direction of the guided missile 2 , forcibly deflected, for example, in his rudder hard, the in 11 is shown. By a backward movement of the blocking agent 24g becomes the helm 12 brought back to its neutral position and upon further movement of the blocking element 24g first partially unlocked and then fully unlocked, as by the three lower positions of the blocking element 24g in 11 is indicated.

It may be that it makes sense, the helm 12 during the flight of the guided missile 2 into his rudder hard, for example, the missile 2 slow down as soon as possible or cause it to crash. This can be achieved by the blocking element 24g the channel 54 until its end or until the hard position of the blocking element 24g traverses. In the embodiment of 11 However, it is visible that this only works when the blocking element 24g within the backdrop 52 located. However, this does not have to be the case.

This example is in 12 clarified. The rudder 12 has a certain rudder deflection and is intended by the blocking element 24g be brought in Ruderhartlage. This could be the helm 12 be placed in its neutral position in 10 is shown, and the blocking element can be moved to the hard position position, as in 11 is shown. Is however a control of the rudder 12 in this neutral position not possible, for example, because the control unit 28 is defective or a signal between a control station and the guided missile 2 Demolished, so should the oar 12 still be in a row. This is possible, as in the two representations of the 12 and 13 is shown. The blocking element 24g is moved in the direction of its blocking position, as in 12 indicated by the arrow. It gets outside at the helm 12 strike it and press it now from the outside into the rudder hard position, as in 13 is shown. The rudder hard of the rudder 12 This is already achieved when the blocking element 24g not yet in its blocking position, as in 13 is shown. Instead, an outer blocking position is reached, in which the rudder 12 its maximum deflection in one direction, that is, its rudder hard, has reached. This is in 13 shown in which the blocking element 24g has taken his outer blocking position. Based on the shape of the backdrop 52 can the oar 12 regardless of its starting position of the blocking element 24g be pushed into his rudder hard.

The embodiment of the 14 and 15 shows an alternative backdrop 52b in which the blocking position of the blocking element 24g lies opposite a hard layer position, which in 15 is shown. 14 shows the blocking element 24g in a rear blocking position, in which it is the trailing edge 40 is closest. Farther forward is the blocking element 24g in a teilentriegelnden position and even further forward in its release position shown in the rudder 12 , without the blocking element 24g Can be moved across this over its full rudder range. Further forward, the canal closes 54 on, the hard position of the blocking element 24g leads.

15 shows the blocking element 24g in five possible positions. The topmost position or from the perspective of the guided missile 2 Foremost position shows the blocking element 24g in its hard position in the channel 54 , Will the helm 12 from the blocking element 24g Pressed from the outside in his Ruderhartlage, so is also drawn hard position of the blocking element 24g a little further back. In addition, the further rear positions of the release position, the teilentriegelnden position and the blocking position along the dash-dotted axis of movement are shown. The embodiment of the 14 and 15 has the advantage that the blocking element 24g can be driven a little faster in its hard position, since it does not have to go through the blocking position. This allows the constriction of the release position in the channel 54 faster or the narrowing of the release position to the point of blocking position can be independent of the channel 54 be designed.

16 shows an embodiment in which the basis of the blocking element 24a out 4 it is shown that this too is the helm 12 can push into a rudder hard position. For this, however, it is necessary that the rudder 12 already in a relatively far moved out of the middle state. A certain control of the rudder 12 through the control unit 28 is therefore still necessary. The advantage with the blocking element 24a is mainly that the rudder 12 can be kept in its Ruderhartlage, even if afterwards the control unit 28 or control of the rudder 12 fails.

Similarly, it is in the embodiment of 17 , This is similar to the embodiment 5 in which a section is shown with a viewing direction from behind. The front tip of the blocking element 24g However, it is rounded to the rudder 12 to push from the outside frictionless in the Ruderhartlage, in 17 is shown. In contrast to 5 is the helm 12 not viewed from the side but from behind, so that the rudder deflection corresponds to the double arrow. Next to the recess 56 in which the blocking element 24 hours is in its blocking position and teilentriegelnden position, is the rudder 12 with tangentially outwardly open recesses 58 provided at which the tip of the blocking element 24 hours driving along.

Based on the rudder width and the rudder deflection, it can be seen that the blocking element 24 hours or the recesses 56 . 58 relatively far forward, so near the rudder axis 46 should lie in which the outer edge of the rudder 12 in hard position not far from the symmetry plane of the rudder 12 should be removed in its center position. Again, the blocking element pushes 24 hours the rudder 12 in an extension towards the blocking position in his Ruderhartlage. At the in 17 the embodiment shown, the blocking element moves 24 hours beyond his blocking position. Here too is a push of the rudder 12 in his Ruderhartlage only possible if the blocking element 24 hours laterally next to its recess 56 comes to rest, in which it is retracted in its blocking position. Again, the advantage lies in the fact that the blocking element 24 hours the rudder 12 can hold in the Ruderhartlage, without this being the control unit 28 requirement.

