RU2459971C1 - Carrier rocket, liquid-propellant rocket engine and roll nozzle block - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: carrier rocket includes central unit comprising of housing, oxidiser and fuel tanks inside housings, and art least two side rocket units connected to it, which also have oxidiser and fuel tanks inside housing, at least one liquid-propellant rocket engine in each rocket package and roll nozzle block, each of which contains two opposite roll nozzles; according to the invention, roll nozzle blocks are installed on external surface of housing of side rocket packages, which is located at some distance from carrier rocket axis. Even number of side rocket packages has been used; roll nozzle blocks are installed on two diametrically opposite side rocket packages. There can be used odd number of side rocket packages, and roll nozzle blocks are installed on all side rocket packages. Liquid-propellant engine comprises power frame, combustion chamber having a head, cylindrical part and muzzle, which is fixed on power frame by means of suspension assembly; provides the possibility of rolling in two planes by means of actuators attached to power ring provided on combustion chamber; gas generator and turbine-pump unit containing in its turn turbine, oxidiser pump, fuel pump, gas line connecting the turbine outlet to combustion chamber head through suspension assembly; according to the invention the roll nozzles are grouped into roll nozzle blocks in pairs and installed on lower power ring installed in lower part of nozzle and connected to nozzle section; to roll nozzles there connected through three-way gas and fuel valves are gas-generator gas supply pipelines; the other ends of which are connected first by means of gas extraction pipeline and fuel pipelines; in addition, roll nozzle blocks are fixed on lower power ring by means of two inclined rods. Roll nozzle block containing two roll nozzles installed in opposite direction and combined into an assembly containing common housing; according to the invention a pair of roll nozzles is equipped with three-way gas and fuel valves installed between roll nozzles and having a common actuator. All roll nozzles are equipped with ignition devices connected by means of communication lines to a control unit. Common housing is equipped with fastening elements attaching the common housing to lower power ring of carrier rocket.

EFFECT: improving control reliability of thrust vector of liquid-propellant engine and roll control reliability of rocket.

7 cl, 16 dwg

Description

The group of inventions relates to rocket technology, specifically to rockets and liquid rocket engines, made in a closed circuit, with afterburning of gas-generating gas, and is intended to control the thrust vector of the engine.

Known liquid rocket engine according to the patent of the Russian Federation for invention No. 2095607, intended for use as part of space booster blocks, stages of rocket launchers and as a marching engine of spacecraft, which includes a combustion chamber with a regenerative cooling path, component feed pumps - fuel and oxidizer with a turbine on one shaft into which the capacitor is inserted. The condenser outlet through the refrigerant line is connected to the entrance to the combustion chamber and to the entrance to the regenerative cooling path of the combustion chamber.

The disadvantage of this engine is the lack of thrust vector control.

Known LRE according to the patent of the Russian Federation for the invention No. 2190114, IPC 7 F02K 9/48, publ. 09/27/2002 This LPRE includes a combustion chamber with a regenerative cooling path, a TNA turbopump unit with oxidizer and fuel pumps, the output lines of which are connected to the head of the combustion chamber, the main turbine and the drive circuit of the main turbine. The main turbine drive circuit includes a fuel pump and a regenerative cooling path of the combustion chamber connected in series with each other and connected to the main turbine inlet. The exit from the turbine TNA is connected to the input of the second stage of the fuel pump.

This engine has a significant drawback. Bypassing the fuel combustion chamber heated in the regenerative cooling path to the entrance to the second stage of the fuel pump will lead to cavitation. Most LREs use fuel components such that the oxidizer consumption is almost always greater than the fuel consumption. Therefore, for powerful rocket engines with great thrust and high pressure in the combustion chamber, this scheme is not acceptable, because fuel consumption will not be enough to cool the combustion chamber and drive the main turbine. In addition, the LRE launch system, the ignition system of the fuel components and the LRE shutdown system and its cleaning of fuel residues in the regenerative cooling path of the combustion chamber have not been developed.

