RU2384473C2 - Hypersonic airplane with combat air craft laser - Google Patents

Abstract

FIELD: air transport.

SUBSTANCE: hypersonic airplane consists of hull, nose conical part, wings, tail group, fuel tanks, rocket propulsion system and fuel supply pipelines to it. Rocket propulsion system is installed in the rear part of hull and includes turbopump unit with shaft-mounted vanes for oxidiser and fuel, turbine, starting turbine and on-line installed gas generator, two combustion chambers and resonating chambers of combat lasers behind them. Regulator is installed in gas pipeline of one combustion chamber. Combat air craft laser is of electric-discharge type; it is installed at the output of combustion chamber. Inside laser there are electrodes connected to generator installed at turbopump unit of rocket propulsion system.

EFFECT: invention allows improvement of combat characteristics of the airplane.

3 cl, 3 dwg

Description

The invention relates to aviation, namely to hypersonic aircraft.

Known hypersonic aircraft according to the patent of the Russian Federation for the invention No. 20100744. The aircraft body is made in any longitudinal section along a cubic parabola with a blunt stern and a sweep angle along the leading edge of at least 60 °. The elevator is made in the form of a hinged front part of the body.

The disadvantage is the relatively low flight speed of the aircraft M = 4 ... 6.

Known hypersonic aircraft according to the patent of the Russian Federation for the invention No. 210407, containing the fuselage, the wings of the launch and mid-flight propulsion systems. Starting propulsion systems are made in the form of gas turbine engines - gas turbine engines, and marching engines - in the form of ramjets, specifically in a patented development it is proposed to use pulsating detonation air-jet engines.

The disadvantages of this aircraft: the relatively low flight speed of the aircraft and its long acceleration to hypersonic speeds due to the low thrust of the gas turbine engine.

The task of creating a hypersonic aircraft: improving the combat qualities of the aircraft.

The solution to this problem was achieved in a hypersonic aircraft with an aviation-based combat laser containing the fuselage, nose cone, wings, stabilizers, fuel tanks, rocket propulsion system and pipelines for supplying fuel components to it, by the fact that a rocket propulsion system is installed in the rear of the fuselage, which contains a turbopump assembly with oxidizer and fuel impellers mounted on the shaft, a turbine, a starting turbine and a coaxially mounted gas generator, two combustion chambers resonator chamber combat lasers - for them, in one of gazovode combustors mounted controller, combat air-based laser, electric discharge is formed, is mounted on the outlet of the combustion chamber, are installed inside the electrodes connected with a generator mounted on a turbopump assembly of rocket propulsion. Aiming lasers are installed on the wings of a hypersonic aircraft. Four control jet nozzles are connected radially in the nose conical part, which are connected through regulators to an auxiliary gas generator.

The invention is illustrated in figure 1 ... 6, where

figure 1 shows a diagram of a hypersonic aircraft,

figure 2 shows a section aa,

figure 3 shows a rear view of the aircraft,

figure 4 - diagram of the rocket propulsion system of the aircraft and the power of the combat aircraft-based laser,

figure 5 shows a diagram of a combat aircraft-based laser,

figure 6 shows a view of BB.

Hypersonic aircraft (figure 1) contains the fuselage 1, the nose conical part 2, wings 3, stabilizers 4 mounted on the axles 5 with the possibility of rotation. The axis 5 is connected to the drives 6. The drive 6 is connected to the control unit 7. At the rear of the fuselage 1 there is a rocket propulsion system 8 containing two combustion chambers 9 and two aviation-based combat lasers 10. An oxidizer tank 11 and a fuel tank 12 are installed inside the fuselage 1 , the oxidizer supply pipe 13 connected to the oxidizer tank 11, and the fuel supply pipe 14 is connected to the fuel tank 12 in its lower part. The oxidizer tank 11 is connected to the oxidizer supply pipe 14 with the rocket propulsion system 8. The fuel tank of fuel inlet 13 is connected to the conduit 14 with the rocket propulsion 8.

The combustion chamber 9 is made of rectangular cross-section. Airborne combat lasers 10 contain resonant chambers 11 installed at the outlet of the combustion chambers 9. Guidance lasers 16 are installed on the wings 3, and a pilot cockpit 17 is located in front of the fuselage 1. Four control nozzles 18 are radially mounted in the nose conical part 2 (FIG. .2) connected to an additional gas generator 19 and having regulators 20. The aircraft contains a control unit 21.

The rocket propulsion system 8 (Fig. 4) contains two combustion chambers 9 and a turbopump unit (TNA) 22. The turbopump unit 22, in turn, contains an oxidizer pump impeller 24 mounted on a TNA shaft 23, a fuel pump impeller 25, and a motor generator 26 , an additional fuel pump 27, with a shaft of an additional fuel pump 28, connected by a multiplier 29, located in the housing 30 with a shaft ТНА 23, the main turbine 31, made in the upper part of the turbopump unit 22. The gas generator 32 is mounted above the main turbine 31 in alignment with by a pumping unit 22. The combustion chamber 21 comprises a nozzle 33 made of two shells and a gap “A” between them, and a head of the combustion chamber 34, inside of which an outer plate 35 and an inner plate 36 with a cavity “B” are made between them. Inside the head of the combustion chamber 34, the oxidizer nozzles 37 and the fuel nozzles 38 are installed. The oxidizer nozzles 37 communicate the cavity “B” with the internal cavity of the combustion chamber “D”, and the fuel nozzles 38 communicate the cavity “B” with the internal cavity of the combustion chamber “D”. On the outer surface of the combustion chamber 9, a fuel manifold 39 is installed, from which the fuel lines 40 extend to the lower part of the nozzle 33. An outlet from the fuel valve 41 is connected to the fuel manifold 39, the inlet of which is connected by a fuel pipe 42 to the outlet of the fuel pump impeller 25. Exit from the additional the fuel pump 27 is connected by a high pressure fuel line 43 through a flow regulator 44 having an actuator 45 and a high pressure valve 46 with a gas generator 32, specifically, with a cavity “E”. The exit from the impeller of the oxidizer pump 24 through the oxidizer pipe 47 through the valve 48 is also connected to the generator 32, specifically with its cavity "G". Ignition devices 49 are installed on the head 35 of the combustion chamber 9, and ignition devices 50 are installed on the gas generator 31.

