RU2305056C1 - Hypersonic aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: proposed aircraft has fuselage, wings, fuel tanks, cruise ramjet engines and booster engines working on liquid propellant components. Oxidizer and fuel tanks are mounted in fuselage. Heat-insulated oxidizer supply pipe line runs inside fuel tank which is connected with booster engines by means of fuel supply pipe lines. Ramjet engines are mounted on wings and are connected with fuel tank by means of fuel pipe lines. Booster engines may be turned and fixed in vertical plane. Cruise ramjet engines are provided with swivel flaps at outlet for pitch angle control.

EFFECT: increased flying speed; enhanced economical efficiency of flight.

4 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 invention No. 2130407, 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.

Tasks of creating a hypersonic aircraft: reducing the time of acceleration of the aircraft to hypersonic speeds and increasing flight speed.

The solution to this problem was achieved due to the fact that a hypersonic aircraft containing the fuselage, wings, fuel tanks, mid-flight engines, launch rocket engines and pipelines for supplying fuel components to them, is characterized in that the launch rocket engines are made using liquid fuel components: oxidizer and fuel, an oxidizer tank and a fuel tank are installed in the fuselage, the oxidizer supply pipe passes inside the fuel tank, and the fuel tank is connected to the fuel supply pipes with everything and starting rocket engines, direct-flow engines are made in the wings and are connected by fuel pipelines to the fuel tank. Starting rocket engines are made with the possibility of rotation and fixation in a vertical plane.

Marching ramjet engines at the exit are equipped with butterfly valves for pitch angle control. The oxidizer supply pipe is thermally insulated.

The proposed technical solution has novelty, inventive step and industrial applicability. The novelty is confirmed by patent research, and the inventive step is due to the fact that a new set of essential features made it possible to obtain a new technical effect, namely, reducing the time to accelerate the aircraft to hypersonic speeds and increasing 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 ... 3, where:

figure 1 shows a diagram of a hypersonic aircraft,

figure 2 - diagram of the march ramjet engine,

figure 3 - diagram of the starting rocket engine.

Hypersonic aircraft (figure 1) contains the fuselage 1, stabilizers 2, wings 3, launch rocket engines 4, marching ramjet engines 5 installed in the wings 3, the oxidizer tank 6, the fuel tank 7. The oxidizer tank 6 is connected to the start of the oxidizer 8 with the start rocket engines 4. The fuel tank 7 is connected by a fuel pipe 9 to the starting rocket engines 4 and fuel pipelines 10 with marching ramjet engines 5.

Scheme marching ramjet engine shown in figure 2. Marching ramjet engines 5 are built into the wings 3 of the aircraft and contain a confuser-shaped air intake 11, a critical part of the combustion chamber 12, an expanding supersonic nozzle 13. Inside the Marching ramjet engines 5, a fuel manifold 14 is installed, which is connected by a fuel pipe 10 to the fuel tank 7. At the top outlet the edge of the wings 3 on the hinge 15 fixed controlled sash 16, to which are connected the rods 17 of the control cylinders 18, which are connected by links 19 to the control unit 20.

The starting rocket engine 4 (Fig. 3) comprises a combustion chamber 21 and a turbopump unit 22. The turbopump unit 22, in turn, comprises an oxidizer pump impeller 24 mounted on a TNA shaft 23, a fuel pump impeller 25, a start turbine 26, and an additional fuel pump 27 , with the shaft of the additional fuel pump 28, connected by a multiplier 29, located in the housing 30 with the TNA shaft 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 the turbopump m unit 22. The combustion chamber 21 comprises a nozzle 33 formed of two shells and a gap "A" therebetween and head of the combustion chamber 34 within which formed the outer plate 35 and inner plate 36 to the cavity "b" 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”. A fuel manifold 39 is installed on the outer surface of the combustion chamber 21, from which the fuel lines 40 extend to the lower part of the nozzle 33. An outlet from the fuel valve 40 is connected to the fuel manifold 39, the inlet of which is connected by a fuel pipe 41 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 42 through a flow regulator 43 having an actuator 44 and a high pressure valve 45 with a gas generator 32, specifically with a cavity “E”. The exit from the impeller of the oxidizer pump 24 through the oxidizer pipe 46 through the valve 47 is also connected to the generator 32, specifically with its cavity "G". Ignition devices 48 are installed on the head 35 of the combustion chamber 21, and ignition devices 49 are installed on the gas generator 31.