Known liquid rocket engine according to the patent of the Russian Federation for the invention No. 2232915, publ. September 10, 2003, which contains a chamber, a turbopump unit, a gas generator, a launch system, means for igniting fuel components and fuel lines. The output of the oxidizer pump is connected to the inlet of the gas generator. The output of the first stage of the fuel pump is connected to the channels of regenerative cooling of the chamber and to the mixing head. The output of the second stage of the fuel pump is connected to an electric flow regulator.

The disadvantage is that the engine does not have a thrust vector control system and roll control.

Known liquid rocket engine and TNA according to the patent of the Russian Federation for the invention No. 2161263, prototype.

This engine contains a power frame, a combustion chamber made with the possibility of swinging in two planes, a gas generator and a turbopump unit, coupled to the gas generator by means of a gas duct, which in turn contains a turbine, an oxidizer pump, a fuel pump and an additional fuel pump, a gas duct connecting the turbine exit with a combustion chamber, and a rocker assembly of the rocket engine combustion chamber installed between the gas duct and the combustion chamber, more precisely, the head of the combustion chamber. This unit is made in the form of a bellows and a universal joint, which together provide the swing of the combustion chamber and sealing the supply of gas-generating gas, which has high pressure and temperature. In addition, a bellows cooling system is provided, since its performance under such extreme conditions is in doubt.

The turbopump assembly comprises a turbine with an impeller and oxidizer pumps, fuel pumps and an additional fuel pump installed coaxially with the pump.

The disadvantages of this engine and the suspension unit of the combustion chamber included in its composition are: low unreliability of the suspension unit of the combustion chamber of the rocket engine due to the presence of a large number of parts, low strength of thin-walled bellows operating at high pressure and temperature. Gimbal bearings, transmitting the thrust of the combustion chamber, reaching 200 ... 1000 tf, also work at high temperatures (from 500 to 800 ° C), while the grease burns out, the bearings are destroyed, the thrust vector control is difficult.

The use for cooling this unit of fuel, intended for feeding into the combustion chamber, not only complicates the design of this unit and the engine as a whole, but also makes its operation extremely dangerous, since when the bellows breaks, the fuel and gas-generating gas containing excess oxidizer will come into contact that will inevitably lead to a fire in the engine compartment of the rocket and the cessation of fuel supply to the combustion chamber.

The thrust vector control is unreliable, and the roll angle control is completely absent.

The objective of the invention is to ensure the reliability of the thrust vector control of the rocket engine and the reliability of rocket control over the roll.

The solution to this problem was achieved in that in a launch vehicle containing a central unit having a body, oxidizer and fuel tanks inside the bodies, and at least two side rocket blocks connected to it, also having oxidizer and fuel tanks inside the bodies, at least , one liquid rocket engine in each rocket unit and the roll nozzle blocks containing two opposed roll nozzles, according to the invention, the roll nozzle blocks are mounted on the housing outer surface separated from the axis of the launch vehicle Side rocket blocks. An even number of side rocket blocks were used, and the roll nozzle blocks were mounted on two diametrically opposite side rocket blocks. An odd number of side rocket blocks can be applied, and roll nozzle blocks are mounted on all side rocket blocks.

The solution to this problem was achieved by the fact that in a liquid propellant rocket engine containing a power frame, a combustion chamber having a head, a cylindrical part and a nozzle, which is mounted on the power frame using a suspension unit that provides the ability to swing in two planes by means of drives attached to the power ring made on the combustion chamber, a gas generator and a turbopump assembly, which in turn contains a turbine, an oxidizer pump, a fuel pump, a gas duct connecting the outlet of the turbine to the head of the combustion chamber through the suspension unit, according to the invention, the nozzles of the bank are grouped in blocks of nozzles of the bank in pairs and are mounted on the lower power ring installed in the lower part of the nozzle and connected to the nozzle section, respectively, gas supply gas supply pipelines are connected to the nozzles of the bank through three-way gas and fuel valves, others the ends of which are connected first by a gas extraction pipe and fuel pipelines, while the roll nozzle blocks are fixed to the lower power ring using two inclined rods.

