RU2532445C1 - Multistage carrier rocket configuration - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to space engineering and can be used in carrier rockets.. Proposed rocket comprises head unit with payload, parallel separable rocket stages with multichamber engines with fuel tanks shaped to torus, tapered tail, short central body at first stage, single trough-like nozzle at second stage, bottom part composed of outer and inner cones composed by outer and inner surfaces of short central body shell and inner surface of single trough-like nozzle shell. Fuel tanks and single trough-like nozzle are arranged inside short central body between first-stage tanks.

EFFECT: decreased bottom resistance, higher specific pulse.

5 cl, 9 dwg

Description

The invention relates to rocket and space technology and is intended for use in the construction of multi-stage launch vehicles (LV), providing the launch of payloads into low Earth orbit. More specifically, the invention relates to multi-stage launch vehicles comprising parallel-mounted rocket units of the first and second stages of the launch vehicle, equipped with multi-chamber liquid-propellant rocket engines (LRE) with self-regulating nozzles of external and internal expansion. The invention can be used in the creation or modernization of multi-stage launch vehicles with marching multi-chamber propulsion systems (DU) with a central body (CT) to reduce bottom resistance in the atmospheric portion of the launch vehicle and improve the altitude characteristics of the launch vehicle (increase in average path impulse along the trajectory) at the flight stage first and second steps.

A multi-stage launch vehicle is known (see patent RU No. 2116941) comprising parallel-mounted rocket blocks of the first and second stages of the launch vehicle, wherein an additional fuel tank connected to its inter-block transition compartment is connected coaxially to the first-stage transition compartment and connected to the fuel compartment of the second-stage launch vehicle rocket through a trunk with a shut-off valve undocked in flight. The rocket blocks of the first and second stages are connected by power communication nodes located on their lateral surfaces. The invention allows to increase the relative mass of the payload and improve the operational performance of a multi-stage launch vehicle [1].

Known multi-stage pH (see patent RU No. 2306242), containing a package of two stages in the form of a Central block of the second stage and four side blocks of the first stage, installed in the planes of stabilization of the PH at an angle to the axis of the block of the second stage, as well as sequentially located the third stage and payload, while the blocks include fuel component tanks, mid-flight and steering rocket engines installed on each block, power units with ball bearings in the upper part of the first stage blocks, the upper power belt on the second stage block and power connections of the tail of the package, and the second-stage block in the zone of the oxidizer tank is cylindrical, and in the zone of the fuel tank has the shape of a truncated cone passing into the cylinder [2].

A known layout of a multi-stage launch vehicle (see RU patent No. 2406660), which contains a package of shared rocket blocks in the form of a central block of the first and second stages, four side blocks of the first stage, a block of the third stage. In the upper parts of the fuel tanks and oxidizer tanks of the side blocks of the first stage in the planes of stabilization of the launch vehicle, on the surfaces facing the central block of the first and second stages, jet nozzles are installed. Each jet nozzle of the fuel tank is equipped with a drain valve. In the tail compartment of the third-stage block, on the frame of the mid-flight engine of the third-stage block, fixed supports are pivotally interacting with the combustion chambers, each of which is movable in one plane parallel to the LV stabilization plane, with the possibility of rotation in the tangential direction around the axis of the fixed support [3].

There are well-known design projects for multi-stage advanced LVs of a heavy and superheavy class of LV type for interplanetary flights [4], using the LV layout according to the package scheme with the parallel arrangement of several side blocks of the first and central block of the second stage of domestic LV: “Volcano” [5], “Yenisei ”And“ Angara-A7 ”[6],“ Rus-MT ”[7],“ Victoria-K ”[8], as well as the US launch vehicle“ Atlas-5 ”[9].

There are well-known designs of multi-stage launch vehicle configurations equipped with marching multi-chamber remote controls with auto-adjustable nozzles of external and internal expansion: for example, in marching remote control systems with first-stage central heating systems in the US Nova-type LV project series [10], as well as in marching remote control systems with central heating systems J-2T- 250k, USA (Rocketdyne project) of the second stage of the Saturn-5 launch vehicle [11].