A high pressure pipeline 50 is connected to the starting turbine 26 with a starting valve 51, designed to start the starting turbine 26.

To the control unit 20 of electrical connections 19 are connected electroslip devices 48 and 49, a fuel valve 40, an oxidizer valve 47, an actuator for the flow regulator 44, a high pressure valve 45, a start valve 51.

A purge line 52 with a purge valve 53 is connected to the fuel manifold 39. A trunnion 54 is made on the combustion chamber to swing it in the same plane. The drive is carried out using a hydraulic cylinder 55 connected to a control unit 20.

Approximate characteristics of a hypersonic aircraft:

Flight speed M = 10 Starting weight, t 250 Thrust of starting engines, t 2 × 150 Thrust of marching ramjet engines, t 6 × 20 Speed up time M = 10, s one hundred

Propellant components for launch rocket engine

Oxidizer oxygen Fuel kerosene Propellant for marching ramjet engine kerosene

A hypersonic plane can take off vertically.

When starting rocket engines 4 are started from the control unit 20, signals are sent to the starting valve 51. High pressure air from the ground system through the high pressure pipe 50 is supplied to the starting turbine 26 and untwists the TNA rotor 22. The oxidizer and fuel pressure at the outlet of the impellers of the oxidizer pumps 22 and fuel 23 is increasing. A signal is sent to open the valves 40, 45 and 47. The oxidizing agent and fuel enter the combustion chamber 21 and the gas generator 32. A signal is supplied to the ignition devices 48 and 49, the fuel mixture in the combustion chamber 21 and in the gas generator 32 are ignited. Starting rocket engine 4 started. The flow regulator 43 using the drive 44 carry out the regulation of its operation mode.

When you turn off the starting rocket engine from the control unit 20, a signal is supplied to the valves 40, 45 and 47, which are closed. Then, a signal is sent to open the purge valve 53 and inert gas through the purge pipe 52 enters the fuel manifold 39 and then into the cavity "A" to remove residual fuel.

After turning off the starting rocket engines or simultaneously with them, marching ramjet engines 5 are started (Fig. 1). To start them, fuel from the fuel tank 7 is fed through a fuel pipe 10 to a fuel manifold 14 of direct-flow marching engines 5 to the fuel manifold 14. When the fuel is burned, energy is generated and the resulting exhaust gases enter the expanding supersonic nozzle 13 and then enter the atmosphere. creating jet thrust.

At the start and acceleration of a hypersonic aircraft, the flight angles are controlled by the mismatch of the thrust of the rocket launch engines 4 and their swing on the pins 54 using the hydraulic cylinders 55. In hypersonic mode, the aircraft is controlled by the control unit 20 using the shutters 16, which are deflected by the control hydraulic cylinders 18.

The application of the invention allowed:

1. Increase the speed of the hypersonic aircraft.

2. Accelerate the process of gaining maximum hypersonic speed.

3. Simplify the fuel supply scheme of starting and main engines.

4. Improve the reliability of hypersonic aircraft.

5. Increase the power and specific characteristics of a hypersonic aircraft.

6. To reduce the weight of the aircraft, starting and ramjet engines by unifying one of the fuel components for two types of engines.

7. Ensure reliable control of the aircraft.

8. Improve engine starting and shutting down and ensure that they are cleaned of residual fuel after shutting down.

Claims (4)

1. A hypersonic aircraft containing the fuselage, wings, fuel tanks, direct-flow marching engines, launch rocket engines and pipelines for supplying fuel components to them, characterized in that the launch rocket engines are made using liquid fuel components: oxidizer and fuel, a tank is installed in the fuselage with an oxidizing agent and a fuel tank, the oxidizer supply pipe passes inside the fuel tank, and the fuel tank is connected to the fuel supply pipelines with all the starting rocket engines; the engines are made in the wings and are connected by fuel pipelines to the fuel tank. 2. The hypersonic aircraft according to claim 1, characterized in that the launch rocket engines are made with the possibility of rotation and fixation in a vertical plane. 3. The hypersonic aircraft according to claim 1 or 2, characterized in that the marching once-through engines at the exit are equipped with rotary dampers for controlling the pitch angle. 4. The hypersonic aircraft according to claim 1 or 2, characterized in that the oxidizer supply pipe is thermally insulated.

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