The generator 51 is docked with a cable 51, which is connected through an electric switch 52 to the electrodes 53 mounted inside the resonant chambers 15.

Electrolap devices 49 and 50, a fuel valve 41, an oxidizer valve 48, an actuator for the flow regulator 45, a high pressure valve 46, a start valve 52, and a regulator 55 installed in the gas duct 56 of one of the combustion chambers 9 are connected to the electric communication control unit 54.

A purge line 57 with a purge valve 58 is connected to the fuel manifold 39. Combustion chambers 9 can be mounted on pins 59 to swing them while controlling the course of the aircraft.

A gas sampling pipe 60 containing a gas sampling regulator 61 is connected to the turbopump assembly 22 behind the turbine 31, and the other end of this pipeline is connected to an aircraft-based combat laser 10. An aircraft-based combat laser 10 includes two mirrors 62 and an optical head 63 for outputting a laser beam. A power supply 64 is installed on the aircraft, which is connected via a start relay 65 to an electric generator 26 to start the TNA 22.

Approximate characteristics of a hypersonic aircraft:

Flight speed M = 12 Starting weight, t 150 Propulsion of a rocket propulsion system, t 2 × 80 Speed gain time M = 12, sec 120

Propellant Components for LRE

Oxidizer: oxygen Fuel: kerosene Combat Laser Power, MW 2 × 25 Time of continuous operation of laser weapons, s one hundred

Conventional armaments can be additionally installed on a hypersonic aircraft: machine guns and an aircraft gun.

When starting a rocket propulsion system 8 from the control unit 21, signals are sent to the starting relay 65, which connects the power source 64 to an electric generator 26 operating in the electric motor mode. The motor generator 26 spins the rotor TNA 22. The pressure of the oxidizer and fuel at the outlet of the impellers of the pumps of the oxidizer 22 and fuel 23 increases. A signal is sent to open the valves 41, 46 and 48. The oxidizing agent and fuel enter the combustion chamber 9 and the gas generator 32. A signal is supplied to the ignition devices 49 and 50, the fuel mixture in the combustion chamber 21 and in the gas generator 32 are ignited. Starting rocket engine 4 started. The flow controller 44 using the drive 45 carry out the regulation of its mode of operation.

When you turn off the starting rocket engine from the control unit 7, a signal is supplied to the valves 41, 46 and 48 and 55, which are closed. The purge valve 58 opens and the inert gas through the purge pipe 57 enters the fuel manifold 39 and then into the cavity "A" to remove residual fuel.

At the start and acceleration of a hypersonic aircraft, the flight angles are controlled by mismatching the thrust of the combustion chambers 9 using a regulator 55, which reduces the supply of gas from the gas generator 32 to one of the combustion chambers 9. When flying in the atmosphere, the airplane is controlled by control unit 7 using actuators 6 that deflect stabilizers 4. When flying outside the atmosphere (in space) or in a rarefied atmosphere at an altitude of more than 20,000 m, an auxiliary gas generator 19 is launched (Fig. 3) and, using the regulators 20, the products of combustion are fed into one from jet control nozzles 18.

To use an aircraft-based combat laser 15, the contacts 52 are closed and electric current is supplied through the electric cables 51 to the electrodes 53, pumping one of the gas-discharge lasers 15 (aircraft-based combat laser), where the electricity is converted into laser beam energy. The laser beam exits the optical head 63.

Landing of the aircraft is carried out horizontally.

The application of the invention allowed:

1. To increase the combat capabilities of the aircraft through the use of powerful laser weapons and their supply with high-energy gas from the rocket engine TNA and electric energy from a motor generator operating in generator mode.

2. Increase the flight speed of a hypersonic aircraft to M = 15.

3. Raise the ceiling of the flight of the aircraft to the level of space heights, because its flight and control do not need an atmosphere.

Claims (3)

1. A hypersonic aircraft with an aviation-based combat laser, containing the fuselage, nose cone, wings, stabilizers, fuel tanks, rocket propulsion system and pipelines for supplying fuel components to it, characterized in that the rocket propulsion system is installed in the rear of the fuselage and contains a turbopump unit with oxidizer and fuel impellers mounted on the shaft, turbine, starting turbine and coaxially mounted gas generator, two combustion chambers and resonator chambers of combat launchers Erov them, in the pipeline of one of the combustion chambers mounted controller, combat air-based laser formed electric discharge is mounted on the outlet of the combustion chamber, are installed inside the electrodes connected with a generator mounted on a turbopump assembly of rocket propulsion. 2. The hypersonic aircraft according to claim 1, characterized in that aiming lasers are installed on the wings of the aircraft. 3. The hypersonic aircraft according to claim 1, characterized in that four control jet nozzles are connected radially in the nose conical part and connected through regulators to an auxiliary gas generator.

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