RU2380651C1 - Multistaged air-defense missile - Google Patents

Abstract

FIELD: defense technology.

SUBSTANCE: multistaged air-defense missile comprises at least two stages with at least one liquid propellant rocket engine at lower stage (LPRE). Fuel and oxidant tanks are connected to LPRE. Controlled aerodynamic rudders and wings are installed on upper stage and at least one solid propellant rocket engine. Solid propellant boosters with solid propellant rocket engines are connected to lower stage parallel to its axis. Each LPRE comprises combustion chamber with system of regenerative cooling, turbopump set and gas generator. Turbopump set comprises oxidant and fuel pumps and main and startup turbine. Gas generator is installed coaxially with turbopump set. Outlet of fuel pump is connected to inlet of regenerative cooling system and to inlet of gas generator, outlet of oxidant pump is connected to the second inlet of gas generator, outlets of gas generator and system of regenerative cooling are connected to cylindrical portion of combustion chamber.

EFFECT: improved technical characteristics of rocket in wide range of flight modes at various height.

2 dwg

Description

The invention relates to rocket technology, specifically anti-aircraft missiles with liquid rocket and solid fuel engines.

Liquid propellant rocket engines are often used as propulsion engines for rockets; they are easier to regulate than solid propellants. But solid propellant rocket engines have several advantages: they take less time to start, they are simpler in design and cheaper.

Known cruise missile according to the patent of the Russian Federation for invention No. 2225975, a prototype, is located in the cavity of the marching stage, which contains its own nose cone, flight control and guidance system for the target, warhead and additional solid fuel engine. The marching stage can be docked with a turbojet engine by means of a docking and separation device. According to the method of using the rocket before the separation of the march and combat stages include a flight control system and guidance on the target march stage. After the separation of the stages, the solid propellant engine of the march stage is started.

Disadvantages: short range, low flight speed and the inability to use a rocket at night. In addition, the control of the missile and its guidance on the target is very difficult, because the warhead contains only a solid fuel engine, the regulation of which is difficult. The control system is included before the separation of the march and combat stages. Maneuvering at supersonic speeds is technically difficult.

The task of creating the invention: improving the technical characteristics of the rocket, reducing its weight and increasing flight range.

The solution of these problems was achieved in a multi-stage anti-aircraft missile containing at least two missile stages with at least one liquid rocket engine in the lower stage and fuel and oxidizer tanks connected by low-pressure pipelines with liquid rocket engines, characterized in that the upper stage is controlled aerodynamic rudders and wings and at least one solid fuel rocket engine, solid fuel accelerators are connected to the lower rocket stage parallel to its axis solid fuel rocket engines, each liquid rocket engine contains a combustion chamber with a regenerative cooling system, and a turbopump assembly, in turn containing oxidizer and fuel pumps and a main and starting turbine, a gas generator installed coaxially with the turbopump assembly, while leaving the pump the fuel is connected to the entrance to the regenerative cooling system and to the entrance to the gas generator, the outlet from the oxidizer pump is connected to the second entrance to the gas generator, the exits from the gas generator and regenerative cooling threads are connected to the cylindrical portion of the combustion chamber.

The invention is illustrated by drawings, where

figure 1 shows a diagram of an anti-aircraft missile,

figure 2 shows a diagram of a liquid rocket engine.

Multistage anti-aircraft missile (figure 1) may contain at least two missile stages. The description is made on the example of a two-stage rocket. A multi-stage anti-aircraft missile contains two missile stages, the lower (first) 1 and upper (second) 2 connected by a connecting farm 3, the head of the rocket 4, in which an explosive device 5 with a fuse 6 is installed. Solid fuel boosters 7 are attached to the lower rocket stage 1 parallel to its axis with rocket engines of solid fuel 8, rotary aerodynamic rudders 9 with actuators 10 and two or four wings 11 are installed on the upper rocket stage 2; At least one liquid fluid is installed inside the lower rocket stage 1 rocket engine 12, comprising a combustion chamber 13 and agrega turbopump 14. Inside the upper stage rocket 2 mounted solid fuel rocket motor 15 having a combustion chamber 16 and a nozzle 17.

Inside the bodies of the lower rocket stage 1, a fuel tank 18 and an oxidizer tank 19. A fuel tank 19 is connected by a fuel pipe 20 containing a fuel valve 21 to a lower stage engine 12. An oxidizer tank 19 is connected by a low pressure oxidizer pipe 22 containing an oxidizer valve 23 to the first engine steps 12.

On the upper rocket stage 2, a control system 24 is installed, connected by electrical connections 25 to the valves and regulators of the engines 12, to the engine 15 and the actuators 10.

The liquid rocket engine 12 and the lower stages 1 can have any design. In the future, the design shows the most optimal design of a liquid-propellant rocket engine 12 (figure 2). This liquid rocket engine 12 contains a combustion chamber 13 and a turbopump assembly TNA - 14.

The combustion chamber 13 comprises a head 26 of the combustion chamber 13, a cylindrical part 27, and a supersonic nozzle 28. The turbo-pumping unit TNA - 14 (Fig. 2), in turn, comprises an oxidizer pump 29, a fuel pump 30, and a starting turbine 31 installed in the housing 32 , the main turbine 33, made in the upper part of the turbopump unit 14.

