Hypersonic aircraft and onboard combat laser

FIELD: aircraft engineering, weapons.

SUBSTANCE: invention relates to combat aircraft. Proposed hypersonic aircraft comprises airframe, conical nose, wings, tailplane, fuel tanks, rocket engine and fuel lines. Airframe top accommodates onboard combat laser fitted along airframe lengthwise axis. Rocket engine plant is mounted at airframe rear and incorporates turbopump unit with oxidiser and fuel impellers fitted on the shaft, turbine, starting turbine and gas generator aligned therewith, two combustion chambers and flat central body mounted there between. Turbopump unit and combat laser communicates via gas bleed pipeline incorporating gas flow rate control valve.

EFFECT: higher combat performances.

4 dwg


The invention relates to aviation, namely to hypersonic aircraft.

Known hypersonic aircraft by RF patent for the invention №2010744. The body of the plane is made in any longitudinal section of the cubic parabola with a blunt aft and angle of sweep of the leading edge is not less than 60°. The rudder is made in the form of a hinged front part of the body.

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

Known hypersonic aircraft by RF patent for the invention №210407 containing the fuselage, wings starter and main propulsion. The starting of the propulsion system made in the form of gas turbine engines - GTE, and propulsion engines in the form of a ramjet engines, specifically in the patented development is proposed to apply the pulsating detonation of the air-jet engines.

The disadvantages of this plane: a relatively low speed flight and a long time it can accelerate to hypersonic speeds due to the low thrust of the CCD.

The task of creating a hypersonic aircraft: improvement of the martial qualities of the aircraft.

The solution of the stated problem is achieved in hypersonic plane containing the fuselage, nose cone portion, wings, stabilizers, fuel tanks, rocket propulsion system and piping for supplying the components is now fuel thereto, the fact that the upper part of the fuselage along its longitudinal axis mounted combat laser aviation bushiribana, rocket propulsion system installed in the rear fuselage and contains turbopump unit, installed on the shaft impellers of oxidizer and fuel, turbine, starting turbine and coaxially mounted generator, two combustion chambers and flat Central body between them, turbopump Assembly and combat aviation laser-based piped gas extraction containing gas flow regulator. On the wings of the aircraft is equipped with laser aiming. In the forward tapered portion radially mounted four control jet nozzles connected to the controllers with auxiliary gas generator. In gazivode one of the combustion chambers installed in the controller.

These objectives are achieved in combat aviation laser-based due to the fact that it is made of gas-dynamic and piped gas extraction, containing the flow regulator gas turbopump Assembly for a turbine.

The proposed solution has novelty, inventive step and industrial applicability. Novelty is confirmed by the results of the patent research, inventive step that a new set of essential features for valila to get a new technical effect, namely reducing the acceleration of the aircraft to hypersonic speeds and increase airspeed. Industrial applicability is due to the fact that the implementation of the invention does not require a new unknown in the prior art parts and components and new technologies.

The invention is illustrated in figure 1...4, where:

figure 1 shows a diagram of a hypersonic aircraft,

figure 2 shows the section a-a,

figure 3 shows a view of the plane from behind,

figure 4 - scheme of the rocket propulsion system of the aircraft and the power of the combat aviation laser-based.

Hypersonic plane (figure 1) contains the fuselage 1, the nose cone part 2, wings 3, stabilizers 4 mounted on the axis 5 can be rotated. Axis 5 is connected to the actuator 6. The actuator 6 is connected to the control unit 7. In the rear part of the fuselage 1 posted by rocket engine unit 8 containing two combustion chambers 9 and the Central body 10. Inside the fuselage 1 is installed oxidizer tank 11 and the fuel tank 12, a pipeline for supplying oxidant 13, connected to the tank of 11 oxidant and fuel to the tank 12 in the bottom of the docked pipeline supply of fuel 14. Oxidizer tank 11 is connected by a pipeline supply of oxidizer 14 with rocket propulsion system 8. Fuel tank 13 is connected by a pipeline supplying fuel 14 with rocket DWI is athelney installation 8.

In the upper part of the fuselage 1 is a combat aviation laser-based 15 on the ends of the wings 3 lasers guidance 16, and in the front part of the fuselage 1 is the pilot's cabin 17. In the forward conical part 2 of radially mounted four governors of the nozzle 18 (figure 2)connected to the additional gas generator 19 and with the regulators 20. The fuselage 1 of the aircraft is mounted on the chassis 21 (figure 3).

Rocket engine unit 8 (figure 4) contains two combustion chambers 9 and turbopump Assembly (TNA) 22. Turbopump Assembly 22, in turn, contains installed on the shaft TNA 23 and the impeller of the oxidizer pump 24, the impeller of the fuel pump 25, starting the turbine 26, the additional fuel pump 27, with the shaft of the additional fuel pump 28 connected to the multiplier 29, accommodated in the housing 30, with the shaft TNA 23, main turbine 31 in the top part of the turbopump Assembly 22. The gas generator 32 is mounted above the main turbine 31 coaxially with the turbopump Assembly 22. The combustion chamber 21 contains a nozzle 33, made of two shells with a gap "A" between them, and the head of the combustion chamber 34 within which is made of the outer plate 35 and the inner plate 36 with the cavity "B" between them. Inside the head of the combustion chamber 34 is installed injector oxidizer 37 and fuel nozzles 38. Injector oxidizer 37 report of the cavity "b" from inside the second cavity of the combustion chamber "D", and fuel nozzles 38 report of the cavity "B" with the internal cavity of the combustion chamber "D". On the outer surface of the combustion chamber 21 has a fuel manifold 39, which runs the fuel lines 40 to the lower part of the nozzle 33. To the fuel manifold 39 is connected to the output of the fuel valve 41, the inlet of which a fuel pipeline 42 is connected to the exit of the impeller of the fuel pump 25. The output of the additional fuel pump 27 is connected by a high pressure fuel line 43 through the flow regulator 44, with the actuator 45 and the high pressure valve 46 with the gas generator 32, specifically with the cavity "E". The exit of the impeller of the pump oxidizer 24 pipeline oxidant 47 through the valve 48 is also connected to the generator 32, specifically with its cavity "W". On the head 35 of the combustion chamber 21 is installed ignition device 49, and the gas generator 31 - ignition device 50.

