RU2667838C1 - Aircraft - Google Patents

Abstract

FIELD: aerospace engineering.SUBSTANCE: invention relates to aerospace engineering. Aircraft consists of two jet engines rigidly connected to the body, cone-shaped combustion chamber, rigidly connected to the exhaust nozzle at the end of the combustion chamber. In the aircraft, a control unit with a laser is used and a light guide is inserted with consecutive branches within the combustion chamber and having an optical input, connected to the optical output of the control unit with a laser having optical outputs connected through refractory transparent inserts at the end of the respective branches, rigidly connected to the inner side of the wall of the combustion chamber, with optical inputs of the corresponding sections of this chamber.EFFECT: technical result of the invention is higher acceleration of an aircraft.1 cl, 1 dwg

Description

The invention relates to the field of aerospace engineering and can be used for flights in the atmosphere and in space. Known aircraft, described in patent No. 2494020 by Chasovskaya A.A., the initial movement of the device can be imparted using jet engines rigidly connected to the hull. A cone-shaped combustion chamber with an exhaust nozzle behind it is also rigidly connected with it. The combustion chamber is in fluid communication with the control unit, supplying and igniting the fuel in continuous or in pulsed mode. However, acceleration is not always enough.

Known aircraft described in the patent of the author No. 2560224. In it, in contrast to the aforementioned, a higher pulse repetition rate is used in the combustion chamber. In this case, the pulse energy is stored regardless of the frequency. Therefore, the amount of ignited fuel and acceleration can be increased. However, the magnitude of the acceleration is not always sufficient.

Using the proposed device increases acceleration without compromising reliability. This is achieved by using a laser control unit and a fiber with successive branches having an optical input connected to the optical output of the control unit and having optical outputs connected through refractory, transparent inserts at the end of the corresponding branches rigidly connected to the inner side of the combustion chamber wall , with optical inputs of the corresponding sections of this camera.

In FIG. 1 and in the text the following notation of elements

1 - case

2 - control unit with laser

3.4 - jet engines

5 - conical combustion chamber

6 - light guide with branches following each other

7 - refractory transparent inserts

8 - an exhaust nozzle _5, while the housing 1 is rigidly connected to a cone-shaped combustion chamber 5 with an exhaust nozzle 8 at the end, with jet engines 3.4 and a control unit with a laser 2, the hydraulic output of which is connected to the hydraulic input of the combustion chamber 5 having an optical output associated with the optical input of the fiber with successive branches having optical outputs connected through refractory transparent inserts 7 at the end of the branches, rigidly connected to the inner side of the wall of the combustion chamber 5 with corresponding sections of this combustion chamber 5.

The device operates as follows: the initial movement of the apparatus is given using jet engines 3, 4 rigidly connected to the housing 1, the cone-shaped combustion chamber 5 is also rigidly connected to the latter with an exhaust nozzle behind 8. The combustion chamber 5 is in fluid communication with the control unit with the laser 2 The laser ignites the fuel in a continuous or pulsed mode using a fiber with subsequent branches 6. The combustion chamber 5 can receive not only continuous light energy, but also with ichennoy repetition frequency of the light pulses. In this case, regardless of the frequency, the pulse energy is stored. Therefore, the amount of ignited fuel and acceleration can be increased. The light energy from the control unit with the laser 2 enters the fiber 6 passing inside the wall of the combustion chamber 5. The branches are shown as dots in FIG. 1, as well as refractory transparent inserts combined with them 7. Branches can be perpendicular to a horizontal plane passing through the chamber. Therefore, the fuel simultaneously ignites inside the combustion chamber 5. In this case, the inserts 7 at the end of the branches of the light guide 6 are rigidly connected to the inner side of the wall of the combustion chamber 5. Thus, the ignition of the fuel in the combustion chamber 5 occurs simultaneously and its propagation speed increases at an increased temperature. Therefore, the increase and the rate of exit of ignited fuel from the nozzle 8. The design of the inserts 7 is similar to the design of the laser lenses.

Due to the use of inserts 7 at the ends of the fiber guide, reliability is also provided. In addition, the newly ignited fuel moves faster than the previously ignited one, which further ignites as it approaches nozzle 8, which increases the acceleration more. Thus, an accelerated flight mode is provided.

Claims (1)

Aircraft, consisting of two jet engines rigidly connected to the body, a cone-shaped combustion chamber, rigidly connected to the exhaust nozzle at the end of the combustion chamber, characterized in that a control unit with a laser is used and a light guide is inserted with branches following each other inside the combustion chamber and having the optical input associated with the optical output of the laser control unit having optical outputs coupled through refractory transparent inserts at the end of the respective branches is rigidly connected associated with the inner side of the combustion chamber wall, with the optical inputs of the respective portions of the chamber.

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