The solution to this problem was achieved by the fact that in a block of roll nozzles containing two roll nozzles installed opposite and combined into one assembly containing a common housing, according to the invention, a pair of roll nozzles is equipped with three-way gas and fuel valves installed between the roll nozzles and having a common drive. All roll nozzles are equipped with ignition devices connected by communication lines to the control unit. The common housing is equipped with fasteners connecting the common housing with the lower power ring of the launch vehicle.

The invention is illustrated in figure 1 ... 15, where

figure 1 shows a diagram of a launch vehicle,

figure 2 shows the layout of the liquid rocket engine in the side rocket unit,

figure 3 ... 6 shows a view of figure 1,

7 and 8 shows a variant of the launch vehicle with detachable side rocket blocks,

in Fig.9 ... 12 shows the layout of the blocks of nozzles of the roll for the launch vehicle with detachable rocket blocks,

Fig.13 shows a diagram of a liquid propellant rocket engine,

Fig.14 shows the suspension unit,

on Fig shows the design of the block nozzle roll,

in Fig.16 shows a section bB,

The carrier rocket (Fig. 1 ... 15) contains a central unit 1 having a body 2, an oxidizer tank 3, a fuel tank 4 and a liquid rocket engine 5, and several (at least two) side rocket blocks 6 containing a housing 7, an oxidizer tank 8 , fuel tank 9. All liquid rocket engines 5 can be made of the same design. The side blocks 6 can be applied either an even number (figure 3 and 5), or odd (figure 4 and 7).

You can use the scheme of the launch vehicle with detachable side rocket blocks 6, which are attached to the Central rocket block by the nodes of the connection 10 (Fig.7 and 8). The connection nodes 10 are made with the possibility of undocking in flight, for example, pyro-bolts are used. On the launch vehicle on the side rocket blocks 6, at least two blocks of roll nozzles 11 are installed.

In this case, the installation arrangement of the nozzle blocks of the roll 11 can be performed as indicated in Figs. 9 ... 12, i.e. with an even number of side rocket blocks 6, only two blocks of roll nozzles 11 can be used, and with an odd number of blocks of roll nozzles 11 is equal to the number of side rocket blocks 6.

The liquid rocket engine 5 (FIG. 2) comprises a combustion chamber 12, capable of swinging in two planes, a gas generator 13 and a turbopump assembly 14 connected to the combustion chamber 12 by means of a gas duct 15, which in turn contains a turbine 16, an oxidizer pump 17, a pump fuel 18. Turbopump assembly 14 may include an additional fuel pump 19.

The output of the fuel pump 18 is connected by a pipe 20 to the entrance to the additional fuel pump 19 (if any). The combustion chamber 12 comprises a head 21, a cylindrical part 22 and a nozzle 23. The gas generator 13 is mounted on the power frame 29 using a hinge 24, and the TNA 14 is mounted using two articulated rods 25. Between the gas duct 15 and the combustion chamber 12, more precisely, its head 21, the suspension assembly 26 of the combustion chamber 12 is installed. It provides the swing of the combustion chamber 12 in one plane relative to the center of the suspension assembly 26 for controlling the thrust vector R, in order to control the launch vehicle in pitch and yaw angles.

For this, each liquid-propellant rocket engine 5 contains actuators 27, made, for example, in the form of hydraulic cylinders 28, attached to the power frame 29, and having rods 30. On the combustion chamber 12, for example, on its cylindrical part 22, the main power ring 31 is made, to which the rods 30 of the actuators 27 are pivotally attached. The actuators 27 are used to control the launch vehicle at pitch and yaw angles.