In well-known designs for the layout of existing and promising multi-stage LVs of medium, heavy and superheavy class [1–9] in longitudinal separation, the first stage consists of several identical missiles operating simultaneously and located around the second stage body symmetrically, so that the resultant thrust forces of the multi-chamber remote control of the first stage are directed along the axis of symmetry of the second. This scheme allows the second-stage engine to operate simultaneously with the first-stage engines, thereby increasing the total thrust of the launch vehicle from the moment of launch at the entire stage of the first-stage flight. With longitudinal separation on the body of the second stage, the PH create power units to which the blocks of the first stage are attached.

The well-known multi-stage launch vehicle configurations with marching multi-chamber remote control systems and large transverse dimensions of rocket blocks and tail engine compartments [1–9] have large bottom drag values on the atmospheric LV flight section, as well as low altitude characteristics (average specific impulse path) of each Remote control of the first and second stages of the launch vehicle.

The occurrence of bottom resistance when using the known multi-stage launch vehicle configurations is explained by the irreversible conversion of part of the kinetic energy of the launch vehicle into heat during flight when a separated flow and vortices form in the tail part of the launch vehicle, and in the supersonic flow when tail shock waves are generated. The outer stream flowing around the body of the PH, having torn off from the surface of the body, is intensively mixed with air located in the stagnant zone behind the bottom of the tail engine compartment, entraining and sucking part of the air from the stagnant zone in which the vacuum occurs.

The aim of the present invention is to reduce the bottom drag with large transverse dimensions of the rocket launcher packs and to improve the altitude characteristics (increase in the average along the flight path of the specific impulse) multi-chamber remote control of the first and second stage of the rocket with a rocket engine.

The purpose of the invention is achieved in that the assembly of the assembled rocket blocks of the first and second stages of the launch vehicle in a parallel circuit contains the basic elements of the structural and layout scheme, consisting of the combined power structure of two marching multi-chamber remote control systems of the first and second stage of the launch vehicle with a rocket engine, which are equipped with a shortened central heating unit with shortened nozzles external and internal expansion, and the bottom of the LV assembled from missile blocks is made in the form of external and internal truncated cones formed by the outer surface of the shell at Orochony DH and the inner mantle surface of the nozzle plate single round or flat shape. In this case, the fuel tanks of the rocket blocks and the single disk nozzle of the second stage of the launch vehicle are located in the inner cavity of the shortened CT between the tanks of the rocket blocks of the first stage of the launch vehicle so that the lower edges of the outer and inner truncated cones coincide in the bottom of the launch vehicle.

The invention is illustrated by drawings in figures 1-9.

Figure 1 presents a side view of the lower part of the known layout of the multi-stage launch vehicle "Volcano" in the embodiment proposed as an example, which was modified using the proposed invention, containing parallel-connected cylindrical missile blocks of the first 1 and second stages of the PH 2.

Figure 2 presents a photograph of a General view of the layout model of the modernized Vulcan design (Fig. 1), equipped as an example with multi-chamber liquid-propellant rocket engines with self-regulating nozzles of external and internal expansion, containing parallel-mounted cylindrical rocket blocks of the first 1 and second stages of the launch vehicle 2, with the third stage 8 and the head part 9.

Figure 3 presents a view A (bottom) of the bottom of the multi-stage launch vehicle in Figures 1 and 2 in the form of a combined design of an external truncated cone (shell CT 3 remote control of the first stage of pH 1) and an internal truncated cone (single poppet nozzle 4 of the second PH stages 2). Combustion chambers 6 and 7 of the remote control of the first 1 and second stage 2 are installed symmetrically to the longitudinal axis of the pH.

The layout of the multi-stage Vulcan launch vehicle modernized using the proposed invention (Figs. 1-3) contains a package of shared rocket blocks in the form of eight side blocks of the first stage of the PH 1, mounted in the planes of stabilization of the PH on the central block of the first and second stages of the PH, with a single multi-chamber remote control with a shortened central body 3 in the first stage of the pH 1 and a single disk nozzle 4 on the second stage of the pH 2.

