RU187985U1 - HYPERSONIC AIRCRAFT ENGINE WITH RECTANGULAR AIR-REACTIVE ENGINE - Google Patents

Abstract

A hypersonic aircraft with a ramjet engine refers to aerospace engineering. The invention includes a hypersonic aircraft, a ramjet and a combustion chamber, as well as power sources and working gases. The low temperature plasma electrochemical generator contains a plasmatron and a thermochemical reactor connected to each other, which is connected to a combustion chamber and to a source of working gases. The plasma torch, in turn, is connected to power sources and working gases. This invention can be applied to ensure hypersonic speed flights in a wide range of Mach numbers M = 6-10 by expanding the range of flight modes and performing their operational adjustment. This makes it possible to use the claimed invention to solve a wide range of economic and environmental problems, namely: geodetic observations, monitoring and destruction of space debris, etc.

Description

The invention relates to the field of aerospace engineering, and in particular to aircraft with jet engines moving at supersonic or hypersonic speeds.

A known hypersonic aircraft (US 5452866 B64G 1/50), in the convex surface of the bow of which there are holes made in the form of microscopic pores. These openings are aligned with the openings to the combustion chamber of the engine. The holes are gasdynamically connected to the gas container. The purpose of this injection is to protect the critical part and the front section of the nose region of the aircraft from heat fluxes. The impedance does not decrease, and can even increase. The air stream is compressed, heats up strongly in the emerging shock wave and partially moves with the injected gas; those. when used for injection of combustible gas, a high-temperature air-fuel mixture is formed. As a result of this, its unwanted ignition is very likely. The flight performance of a hypersonic aircraft (GLA) in this case does not increase. The use of non-combustible gases is suitable for such an injection, which increases the wave resistance.

A device of the aircraft is known (patent RU 2107010, 03/20/1998 IPC В64С 21/02, В64С 23/00, В64С 30/00), containing inside the body a radiation energy source and a power source electrically connected to the radiation energy source. A device for focusing the radiation energy flux optically coupled to the radiation energy source is located in the frontal part of the aircraft body. There is a gas storage device, a device for preparing and supplying it. In the frontal part of the aircraft body, a nozzle system is made. This device provides shockless supersonic motion with simultaneous energy gain, high speed and range. The level of impact on the Earth's surface for a wide range of supersonic aircraft of various types and purposes is reduced. However, the performance characteristics of the known aircraft are not high enough.

Known hypersonic aircraft with ramjet engine (RU 2604975 04/20/2015 IPC F02K 7/10). This technical solution for the maximum number of similar essential features and for the achieved result when using it is taken as a prototype. In the front part of the known device, a recess (capacity) is formed, the volume of which is filled with combustible gas through openings located on the surface of the recess. An isobaric region is formed in this volume. On its flat border with air, a fuel-air mixture is formed, which enters the combustion chamber (CS) of the ramjet and is ignited in the combustion stabilization zone. However, to create a thrust that compensates for the aerodynamic drag force, a lot of combustible gas is consumed, and a large aerodynamic drag causes excessive heating of the hypersonic aircraft and negatively affects the range of flight modes.

The problem to which the invention is directed and the technical result that can be obtained by its implementation, allows to expand the range of hypersonic flight modes of a hypersonic aircraft and to carry out their operational correction when changing external flight conditions or flight mission. This is achieved by increasing the efficiency of the ramjet engine due to the organization of stable ignition and stable combustion of fuel while increasing the completeness of its combustion.

The essence of the claimed technical solution is illustrated by the drawing, where the figure shows a diagram of a hypersonic aircraft GLA with ramjet ramjet engine.

1 - GLA;

2 - ramjet;

3 - KS;

4 - power source plasmatron;

5 - source of the working gas of the plasma torch;

6 - source of working gas of a thermochemical reactor TXR;

7 - electrochemical generator of low-temperature plasma

8 - plasmatron;

9 - thermochemical reactor TXR.

The claimed invention, as well as the prototype, contains a hypersonic aircraft GLA 1 with ramjet ramjet engine 2 with a supersonic combustion chamber KS 3, as well as a power source 4 and sources of working gases 5 and 6. In contrast to the prototype, the claimed device is equipped with an electrochemical generator low-temperature plasma 7, consisting of interconnected plasmatron 8 and thermochemical reactor TXR 9 connected to a supersonic combustion chamber KS 3. An electrochem is connected to the channel of the combustion chamber KS 3 a low-temperature plasma generator 7 for a more effective effect on internal processes in the combustion chamber 3. An electric power source 4 and a working gas source 5 are connected to the plasma torch 8. A working gas source 6 is connected to the thermochemical reactor TXR 9.

The operation of the claimed invention is as follows. A plasma jet is introduced into the channel of the KS 3 supersonic combustion chamber of the ramjet engine 2 of the ramjet 2 engine from the thermochemical reactor TXR 9 of the low-temperature plasma generator 7. The introduction of the plasma jet into the channel of the compressor 3 improves the quality of mixing the fuel with air. Plasma heats the air-fuel mixture and enriches it with highly reactive elements (radicals, charged and excited particles). These elements are necessary to reduce the delay time of ignition of hydrocarbon fuel in a supersonic air flow and to stabilize its subsequent combustion in the combustion chamber of KS 3. Initially, a plasma of a certain composition, flow rate and temperature is formed in the plasma torch 8 using the working gas from source 5 and the electrical energy of power supply 4. Before the plasma is injected into the channel KS 3, it passes through the channel of the thermochemical reactor TXR 9. Here, the plasma from the plasma torch 8 interacts with the working gas TXR 9 from the source 6. As a result of this interaction, an additional amount of highly reactive elements is formed. The use of TXR 9 as part of an electrochemical generator of low-temperature plasma 7 makes it possible to economically consume electric power by a plasma torch 8. The possibility of performing a GLA flight on hydrocarbon fuel in the range of Mach numbers M = 6-10 is ensured by controlling the combustion process in KS 3 ramjet 2 in a wide range of and supersonic air flow rates in it.

The technical result of the claimed invention is to expand the range of flight modes of a hypersonic aircraft GLA with ramjet and performing operational adjustments by improving the efficiency of ramjet ramjet engine 2. Achieving the claimed technical result is confirmed by the calculation and experimental studies conducted at the enterprise.

Claims (1)

A hypersonic aircraft with a ramjet engine containing a supersonic combustion chamber, an electric power source and sources of working gases, characterized in that the hypersonic aircraft is equipped with an electrochemical low-temperature plasma generator consisting of interconnected plasmatrons and a thermochemical reactor that is directly connected to the channel supersonic combustion chamber, while the plasma torch is connected to a power source, and to a thermochemical reactor at and to a plasmatron sources of working gases are connected.

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