A possible pneumohydraulic scheme of the liquid propellant rocket engine is shown in Fig. 13 and contains a fuel pipe 32 connected at one end to the outlet of the fuel pump 18, containing a start-off valve 33 and a bellows 34, the output of this pipe being connected to the main manifold 35 of the combustion chamber 12. The output from the oxidizer pump 17 the oxidizer pipe 36 containing the start-off valve of the oxidizer 37 is connected to the gas generator 13. Also, the output from the additional fuel pump 19 the fuel line 38 containing the start-off valve of the fuel 39 is connected to at least one ignition device 40 is installed on the gas generator 13 and on the combustion chamber 12.

The engine is equipped with a control unit 41, which is connected by electrical connections 42 to the ignition devices 40 and to the shut-off valves 33, 37 and 39.

A feature of the engine (Figs. 1, 2, and 13) is that the TNA 14 is rigidly fixed to the power frame 29 with at least three articulated rods 25, and the combustion chamber 12 has the ability to rotate relative to the center of the suspension assembly 26 in one plane.

The suspension assembly 26 of the combustion chamber 12 of the rocket engine (Fig. 14) contains two parts: the fixed 43 and the movable 44. The fixed part 43 is rigidly connected to the gas duct 15, and the movable part 44 is rigidly connected to the head 21 of the combustion chamber 12 due to the fact that both parts form a spherical joint 45 made hollow inside.

The roll angle control system (FIGS. 1 ... 16) contains at least two blocks of roll nozzles 11 installed on the housings 7. Blocks of the roll nozzles 11 (FIGS. 15 and 16) contain two opposite mounted roll nozzles 46. Blocks of the roll nozzles 11 contain a common housing 47 with fasteners 48 and are attached to the lower power rings 49 installed inside the housings 7 of the side rocket blocks 6. The nozzle blocks of the bank 11 contain nozzles 50 to which the gas supply gas supply pipelines 51 are connected, the other ends of which are connected to the gas duct 15. In the central part of the blo For the nozzles of the bank 11, a three-way gas valve 52 and a three-way fuel valve 53 are installed, to which a fuel pipe 54 connected from the main manifold 35 is connected. A three-way valves 52 and 53 have a common drive 55 on each block of bank nozzles 11. Thus, every two roll nozzles 46, three-way valves 52 and 53 and a common drive 55 form one assembly: a block of nozzles of roll 11.

The nozzle roll 46 (Fig and 16) is made with two walls 56 and 57 and collectors 58 for the passage of cooling fuel. In each nozzle of the roll 46, fuel nozzles 59, an oxidizer 60, and an ignition device 61 are installed. The collectors 58 are connected to a three-way fuel valve 53 by pipelines 62 for transferring fuel. Roll nozzles 46 have uncooled nozzles 63

The gas supply gas supply pipelines 51 contain bellows 64 (Fig. 13) to prevent deformation of the gas supply gas pipelines 51 when the combustion chambers swing 12. The power frames 29 are mounted on the based power rings 65.

The engine starts as follows.

In the initial position, all engine valves are closed. When starting a liquid propellant liquid propellant rocket engine from a control unit 41 through an electric communication channel 42, a command is issued to the rocket valves of the oxidizer and fuel (rocket valves in FIGS. 1 ... 15 are not shown). After priming the oxidizer 17 and fuel 18 pumps, the shut-off valves 33, 37 and 39 (Fig. 13) are installed, installed behind the oxidizer 17, after the fuel 18 and after the additional fuel 19, the oxidizing agent and the fuel enter the gas generator 13, where they ignite aid of the igniter 40. Gas-generating gas and fuel is supplied to the combustion chamber 12. The fuel cools the combustion chamber 12, passing through the gap, between the shells of its nozzle 23 and the cylindrical part 22 forming the regenerative cooling path (Fig. 13), enters the inner 12 smallness combustion chamber for afterburning gasification gas coming from the gasifier 13. The ignition of these components is also carried ignition device 40 installed on the combustor 12

After starting the turbopump assembly 14 (Fig. 13), the gas-generating gas is supplied from the gas-generator 13 to the turbine 16, the TNA rotor is untwisted (the rotor is not shown in Figs. 1 ... 15), and the pressure at the pump outputs 17, 18 and 19 increases. Next, through the gas duct 15 and through the suspension assembly 26, the gas-generating gas is supplied to the head 21 of the combustion chamber 12. A part of the gas-generating gas is taken through the gas sampling pipe 51 and then through the pipe 50 and through three-way valves 52 enters the nozzle blocks of the bank 11.

