RU2560224C1 - Airborne vehicle - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering. Airborne vehicle comprises airframe, air intake, control unit and conical combustion chamber with exhaust nozzle. Airframe is rigidly coupled with control unit and conical combustion chamber. Combustion chamber has two hydraulic links with control unit and is rigidly coupled with exhaust nozzle.

EFFECT: decreased overall dimensions, sufficient acceleration.

1 dwg

Description

The invention relates to the field of aerospace engineering and can be used for flights in the atmosphere and space.

Known aircraft, described in patent No. 2363625, author Chasovskaya A.A. It uses a cone-shaped combustion chamber with an exhaust nozzle behind it, rigidly connected to the housing, to which the control unit that delivers fuel to this chamber is also rigidly connected. The fuel can be two-component and consist of fuel and an oxidizing agent. Therefore, the combustion chamber may have two hydraulic connections with the control unit. The device may include an air intake device rigidly connected to the housing and placed in front of it. Air flows through this device to additional units, which, together with other units, are used to increase flight speed. However, the use of these nodes increases cumbersomeness.

Known aircraft described in patent No. 2494020, author Chasovskaya A.A. It may include the same nodes as in the aforementioned analogue. But it creates the opportunity to increase speed by increasing the frequency of ignition while maintaining the amount of fuel in each portion between ignitions. But the device also includes additional nodes that increase bulkiness.

Using the proposed device reduces bulkiness without reducing acceleration. This is achieved by introducing a hydraulic connection between the air intake device and the cone-shaped combustion chamber and the implementation in the combustion chamber, after spraying the oxidizing agent, mixing its atomized particles with an air stream before ignition using sprayed kerosene.

In figure 1 and in the text the following notation:

1 - device air intake

2 - housing

3 - control unit,

4 - conical combustion chamber,

5 - exhaust nozzle,

while the housing 2 is rigidly connected with the control unit 3 and with a cone-shaped combustion chamber 4 having two hydraulic connections with the aforementioned control unit 3 and hydraulic connection with the air intake device 1, as well as a rigid connection with the exhaust nozzle 5.

The operation of the device is as follows.

The initial movement of the aircraft is due to the supply of oxidizer and fuel in the form of kerosene from the control unit 3 to a cone-shaped combustion chamber 4, which has two hydraulic connections with the above-mentioned block 3. In the combustion chamber after the components are sprayed, the mixture forms, ignites and exits through the exhaust nozzle 5 rigidly connected with the tip of the cone-shaped combustion chamber 4. Air is also increased through the air intake device 1 located in the front of the housing 2 and tightly bound to it. Through this device, air in the form of a jet enters a cone-shaped combustion chamber 4, hydraulically connected to this device. As a result, after spraying the oxidizing agent, its atomized particles are picked up and mixed with an air stream. At the same time, the jet velocity does not decrease, but the amount of oxygen components increases before ignition using sprayed kerosene, which increases the flight speed. In addition, due to the use of kerosene as fuel, the combination of air-reactive and liquid-rocket processes in the combustion chamber 4 is ensured. Upon reaching a height of 20 km and the required speed, additional acceleration begins by carrying out ignitions with an increased frequency. Moreover, due to the effect on the walls of the chamber of pulsed ignitions, it is possible to increase the maximum amount of oxidizing agent and kerosene, at which reliability remains, depending not on the ignition frequency, but on the amount of ignited fuel between ignitions. Therefore, by choosing the maximum ignition frequency, you can achieve the maximum final speed. In addition, the acceleration is increased due to the presence of the relative motion of the body and the newly ignited fuel, relatively previously ignited, but not yet exiting the combustion chamber.

A use case is possible when movement to a height from which additional acceleration begins does not occur when an oxidizing agent arrives from the control unit, but only by drawing air into the combustion chamber.

In the proposed device, thanks to a preliminary increase in speed, it is possible, when using one engine and nozzle, to increase the final speed, which will improve the tactical and technical characteristics of aircraft during flights in the atmosphere and space.

Claims (1)

Aircraft, consisting of rigidly connected to the control unit body and a cone-shaped combustion chamber, rigidly connected to the exhaust nozzle at the end of the chamber, having two hydraulic connections with the control unit, and located in front of the air intake device body, characterized in that in the process of arrival into the combustion chamber of this air, the oxidizer components also enter it and after the oxidizer is sprayed, its atomized particles are mixed with an air stream before ignition with oschyu atomized kerosene.