The gas generator 34 is mounted above the main turbine 33 coaxially with the turbopump unit 14 and has a cavity “A” and “B” in the upper part of the cavity. The housing 32 may be common to the turbopump assembly 14 and the gas generator 34 and may have the necessary connectors for assembly. The supersonic nozzle 28 is made of two shells 35 and 36 with a gap "B", which forms a regenerative cooling system. A fuel manifold 37 is mounted on the outer surface of the combustion chamber 13 at its lower part. A main fuel pipe 38 is connected to the fuel manifold 37, in which the fuel shut-off valve 39 is installed. An additional fuel pipe 40 is connected to the outlet of the fuel pump 30, in which the regulator is installed flow 41 with actuator 42, a fuel valve 43 and which is connected to the cavity "B" of the gas generator 34. The output from the oxidizer pump 29 by the oxidizer pipe 44 through the shut-off valve of the oxidizer 45 is also connected to the gas generator 3 4, more precisely with the cavity "A". In the upper part of the gas generator 34, oxidizer nozzles 46 and fuel nozzles 47 and ignition devices 48 are installed. Similar ignition devices 48 are installed on the combustion chamber 13. The outlet of the gas generator 33 is connected to the head 26 of the combustion chamber 13 by the gas duct 49. A pipeline 50 s is connected to the starting turbine 31. a start valve 51 for starting a start turbine 31, for example, high pressure air supplied from ground equipment. An exhaust pipe 52 is connected to the exit of the starting turbine 31. The control unit 24 of the electric connections 25 is connected to the fuel shut-off valve 39, the oxidizer shut-off valve 45, the additional fuel shut-off valve 43, the actuator 42 of the flow controller 41 and the start valve 51. Connected to the fuel manifold 47 a purge line 53 with a purge valve 54. The purge is carried out with an inert gas, such as nitrogen. Solid fuel boosters 7 are connected to the rocket block of the lower stage 1 using pyro-bolts 55.

When the propulsion system starts from the control unit 24, signals are sent simultaneously to the solid fuel rocket engines and to the start valve 51. The solid fuel in the solid fuel rocket engines 8 is ignited and the anti-aircraft missile starts almost instantly. The liquid rocket engine of the lower stage 12 starts in flight after 0.1 ... 0.2 seconds. High pressure air (or inert gas or products of gasification of one-component fuel) from a boat system (not shown) is fed through a pipeline 50 to a starting turbine 31 and untwists ТНА 14 (more precisely, its rotor). The pressure of the oxidizer and fuel at the outlet of the oxidizer pumps 9 and the fuel pump 30 increases. A signal is sent to open the shut-off valves of the fuel 39, the oxidizer 45 and the additional shut-off valve of the fuel 43. The oxidizer and the fuel are supplied by the gas generator 34. The signal is supplied to the ignition devices 48, the fuel mixture in the combustion chamber 13 and in the gas generator 34 are ignited.

The post for the production of solid fuel is fed a signal to pyro-bolts 55 and solid fuel boosters 7 are discarded.

After developing the oxidizing agent and fuel from the tanks 18 and 19 of the first rocket stage 1, the valves 39, 43 and 45 are closed. The purge valve 53 is opened. The first rocket stage 1 is discarded by means of pyro-bolts installed in the connecting truss 3 (not shown). The rocket engine of solid fuel (engines) 15 of the second stage 2 is started. Traction control is also carried out by the control unit 24 by supplying signals to the drive 42 of the corresponding engine. Control during flight in the initial portion of the trajectory and at the final - is carried out by aerodynamic rudders 9. Wings 11 provide stabilization of the flight of an anti-aircraft missile in the atmosphere at an altitude of up to 10,000 m.

The application of the invention allowed:

1. Significantly increase the flight range of an anti-aircraft missile with its identical starting weight due to the use of liquid rocket engines for the lower stage of a multi-stage anti-aircraft missile and solid fuel rocket engines for upper rocket stages and for solid fuel boosters.

2. To optimize the launch weight of the rocket through the use of a control system installed only on the upper rocket stage.

3. Ensure good rocket controllability both in the initial part of the trajectory and in the final one by installing rotary aerodynamic rudders on the upper stage of an anti-aircraft missile.

Claims (1)

A multi-stage anti-aircraft missile containing at least two missile stages with at least one liquid rocket engine at the lower stage and fuel and oxidizer tanks connected to it by low pressure pipelines, characterized in that the aerodynamic steering wheels and wings are installed on the upper stage and, at least one solid fuel rocket engine, solid fuel accelerators with solid fuel rocket engines connected to the lower rocket stage parallel to its axis, each liquid The jet engine contains a combustion chamber with a regenerative cooling system and a turbopump unit containing oxidizer and fuel pumps, a main and starting turbine and a gas generator installed coaxially with the turbopump unit, the output of the fuel pump being connected to the input of the regenerative cooling system and to the gas generator input, and the pump output the oxidizer is connected to the second inlet of the gas generator, and the exits from the gas generator and the regenerative cooling system are connected to the cylindrical part of the combustion chamber.

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