Figure 4 presents a side view of the general layout of a promising multi-stage launch vehicle in an embodiment proposed as an example, comprising rocket blocks connected in parallel with torus tanks of the first stage of pH 1 and with cylindrical tanks of the second stage of pH 2, with head part 9 and payload 10 under the fairing of the lively shape 11.

In section B - B of the aerodynamic model of the launch vehicle (in the photograph of FIG. 4), a side view ^{of the} _1/4 section ^{of the} launch vehicle structure is shown, obtained using the front and profile cutting planes of the design of the launch vehicle layout of the launch vehicle in Fig. 5.

Figure 5 presents a view A (bottom) of the bottom of the layout of a promising multi-stage launch vehicle in the form of a combined design of the outer truncated cone (round shell CT 3 of the first stage of the launch vehicle 1) and the internal truncated cone (round single dish-shaped nozzle 4 of the remote control of the second runway of the pH 2 ) in Fig. 4, as well as a tapering tail section to reduce drag coefficient in the active atmospheric portion of the PH flight. Combustion chambers 6 and 7 of the remote control of the first 1 and second stage 2 are installed symmetrically to the longitudinal axis of the pH similar to the layout of the pH in figure 3

Figure 6 presents a General side view of the layout of the reusable promising multi-stage launch vehicle in the design variant proposed as an example of the reusable space system (MRKS), containing paralleled salvage cylindrical rocket blocks of the first 1 and second stages of the PH 2, with the head part 9.

In Fig.7 presents a General top view of the layout of MRKS in Fig.6.

On Fig presents a view A (bottom) in Fig.6 and 7.

Fig. 9 is an enlarged image of Fig. 8 of the PH layout A view (bottom), where A is shown for marching multi-chamber remote controls with auto-adjustable nozzles of external and internal expansion, as well as to the bottom of the PH layout in the form of a combined design of an external planar truncated cone (flat pin CT 3 remote control of the first stage of pH 1) and an internal flat truncated cone (flat single disk nozzle 4 remote control of the second stage of pH 2). Combustion chambers 6 and 7 of the remote control of the first 1 and second stage 2 are installed symmetrically to the longitudinal axis of the pH, as well as symmetrically relative to the axis of the flat single disk nozzle 4 and the flat shortened CT 3.

Figure 1-9 shows: the fuel tanks of the rocket blocks of the first stage of the pH 1; fuel tanks of rocket blocks of the second stage of PH 2; a shortened CT 3 of the first stage of PH 1 and a single dish-shaped nozzle 4 (round shape in FIGS. 1-5 and flat shape in FIGS. 6-9) LRE multi-chamber remote control of the second stage PH 2; the lower edge 5 in the bottom of the shortened CT 3 and a single disk nozzle 4 (round in figure 1-5 and flat in figure 6-9); primary shortened nozzles of the LRE 6 combustion chambers in a multi-chamber remote control of the second stage of the PH 2; primary shortened nozzles of the combustion engines LRE 7 in a multi-chamber remote control of the first stage of the launch vehicle 1; upper (third) stage of the launch vehicle (or upper stage) 8; head unit 9 with payload 10 and fairing 11.

Figure 6-9 shows the elements of MRKS: a direct wing 12 in the launch configuration, which is located along the block body of the first stage of the PH 1; an upper keel 13 for ensuring road stability, controllability and balancing with respect to the vertical axis of the block and a horizontal stabilizer 16 for ensuring the longitudinal stability of the rescue block of the first stage of PH 1; wing 14 and the upper keel 15 of the reusable block of the second stage of the PH 2.