To control the thrust vector R using the drive 27, acting on the power ring 31 by the stem 30, the combustion chamber 12 is rotated relative to the center point of the suspension assembly 26 by an angle of 5 ... 7 °. The direction of the thrust vector R ₁ deviates relative to the initial position R _{1 of the} longitudinal axis of symmetry of the combustion chamber 12 and relative to the launch vehicle on which this engine 5 is mounted.

To control the launch vehicle, on which liquid-propellant rocket engines 5 are installed, a command is sent from the control unit 41 (FIG. 2) to the actuators 55 (FIG. 15), and one roll nozzle 46 from each pair is turned on, and their jet thrust creates a torque that is transmitted through the lower power ring 49 first to the nozzle 23, then to the power frame 29 and then to the main power ring (Fig.13) and to the housing 7 of the side rocket block 6 of the launch vehicle.

After the separation of the nodes of the connection 10 (Fig.8), the side rocket blocks 6 are discarded. Further, the flight is performed only by the central missile unit 1, while the roll control is carried out by the nozzle blocks of the roll 11 mounted on the body 2.

The application of the invention allowed:

1) to provide reliable control of the thrust vector of the rocket engine and control of the launch rocket along the roll angle through the use of two blocks of roll nozzles containing two opposed roll nozzles and the rational mounting of their bodies on the rocket on the lower power rings;

2) significantly increase the reliability of the rocket control system by roll through the use of two three-way valves: gas and fuel and a common drive for them. This design prevents the inclusion of one of the nozzles of the roll, for example, due to a failure of the start-off fuel valve.

Claims (7)

1. A booster rocket containing a central unit having a housing, oxidizer and fuel tanks inside the buildings, and at least two side rocket blocks connected to it, also having oxidizer and fuel tanks inside the buildings, at least one liquid rocket engine in each missile block, and roll nozzle blocks containing two opposed roll nozzles, characterized in that the roll nozzle blocks are mounted on the outer surface of the side rocket block bodies, which is remote from the launch vehicle axis. 2. The launch vehicle according to claim 1, characterized in that an even number of side rocket blocks are used, and the roll nozzle blocks are mounted on two diametrically opposite side rocket blocks. 3. The launch vehicle according to claim 1, characterized in that an odd number of side rocket blocks are used, and the roll nozzle blocks are installed on all side rocket blocks. 4. A liquid rocket engine containing a power frame, a combustion chamber having a head, a cylindrical part and a nozzle, which is mounted on the power frame using a suspension unit that provides the ability to swing in two planes by means of actuators attached to a power ring made on the combustion chamber, a gas generator and a turbopump assembly, which in turn contains a turbine, an oxidizer pump, a fuel pump, a gas duct connecting the outlet of the turbine to the head of the combustion chamber through a suspension unit, characterized in that bank rolls are grouped in roll nozzle blocks in pairs and mounted on the lower power ring mounted in the lower part of the nozzle and connected to the nozzle exit, to the roll nozzles through three-way gas and fuel valves, respectively, gas-generating gas supply pipelines are connected, the other ends of which are connected first by a gas sampling pipeline and fuel pipelines, while the roll nozzle blocks are fixed to the lower power ring using two inclined rods. 5. The block of nozzles of the roll, containing two nozzles of the roll installed opposite and combined into one node containing a common housing, characterized in that the pair of nozzles of the roll is equipped with three-way gas and fuel valves installed between the nozzles of the roll and having a common drive. 6. The roll nozzle block according to claim 5, characterized in that all roll nozzles are equipped with ignition devices connected by communication lines to the control unit. 7. The roll nozzle block according to claim 5, characterized in that the common housing is equipped with fasteners connecting the common housing with the lower power ring of the launch vehicle.

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