RU2366593C1 - Military-space airplane with aviation-based fighting laser - Google Patents

Abstract

FIELD: transportation.

SUBSTANCE: airplane comprises fuselage, front and back wings, gas-turbine engines installed on wings, and rocket engine installed in back part of fuselage. On upper part of fuselage along its longitudinal axis there is aviation-based fighting laser installed, which is connected by air sampling pipelines that comprises controller valve to at least one gas-turbine engine and with rocket engine. Laser is arranged as gas-dynamic, comprises optical head and exhaust system, is connected by air sampling pipeline comprising controller valve to turbo-pump set downstream turbine.

EFFECT: improved fighting properties of airplane.

5 cl, 5 dwg

Description

The invention relates to aviation, namely to military 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 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 armament of the aircraft with conventional weapons: machine guns and cannons.

The task of creating an aircraft and aircraft-based combat laser: improving the combat qualities of the aircraft.

The solution of these problems was achieved in a military space aircraft containing the fuselage, front and rear wings, gas turbine engines mounted on the wings and a rocket engine mounted in the rear of the fuselage, in that an aviation-based combat laser was installed on the upper part of the fuselage along its longitudinal axis which is connected by air extraction pipelines containing a control valve to at least one gas turbine engine and to a rocket engine. The rocket engine contains a turbopump assembly, two combustion chambers and a central body between them, and an air exhaust pipe is connected to the turbopump assembly. Each gas turbine engine contains a compressor, a combustion chamber, and a turbine, and an air exhaust pipe is connected to a manifold arranged behind the compressor of the gas turbine engine. Aircraft-based combat laser can be pivotally mounted on the fuselage, and vertical and horizontal guidance cylinders are attached to its front.

The solution of these problems was achieved in an aviation-based combat laser containing an optical head and an exhaust system, in that it is gasdynamic and connected by air extraction pipelines containing a control valve to a compressor of at least one gas turbine engine and with a turbo pump unit behind the turbine.

The proposed technical solution has novelty, inventive step and industrial applicability, i.e. all the criteria of the invention.

The novelty of the proposed technical solution is confirmed by patent research, the inventive step is that a new set of essential features made it possible to obtain a new technical effect, namely, a decrease in the acceleration time of the aircraft to hypersonic speeds and an increase in flight speed. Industrial applicability is due to the fact that the implementation of the invention does not require the creation of new unknown from the prior art parts and assemblies and new technologies.

The invention is illustrated in figure 1 ... 5, where:

figure 1 shows a diagram of a military space aircraft, top view,

figure 2 shows a side view of a military space aircraft,

figure 3 shows a rear view of a military space aircraft,

figure 4 shows a diagram of a gas turbine engine of a military space aircraft and a power supply system for an aircraft-based combat laser from a gas turbine engine,

figure 5 shows a diagram of a rocket engine of a military space aircraft and a power supply system for a combat-based aviation laser from a rocket engine.

Hypersonic aircraft (figure 1 ... 5) contains the fuselage 1, cockpit 2, front wings 3, rear wings 4 and tail unit 5. Gas turbine engines 6 are installed on the front wings 3.

In the upper part of the fuselage 1, there is an aviation-based combat laser 7 containing an optical head 8, a vertical guidance cylinder 9 and a rotary mechanism 10 with a shaft 11 and a hinge 12. A system of vertical and horizontal laser guidance is provided. The horizontal guidance system can be used in space or at high altitude, as when flying in dense layers of the atmosphere, when turning a laser body with large axial dimensions, the aerodynamic qualities of the aircraft will significantly deteriorate. The aircraft contains an air sampling system 13 with control valves 14, connecting gas turbine engines 6 with aviation-based combat lasers 7 for supplying high-energy compressed air for pumping a combat laser. An exhaust system 15 is provided for discharging exhaust air from the laser cavity 7. A rocket engine 16 is installed at the rear of the fuselage 1, comprising a turbopump unit 17 with two combustion chambers 18 and a central body 19 installed between them. The aircraft fuselage 1 is mounted on the chassis 20 (Fig. 3) designed for take-off and landing of the aircraft.

Gas turbine engines 6, which can be from one to eight, are made of the same design (Fig. 4), in the case of using two or more engines, and contain an air intake 21, a compressor 22, a combustion chamber 23 with nozzles 24, a turbine 25 and a jet nozzle 26 The gas turbine engine 6 has one or two shafts 27 mounted on bearings 28. The fuel supply system includes a fuel line 29, a fuel pump 30 with a drive 31. Behind the compressor 22 (preferably the last stage of the compressor), an air intake manifold 32 is made to which through a valve An regulator 14 is connected to an air sampling system 13, the other end of which is connected to a ground-based combat laser 7.