The solution to this problem is achieved by the fact that:

1. The layout of the multi-stage launcher (Figs. 1-9) contains a head unit 9 with a payload 10 and a fairing 11 connected by power communication units to parallel separated rocket blocks of stages 1 and 2, equipped with multi-chamber remote control with fuel tanks, shortened CT 3 on the first stage of PH 1 and a single disk nozzle 4 on the second stage of PH 2, characterized in that the bottom of the PH is made in the form of external and internal truncated cones (pins) of round or flat shape, formed by the outer surface of the conical shell or pl of the shortened CT 3 shape and the inner surface of the cone of a flat or flat shape of a single disk nozzle 4, the fuel tanks and a single disk nozzle of the second stage PH 2 are located in the inner cavity of the shortened CT 3 between the tanks of the first stage PH 1 so that the lower part of the PH the edges of the outer and inner truncated cones 5 coincide, and both shells have the same round or flat shapes of conical structural elements of a shortened CT 3 and a single disk nozzle.

2. The layout of the multi-stage launch vehicle (Fig.6-9) according to claim 1, characterized in that the bottom of the launch vehicle is made in the form of external and internal truncated cones of a flat shape (Fig.8-7), and the internal cavity of a shortened central heating unit and the internal space between the blocks of the first stage, PH 1 is made in the profile of a flat pin TsTZ, and both shells have a flat pin shape of conical structural elements of a shortened CT 3 and a single disk nozzle 6.

3. The layout of the multi-stage launch vehicle (Figs. 4 and 5) according to claim 1, characterized in that the rocket units of the first stage of the launch vehicle 1 are equipped with fuel tanks in the shape of a torus, inside which the missile units of the second stage 2 are located, the bottom of the launch vehicle (Fig. 5 ) is made in the form of outer and inner truncated round cones, and the inner cavity of the shortened CT 3 and rocket blocks of the second stage 2 are located inside the torus tanks of the first stage PH 1 coaxially to the round pin of CT 3, and both shells have a round shape of the pin of conical structural elements of the shortened CT 3 and dinogo poppet nozzle 6.

4. The layout of the multi-stage launch vehicle (Fig.6-9) according to claim 2, characterized in that the two outer and one central inner truncated cones of a flat shape in the bottom of the launch vehicle (Fig.7) are made in the form of components of the reusable elements of multi-chamber reusable rocket blocks of the first 1 and second 2 stages equipped with wings 12 and 14 for returning to the ground using the aerodynamic quality of rocket blocks 1 and 2.

5. The layout of the multi-stage launch vehicle (Figs. 4 and 5) according to claim 3, characterized in that the outer truncated cone of the central-type CT 3 pin in the bottom of the launch vehicle (Fig. 5) is aligned with the longitudinal axis of the first stage rocket unit 1, having tapering conical tail section to stabilize passive flight when returning to the ground using aerodynamic quality after separation from the second stage of PH 2 and flight in the atmosphere with a pressure center above the center of mass of the rocket block of the first stage 1, which is shifted to the lower edge of the CT3 pin.

The layout of the multi-stage launch vehicle operates in the following sequence.

In the initial position, the launch vehicle charged with rocket fuel components (CRT) is in a vertical position in the launch system.

The launch of marching multi-chamber remote control missile blocks of the first and second stages of launch vehicles is carried out from the Earth. The proposed starting scheme provides the maximum initial thrust-to-weight ratio and the greatest likelihood of a successful start, as it allows you to stop starting by turning off all engines or to restart if an emergency shutdown of one of the engines occurs or deviations in the remote control operation are noticed.

The launch of the launch vehicle is carried out without being held on the starting device. After reaching the total thrust of the remote control equal to the mass of the launch vehicle, the launch of the launch vehicle begins.

The remote control of the first stage creates the main external gas flow from the primary shortened combustion chambers of the liquid propellant rocket engine 7 with the shortened central heating unit 3 of the first stage of the PH 1, and the remote control of the second stage creates the internal gas flow from the primary shortened combustion chambers of the liquid propellant rocket engine 6 of a single poppet nozzle 4 of the multi-chamber remote control of the second stage of the ph 2. Each of the two flows after separation from the lower edge of the CT 3 and a single disk nozzle 4 provides a reversal of the total gas flow strictly along the vertical axis of symmetry of the entire layout of the two-stage launch vehicle. The total thrust vector of the remote control of the first and second stage of the launch vehicle is on the same axis as the flight speed vector of the launch vehicle.

