RU2312045C1 - Flying vehicle - Google Patents

Abstract

FIELD: aero-space engineering; flying vehicles for flights in atmosphere and in space.

SUBSTANCE: proposed flying vehicle has body, main and additional shock absorbers, control unit of main shock absorber, jet engines, exhaust nozzle and pipes. Body of flying vehicle has recess where additional mechanical shock absorber is located in its front cylindrical part. Rigidly connected with this shock absorber at the rear is cylindrical plate. Main shock absorber is made in form of tapering recess behind said plate; exhaust nozzle is mounted at its end. Bent exhaust pipes of main shock absorber are made inside body; two jet engines are rigidly connected with flying vehicle body.

EFFECT: simplified construction and reduced sizes of flying vehicle.

1 dwg

Description

The invention relates to aerospace engineering, in particular to propulsion systems of aircraft (LA) for flights in the atmosphere and space.

Known LA Pat. RU 2134218 C1 (Chasovskoy A.A.), in which the reciprocating movement of the piston with a jet engine inside the cylinder, which is rigidly connected to the body. The piston is repelled in the opposite direction by means of a shock absorber, where the shock absorber control unit carries out a metered fuel supply.

Known LA Pat. RU 2270143 C1 (Chasovskoy A.A.), adopted for the prototype. This aircraft contains a housing, main and additional shock absorbers, a control unit for the main shock absorber hydraulically connected with this shock absorber, jet engines located behind the shock absorbers, exhaust nozzles and pipes.

Due to the presence of an extended cylinder with a piston, this aircraft is quite complex and cumbersome.

The objective of the invention is to simplify the design of the aircraft and reduce its size.

This problem is solved by the fact that a recess is made in the body of a known aircraft, in the cylindrical front part of which there is an additional mechanical shock absorber rigidly connected to the rear of the cylindrical plate, while the main shock absorber is made in the form of a cone-shaped narrowing of the body recess behind the plate, at the end of which there is an exhaust nozzle, curved exhaust pipes of the main shock absorber are made inside the body, and two jet engines are rigidly connected to the body.

The invention is illustrated in the drawing. In this case, the following notation is used in the drawing and in the text:

1 - housing;

2 - control unit of the main shock absorber;

3 - recesses in the housing;

4 - additional mechanical shock absorber;

5, 6 - curved exhaust pipes of the main shock absorber;

7 - a cylindrical plate;

8 - the main shock absorber in the form of a cone-shaped narrowing of the recess 3;

9, 11 - jet engines;

10 - exhaust nozzle.

The housing 1 is rigidly connected with jet engines 9, 11 and an exhaust nozzle 10 mounted behind the main shock absorber 8.

An additional mechanical shock absorber 4 is mounted inside the front cylindrical part of the recess 3, to which the plate 7 is rigidly connected. The main shock absorber 8 is hydraulically connected to its control unit 2.

The operation of the device is as follows.

The initial movement is attached to the aircraft using jet engines 9, 11. The mechanical shock absorber 4 in the initial state is in an elongated (unclenched) state.

To carry out further acceleration using the control unit 2 of the shock absorber 8, the gases supplied to the shock absorber 8 are ignited from the output of the control unit 2 through the hydraulic connection of the block and the shock absorber.

Hot gases exert pressure on the conical walls of the shock absorber 8 and the surface of the plate 7. Due to this, there is some relative movement of the parts of the aircraft: the plate 7 in the compression direction of the shock absorber 4, the housing 1 in the opposite direction. The latter contributes, according to the general principles of this aircraft acceleration scheme, to an increase in the efficiency of jet engines 9, 11. This is expressed mainly in a decrease in the total fuel consumption, compared to traditional vehicles, with the same increment in aircraft flight speed.

Other thermodynamic efficiency factors of the proposed aircraft jet acceleration system are also possible.

Exhaust gases exit through the exhaust nozzle 10 and curved exhaust pipes 5, 6, providing an additional impulse for the outflow of ignited gases, and thanks to the curved exhaust pipes and compression of the mechanical shock absorber 4, the presence of residual exhaust gases is eliminated and their complete exhaust is ensured.

After repeated elongation (decompression) of the mechanical shock absorber 4 and receipt of a sufficient amount of fuel from the control unit 2 of the shock absorber 8 to control this shock absorber, gases are ignited by this block. Next, repulsive cycles following each other are repeated.

As the kinetic energy of the aircraft increases, so does its speed. The repulsion frequency depends on the amount of fuel to ignite gases per unit of time in the shock absorber 8 from the shock absorber control unit 2.

In the proposed device, in the absence of a cylinder with a piston, it is possible to achieve simplification of the design and reduce the size of the aircraft.

Claims (1)

Aircraft comprising a body, main and additional shock absorbers, a control unit for the main shock absorber hydraulically connected with this shock absorber, jet engines located behind the shock absorbers, exhaust nozzles and pipes, characterized in that the body has a recess in the cylindrical front of which there is an additional a mechanical shock absorber rigidly connected to the rear of the cylindrical plate, while the main shock absorber is made in the form of a cone-shaped narrowing of the housing recess and said plate, the end of which is installed exhaust nozzle, curved main exhaust damper formed within the housing, and the housing are rigidly connected two jet engine.