The rocket engine 16 (figure 5) contains a turbopump assembly (TNA) 17, two combustion chambers 18 and a flat central body 19 installed between them, providing additional expansion of the exhaust jet of the combustion chambers 18 in space. The turbopump assembly 17, in turn, comprises an oxidizer pump impeller 34 mounted on a TNA shaft 33, a fuel pump impeller 35, a starting turbine 36, an additional fuel pump 37, with an additional fuel pump 38 shaft connected by a multiplier 39, which is located in the housing 40 with the shaft TNA 33, the main turbine 41, made in the upper part of the turbopump unit 42. The gas generator 42 is mounted above the main turbine 41 coaxially with the turbopump unit 17. The combustion chamber 18 contains a nozzle 43 made of two shells and a clearance of "Therebetween, and a head combustion chamber 44 within which formed the outer plate 45 and inner plate 46 to the cavity" b "between them. Inside the head of the combustion chamber 44, the oxidizer nozzles 47 and the fuel nozzles 48 are installed. The oxidizer nozzles 47 communicate the cavity “B” with the internal cavity of the combustion chamber “D”, and the fuel nozzles 48 communicate the cavity “B” with the internal cavity of the combustion chamber “D”. A fuel manifold 49 is installed on the outer surface of the combustion chamber 18, from which the fuel lines 50 exit to the lower part of the nozzle 43. An outlet from the fuel valve 51 is connected to the fuel manifold 49, the inlet of which is connected by a fuel pipe 52 to the outlet of the fuel pump impeller 35. Exit from the additional the fuel pump 37 is connected by a high pressure fuel line 53 through a flow regulator 54 having an actuator 55 and a high pressure valve 56 with a gas generator 42, specifically with a cavity “E”. The exit from the impeller of the oxidizer pump 34 through the oxidizer pipe 57 through the valve 58 is also connected to the generator 42, specifically with its cavity "G". Ignition devices 59 are installed on the head 45 of the combustion chamber 18, and ignition devices 60 are installed on the gas generator 41.

A high pressure pipe 61 with a start valve 62 is connected to the start turbine 36, designed to start the start turbine 36. The other end of the high pressure pipe 62 is connected to a compressed air cylinder 63.

Electrolap devices 59 and 60, a fuel valve 51, an oxidizer valve 58, an actuator for the flow regulator 55, a high pressure valve 56, a start valve 62, and a regulator 65 installed in the gas duct 66 of one of the combustion chambers 18 are connected to the control unit 64.

A purge line 67 with a purge valve 68 is connected to the fuel manifold 49. Combustion chambers 18 can be mounted on pins 69 to swing them while controlling the course of the aircraft.

A gas sampling pipe 70 containing a gas sampling regulator 71 is connected to the turbopump assembly 32 behind the turbine 41, the other end of this pipeline is connected to an aircraft-based combat laser 7, to which the exhaust device 15 is also connected. The rocket engine 16 has a control system 64, which is electrically connected 72 is connected to all valves, regulators and ignition devices.

Indicative characteristics of a military space aircraft:

Flight speed M = 15 Starting weight, t 250 Take-off thrust of turbojet engines, t 4 × 20 Propulsion of a rocket propulsion system, t 2 × 80 Speed gain time M = 15, sec 120

Propellant Components for LRE

Oxidizer: Oxygen Fuel: Kerosene Dense combat laser power atmospheric layers, MW 5 The power of a combat laser in space, MW twenty Laser uptime weapons in a dense atmosphere, with 6000 Laser uptime weapons in space, with one hundred

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

During take-off, the fuel pump 30 is unwound by the drive 31 and the fuel is supplied through the fuel line 29 to the nozzles 24 of the combustion chamber 23, where it is ignited. The combustion products spin the turbine 25. The turbine 25 through the shafts 27 spins the compressor 22, as a result of the jet nozzle 26 creates a jet thrust for flying in dense layers of the atmosphere.

For flight at high altitudes or in space, a rocket engine 16 is launched. For this, a rocket engine 16 is launched.