For starting the turbine 26 is docked the high pressure pipeline 51 with starting valve 52, which is intended for starting the turbine 26. The other end of the high pressure pipeline 52 is connected with a cylinder of compressed air 53.

To the control unit 21 electrical connections 54 connected electrosupply devices 49 and 50, the fuel valve 41, the valve oxidizer 48, the actuator of the flow regulator 45, the high pressure valve 46, starting valve 52 and the controller 55, have been fitted the th in gazivode 56 one of the combustion chambers 9.

To the fuel manifold 39 is connected vent pipe 57 with the purge valve 58. The combustion chamber 9 can be installed on the pins 59 to swing in the management of the aircraft's heading.

To turbopump Assembly 22 for turbine 31 is connected to the pipeline gas extraction 60 containing the regulator of gas sampling 61, the other end of this pipe is connected to a combat aviation laser base 15 to which is also connected to an exhaust device 62. Combat aviation laser-based contains optical head 63 to output the laser beam.

Indicative characteristics of hypersonic aircraft:

Flight speedM=12
Starting weight, t150
Thrust rocket propulsion, t2×80
Time set the speed of M=12, p120

Components of rocket fuel for rocket engines

The combat power of the laser, MW 5
Time of continuous operation of the laser weapon,600

On hypersonic aircraft can be optionally installed conventional weapons: machine guns and air gun.

When launching the rocket propulsion system 21 from the control unit 7 serves signals for starting valve 52. The high pressure air to ground systems for high pressure pipeline 51 is fed to starting the turbine 26 and spins the rotor TNA 22. The pressure of the oxidant and fuel at the outlet of impeller pumps oxidant 22 and 23 fuel increases. The signal to open valve 41, 46 and 48. The oxidizer and fuel enter the combustion chamber 21 and the gas generator 32. A signal to the ignition device 49 and 50, the fuel mixture in the combustion chamber 21 and the gas generator 32 is ignited. Launch rocket engine 4 started. Flow regulator 44 through drive 45 control mode operation.

When starting off a rocket engine control unit 7 sends the signal to the valves 41, 46 and 48 and 55, which are closed. Then the signal to open the purge valve 52, and an inert gas purge pipe 51 flows into the fuel manifold 39 and then into the cavity "A" to remove excess fuel.

When the start and acceleration of the ISU is zvukovogo aircraft control angles of flight is a misalignment of the thrust of the combustion chamber 9 by means of the knob 55, reducing the flow of gas from the gas generator 32 into one of the combustion chambers 9. When flying in the atmosphere of the management plane performs the control unit 7 by means of the actuators 6, which rejects the stabilizers 4. When flying out of the atmosphere (in space) or in a reducing atmosphere at a height of more than 200,000 m start the auxiliary generator 19 (Fig 3) and using the controllers 20 serves the products of combustion in one of the reactive control nozzles 18.

To use the combat aviation laser-based 15 open the regulator of the gas 61, and the gas of high pressure and temperature (up to 20% of the total gas flow generated by the gas generator (22) for pipeline gas extraction 60 enters combat aviation laser-based 15, where the energy of the gas is converted into energy of the laser beam. Exhaust gas is discharged to the system gas outlet 62. The laser beam exits the optical head 63.

The landing of an aircraft is carried out horizontally on the chassis 21.

The application of the invention allowed:

1. To enhance the combat capabilities of the aircraft through the use of a powerful laser weapon and its power of high-energy gas from TNA rocket engine.

2. To increase the speed of flight of a hypersonic aircraft up to M=12.

3. To increase the ceiling plane to the level of cosmic heights, as his flight and control is not needed is and the atmosphere.

4. To speed up the process set maximum hypersonic speed.

5. To simplify the design of the fuel supply starting and engines.

6. To increase the reliability of hypersonic aircraft.

7. To increase the capacity and the specific characteristics of hypersonic aircraft,

8. To reduce the weight of the plane.

9. To ensure reliable operation of aircraft through the use of two control systems: aerodynamic and hydrodynamic.

10. To improve the startup and shutdown of the rocket propulsion system and to ensure their clearance from combustible residues after turning off the blow cavities of the combustion chambers with an inert gas.

Hypersonic plane containing the fuselage, nose cone portion, wings, stabilizers, fuel tanks, rocket propulsion system and piping for supplying fuel components to it, characterized in that on the upper part of the fuselage along its longitudinal axis mounted combat aviation laser-based missile propulsion system installed in the rear fuselage and contains turbopump Assembly installed on the shaft impellers of oxidizer and fuel, turbine, starting turbine and coaxially mounted generator, two combustion chambers and flat Central body between them, turbopump Assembly and combat aviation laser-based connected trubor what Bodom gas extraction, containing gas flow regulator.


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