In the bottom part of the LV, made in the form of external and internal truncated cones, the profiles of the outer surface of the shell of a shortened CT 3 and the inner surface of the shell of a single disk nozzle 4 provide the calculated mode of auto-regulation during acceleration of the external and internal gas flows in a composite nozzle block with a shortened CTZ.

This forms the external and internal annular flows of gases flowing from the combustion chambers of the liquid propellant rocket engine with a central heating unit 3 and a single disk nozzle 4 having round shapes (Figs. 1-5). From the combustion chambers of the liquid propellant rocket engine with a central heating unit 3 and a single disk nozzle 4 having a flat shape (FIGS. 6–9), the outgoing two external and two internal flows will create four flat gas flows that are symmetrical to the axis of the LV velocity vector.

After the launch of the launch, the main engines of the second-stage unit can switch to various modes from 70% to 100% of the nominal thrust. These modes will save fuel of the second stage and provide an increase in the mass of the output payload.

Flight control is provided by the throttling of symmetrically located remote control chambers of the first and second stages. Combustion chambers are stationary. The control moments in the pitch and yaw planes are created by throttling and forcing the opposing engines. The control over the roll thrust channel is carried out by small thrust steering engines located in pairs by nozzles in opposite directions on the frame of the engine compartment.

To limit the velocity head in the flight section of the first stage of the launch vehicle, it is possible to throttle simultaneously the combustion chambers of the remote control of the first and second stages in the zone of passage of the maximum velocity stream.

At the end of the multi-chamber remote control of the first stage of the rocket launcher, the combustion chambers of the rocket engine 7 with a shortened CT 3 are turned off and missile units 1 are separated from the second stage of the rocket launcher. The multi-chamber remote control of the second stage of the PH 2 continues auto-regulation and operation in the single disc nozzle 4 mode.

The rocket block of the first stage of the launch vehicle 1 has a speed at the moment of separation from the central unit of the second stage 2 of about 1.9 km / s, close to the same speed of movement of the side blocks in the launch vehicle "Energy" (1.8 km / s), which makes it possible their salvation [5].

After the set speed of the launch vehicle is set, the remote control of the second stage 2 is completely turned off.

The use of the invention in rocket technology allows you to:

1. To ensure an increase in the relative mass of the payload in promising projects of multi-stage launch vehicles and an improvement in their operational characteristics compared to the prototype by reducing the bottom drag and improving the altitude characteristics of multi-chamber remote control.

2. To reduce the loss of total thrust of multi-chamber remote control at large transverse dimensions of existing LV projects with parallel arrangement of rocket blocks of the first and second stages by reducing bottom drag in the atmospheric phase of the LV flight. For example, if you propose to implement the invention in projects for the development of promising domestic heavy and superheavy launch vehicles of the Yenisei and Angara-A7 type [6], Rus-MT [7], Victoria-K [8], and also the LV USA "Atlas-5" [9].

3. Improve due to the auto-regulation of two supersonic gas flows (external flow from short-circuited liquid propellant combustion chambers and internal flow from a single disk nozzle) altitude characteristics (increase the average specific impulse along the trajectory) the liquid propellant rocket engine of each of the multi-chamber remote control systems of existing and promising LV projects with parallel the location of the rocket blocks of the first and second stages with a single nozzle block of a multi-chamber remote control at the stage of their joint operation in the LV flight.

4. To provide the possibility of multiple use of salvage elements of multi-chamber remote control from reusable missile blocks of the first and second stages, equipped with wings for returning to the ground using aerodynamic quality missile blocks, equipped with a two-part aerodynamic nozzle with a flat composite shortened first stage CT and a single flat disk nozzle in the second stage.

5. To provide the possibility of multiple use of the salvage elements of the multi-chamber remote control of a reusable first stage rocket block, equipped to return to the ground using the aerodynamic quality of the rocket block, equipped with torus tanks and an aerodynamic nozzle with a round shortened central heating unit, having a tapered tail section for stabilization and stability of the passive flight when returning to earth after separation from the second stage of the launch vehicle and forward flight in the atmosphere of the central heating with a pressure center The second one is shifted to the lower edge of the central heating pin above the center of mass of the rocket block of the first stage.