When the rocket engine 16 is started from the control unit 64, signals are sent to the start valve 62. High pressure air from the ground system through the high pressure pipe 61 is supplied to the start turbine 36 and spins the TNA rotor 17. The oxidizer and fuel pressure at the outlet of the impellers of the oxidizer pumps 32 and fuel 33 is increasing. A signal is sent to open the valves 51, 56 and 58. The oxidizing agent and fuel enter the combustion chamber 31 and the gas generator 42. A signal is supplied to the ignition devices 59 and 60, the fuel mixture in the combustion chambers 18 and in the gas generator 42 are ignited. Rocket engine 16 started. The flow regulator 54 using the drive 55 carry out the regulation of its mode of operation.

When you turn off the starting rocket engine from the control unit 64, a signal is supplied to the valves 51, 56 and 58 and 65, which are closed. Then, a signal is sent to open the purge valve 62, and inert gas through the purge pipe 61 enters the fuel manifold 59 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 18 with the help of a regulator 65, which reduces the gas supply from the gas generator 42 to one of the combustion chambers 18.

For the use of laser weapons in dense layers of the atmosphere, the control valve 14 is opened and part of the compressed air (up to 20% of the total air flow through the gas turbine engine 6) is taken from each gas turbine engine 6 for pumping a laser beam in an aircraft-based combat laser 7. Applied gas-dynamic laser, as the reserves of compressed air taken from engines 6 are practically unlimited, compared with a chemical or carbon dioxide laser.

The laser beam exits through the optical head 8 and is aimed at the target using the guidance system, which is not shown in FIGS. 1 ... 5 in detail, only the executive organs of the laser beam guidance system are shown on the target. Vertical guidance is carried out by a vertical guidance hydraulic cylinder 9. When the rod of the hydraulic cylinder 9 is extended, the angle α between the axis of the aircraft and the longitudinal axis of the aircraft-based laser 7 increases. Horizontal guidance during flight in dense layers of the atmosphere is carried out by plane, mismatch of engine thrust 6 and / or aerodynamic means. When flying in space or at high altitudes, another guidance system is used, described below. When flying at high altitudes or in space, horizontal laser control is preferred. To do this, include a drive 10 that rotates the airborne laser housing at + -40 degrees.

To use an aviation-based combat laser 7 at high altitudes or in space, a gas sampling regulator 71 is opened and high-pressure and temperature gas (up to 20% of the total gas flow generated by the gas generator 42) is supplied to the aviation-based combat laser 7 via a gas sampling pipeline 70, where the energy of the gas is converted into the energy of a laser beam. The exhaust gas is discharged into the gas discharge system 15. The laser beam exits the optical head 8 and hits the target. For aiming, guidance lasers can be used, which have significantly lower power and are installed on the front wings of a military-space aircraft. (In figure 1 ... 5 laser lasers are not shown).

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 compressed air taken from one engine or all engines of a multi-engine aircraft due to the compressor (behind its last stage) or gas extraction from the turbine engine of a rocket engine with a higher energy potential.

2. To ensure the possibility of using laser weapons for a long time throughout the flight both in dense atmospheric layers to protect the aircraft from fighter and air defense missiles, and against satellites and ballistic missiles flying at high speed in space or at high altitudes.

3. To ensure that the laser beam is aimed at the target without impairing the aerodynamic qualities of the aircraft in dense layers of the atmosphere and horizontal guidance in space and at high altitudes.

Claims (5)

1. A military space aircraft containing the fuselage, front and rear wings, gas turbine engines mounted on the wings, and a rocket engine mounted in the rear of the fuselage, characterized in that on the upper part of the fuselage along the longitudinal axis there is an aircraft-based combat laser, which is connected by air extraction pipelines containing at least one control valve with at least one gas turbine engine and a rocket engine. 2. The military space aircraft according to claim 1, characterized in that the rocket engine comprises a turbopump assembly, two combustion chambers and a central body between them, and an air sampling pipe is connected to the turbopump assembly. 3. The military spacecraft according to claim 1 or 2, characterized in that each gas turbine engine contains a compressor, a combustion chamber and a turbine, and the air intake pipe is connected to a manifold made behind the compressor of the gas turbine engine. 4. A military space aircraft according to claim 1 or 2, characterized in that the aircraft-based combat laser is pivotally mounted on the fuselage, and a vertical guidance hydraulic cylinder is attached to its front. 5. Aircraft-based combat laser containing an optical head and an exhaust system, characterized in that it is gas-dynamic and connected by an air sampling pipe containing a control valve with a turbopump assembly behind the turbine.

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