In the embodiments of the 10 to 17 takes the blocking element 24g . 24 hours a double function. It blocks the rudder 12 in its rudder deflection completely, for example during a flight. There is also the helm 12 in a teilentriegelnden position partially free and in the release position completely free. It can also be the helm 12 push into his rudder hard and hold in this. Here are the functions of blocking, Teilentriegelns and releasing one hand, and the pressing in the Ruderhartlage and holding there on the other hand independent of each other. It is therefore possible, the blocking element 24g . 24 hours to have only one function, for example for pressing or holding the rudder 12 in the hard layer, wherein the release with the Teilentriegelung is omitted.

LIST OF REFERENCE NUMBERS

2

Missile

4

platform

6

coupling unit

8th

pylon

10

engine

12

rudder

14

steering wings

16

crossflow

18

roll moment

20

wing

22

hull

24a-h

blocking element

26

rudder system

28

control unit

30

actuator

32

drive

34

radial direction

36

axially

38

static system

40

trailing edge

42

part

44

Rudder area

46

axis of rotation

48

recess

50a-c

Form-fitting backdrop

52a-b

scenery

54

channel

56

recess

58

recess

Claims (14)

A method for launching a guided missile (2) from a flying platform (4), wherein the missile (2) is dropped from the flying platform (4) and controls at least one movable rudder (12) to roll about its longitudinal axis, characterized in that the rudder (12) is blocked from being dropped by a mechanical blocking element (24), the rudder (12) is partially unlocked in the course of a dropping process by a movement of the blocking element (24), so that the rudder (12) is only partially connected ( 42) of its rudder deflection area (44) is movable, and the blocking element (24) after reaching a predetermined flight phase of the missile (2) the rudder (12) completely unlocked, so that it is movable over its entire rudder deflection area (44). Method according to Claim 1 , characterized in that the blocking element (24b-h) engages in the rudder (12) and is moved out of the rudder (12) for unlocking. Method according to Claim 1 or 2 , characterized in that the blocking element (24g) from radially inward in the radial direction (34) outwardly into the rudder (12) engages and for unlocking at least predominantly in the axial direction (36) is moved out of the rudder (12). Method according to one of the preceding claims, characterized in that a form-fitting gate (50) of the blocking element (24d-f) and rudder (12) is at least twice stepped to each other, so that the blocking element (24d-f) the rudder (12) in the locked state holds with a blocking stage, then moved to the teilentriegelte position and there holds the rudder (12) partially unlocked with a partially blocking stage, remains there dormant and then moved to a release position and thereby completely unlocks the rudder (12). Method according to one of Claims 1 to 3 characterized in that the blocking member (24a-c, 24g-h) continues to release the rudder (12) from the blocked position to the fully unlocked position by removal from the rudder (12). Method according to one of the preceding claims, characterized in that the rudder (12) is released asymmetrically in the partially unlocked position, so that the maximum released rudder deflection in one direction is greater than in the other direction. Method according to one of the preceding claims, characterized in that the rudder (12) is guided by a rudder system (26) and the flight of the guided missile (2) is controlled thereby after the discharge and by the rudder (12) then into a rudder hard position is brought, in which the rudder (12) is in a maximum deflection, and remains there, wherein the rudder (12) by the rudder system (26) additional blocking element (24) is held in the Ruderhartlage. Method according to one of the preceding claims, characterized in that the Blocking element (24) moved by its movement in a hard position position the rudder (12) in a Ruderhartlage. Method according to one of the preceding claims, characterized in that the blocking element (24g), as it moves into a hard-position position, passes through a link (52), by which the movement of the blocking element is converted into a rudder movement into the rudder-hard position of the rudder (12). Method according to one of the preceding claims, characterized in that the blocking element (24) is moved from its release position into its hard-layer position and holds there the rudder (12) in the rudder-hard position. Method according to Claim 10 , characterized in that the blocking element (24g) when moving from the release position to the hard position passes through the blocking position. Method according to Claim 10 , characterized in that the hard position of the blocking element (24g) is in relation to a release position against a blocking position. Method according to one of the preceding claims, characterized in that the blocking element (24) presses the rudder (12) from the outside into the rudder hard position when moving into the hard-layer position. Rudder system (26) for a discharge missile (2) with a static system (38) for fixation in the missile (2) and a static system (38) movable rudder (12), characterized in that the static system (38) a blocking element (24) and a drive (32) for moving the blocking element (24), wherein the blocking element (24) and the rudder (12) are arranged relative to each other such that the blocking element (24) mechanically fixes the rudder (12) and the rudder (12) is partially unlocked after movement of the blocking element (24) by the drive (32) and is movable only over part (42) of its rudder deflection area (44) and is fully unlocked after further movement of the blocking element (24) so that it is movable over its entire rudder deflection area (44).

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