Information sources

1. Multistage pH (patent RU№2116941), 08/10/1998.

2. Multistage pH (patent RU No. 2306242), 01/10/2006.

3. The layout of a multi-stage pH (patent RU No. 2406660), 12.20.2010.

4. I. Black. Boosters to return to the moon. "Cosmonautics News". No. 01, 2006.

5. B.I. Gubanov. “The triumph and tragedy of Energy. Reflections of the chief designer. N. Novgorod: ed. NIER, 1998, on the website http://vvwvv.buran.ru/htm/gubanov.htm

6. The family of Angara launch vehicles on the website of the FSUE GKNPTS named after M.V. Khrunicheva ”) http://www.khrunichev.ru/main.php?id=44

7. Heavy carrier rocket "Rus-M". Missile production in Russia. Aviation and astronautics, on the website http://www.nemiga.info/discovery/rossiya/raketa-rus.htm

8. V. Degtyar et al. "Victoria-K" the third coming of the superheavy? "Cosmonautics News". No. 05, 2006.

9. Atlas-5 launch vehicle, article at http://space.skyrocket.de/doc_lau/atlas-5.htm

10. Encyclopedia of Astronautics, Encyclopedia Astronautica, Nova article at http://www.astronautix.com/lvs/nova.htm

11. O'Leary R.A., Beck J. E. Nozzle Design article in Pratt & Whitney Rocketdyne's engineering journal of power technology, 1992, article at http://www.pwrengineering.com/articles/nozzledesign.htm

Claims (5)

1. The layout of a multi-stage launch vehicle containing a head unit with a payload, connected by power communication nodes with parallel separated rocket units of stages equipped with multi-chamber propulsion systems with fuel tanks, a shortened central body at the first stage of the launch vehicle and a single disk nozzle to the second stages of the launch vehicle, characterized in that the bottom of the launch vehicle is made in the form of external and internal truncated cones formed by the outer surface the shell of the shortened central body and the inner surface of the shell of a single disk nozzle, and the fuel tanks and the single disk nozzle of the second stage of the launch vehicle are located in the internal cavity of the shortened central body between the tanks of the first stage of the launch vehicle so that the lower part of the launch vehicle the edges of the outer and inner truncated cones coincide. 2. The layout of the multi-stage launch vehicle according to claim 1, characterized in that the bottom of the launch vehicle is made in the form of external and internal truncated cones of a flat shape, and the internal cavity of the shortened central body and the internal space between the blocks of the first stage of the launch vehicle profile of the flat pin of the central body. 3. The layout of the multi-stage launch vehicle according to claim 1, characterized in that the rocket blocks of the first stage of the launch vehicle are equipped with fuel tanks in the shape of a torus, inside which the rocket blocks of the second stage are placed, the bottom of the launch vehicle is made in the form of external and internal truncated round cones, and the inner cavity of the shortened central body and the second stage rocket blocks are located inside the torus tanks of the first stage of the launch vehicle coaxially to the round pin of the central body. 4. The layout of the multi-stage launch vehicle according to claim 2, characterized in that the outer and central inner truncated cones of a flat shape in the bottom of the launch vehicle are made in the form of components of salvage elements of multi-chamber propulsion systems of reusable rocket blocks of the first and second stages equipped with wings to return to earth using the aerodynamic quality of rocket blocks. 5. The layout of the multi-stage launch vehicle according to claim 3, characterized in that the outer truncated cone of the pin of the central body of a circular shape in the bottom of the launch vehicle is made coaxially with the longitudinal axis of the first stage rocket unit having a tapered tail portion of the conical shape to stabilize passive flight when returning to earth using aerodynamic quality after separation from the second stage of the launch vehicle and flight in the atmosphere with a pressure center above the center of mass of the first stage rocket unit, which offset to the lower edge of the pin of the Central body.

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