RU2616095C1 - Aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: aircraft includes a control unit to output a pulsed or continuous voltages, a rectangular chamber with a shock-absorber inside with roundings between the walls. Two semicircular magnets are disposed at the chamber end rigidly connected with its side walls behind the springs of the spring valves with rounding at the end located in front of these roundings between the shock-absorber walls of the chamber. The entrances of the semicircular magnets are connected to the exits of the control unit.

EFFECT: increased speed of the aircraft.

1 dwg

Description

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

Known aircraft presented in patent No. 2363625, author Chasovskaya A.A. In it, fuel flows from the control unit into the combustion chamber. The control unit, the hydraulic output of which is in communication with the hydraulic input of the combustion chamber, issues commands for igniting portions of fuel. As a result, the pulsed outflows of the ignited fuel exit the combustion chamber. Two jet engines can be rigidly connected to the casing, with the help of which the initial movement of the apparatus begins. However, the magnitude of the acceleration may not always be sufficient.

Known aircraft, presented as a propulsion device in the patent No. 2532326, author Chasovskaya A.A. In it, unlike the aforementioned, two refractory spring valves and a shock absorber located inside a rectangular chamber are introduced, which can be represented as a rectangular chamber with a shock absorber inside, located inside the housing. In the initial state, the valves touch each other and do not pass fuel until it ignites. The shock absorber inside the rectangular chamber is hydraulically connected to the control unit. After fuel is supplied from the control unit, it ignites. As a result, the spring valves are pressed against the walls of the rectangular chamber. Repulsion of the body occurs when exposed to ignited fuel on the surface of the valves. Initially, the movement is due to the operation of jet engines rigidly connected to the body. Next, an increase in acceleration begins due to the excess of speed at the end of the body repulsion over the speed before repulsion, which is ensured by an increase in the kinetic energy during repulsion. This is explained by the fact that with the same push force of a moving object, its speed after the push will be the greater, the greater its speed before the push.

However, at the end of repulsion, the pressure of the ignited gases on the valves decreases, which leads to the presence of residual acceleration. Using the proposed device increases acceleration without compromising reliability. This is achieved through the use of a control unit with the possibility of issuing pulse or continuous voltages, a rectangular chamber with a shock absorber inside with curves between the walls, and the introduction of two semicircular electromagnets at the end of the chamber, rigidly connected to its side walls behind the spring springs with rounded ends at the end, located before these curves between the walls of the shock absorber of this chamber, and the inputs of the semicircular electromagnets are connected to the outputs of the said control unit.

In FIG. 1 and the following notation is used in the text:

1 - housing;

2 - control unit with the possibility of issuing pulse or continuous voltages;

3 - a rectangular chamber with a shock absorber inside with curves between the walls;

4, 5 - spring valves with curves at the end;

6, 7 - semicircular electromagnets;

8, 9 - jet engines, while the housing 1 is rigidly connected with the jet engines 8, 9 and with a rectangular chamber located inside it with a shock absorber inside with curves between the walls 3 having a hydraulic inlet connected to a hydraulic outlet located inside the control unit c the possibility of issuing pulsed or continuous voltages 2 having an output connected to the inputs of semicircular electromagnets 6, 7.

The device operates as follows.

In the initial period of time, the movement is carried out using jet engines 8, 9, rigidly connected with the housing 1.

Next, portions of fuel from the hydraulic output of the control unit with the possibility of issuing pulse or continuous voltages 2 are fed to the hydraulic input of the shock absorber with curves between the walls inside the rectangular chamber 3. A rectangular chamber with a shock absorber inside with curves between the walls 3, together with the aforementioned control unit, are rigidly connected with case 1 and placed inside it. On commands from the control unit 2, the fuel ignites and exits the housing 1 through the curves of the spring valves 4, 5. Ignited gases act on the spring valves with curves at the end. The spring valves are pressed against the inner walls of the chamber 3 without touching the semicircular electromagnets 6, 7 located behind the valve springs, rigidly connected to the walls of the chamber 3 and placed behind the said curvatures between the walls. Thanks to the electromagnets, the valves are pressed against the walls of the chamber until the supply of voltage to the electromagnets of this chamber 3 at the end of it is stopped, behind the spring springs of the valves with rounding behind 4, 5, behind the rounding between the shock absorber walls of the aforementioned chamber 3.

The rounding between the walls in the shock absorber provides a smooth movement of ignited gases, which also act on the front wall of the shock absorber, increasing the repulsion of the body before the exit of these gases, which also act on the front wall of the shock absorber, increasing the repulsion of the body before these gases exit the chamber. In this case, the perimeter inside the rectangular chamber 3, where the valves and electromagnets are located, is increased due to the absence of the aforementioned curvatures between the walls of the chamber in it. The control unit 2 generates voltage pulses or continuous voltage in two semicircular electromagnets 6, 7, which are magnetized and enhance the attraction of the spring valves 4, 5 to the side walls of the chamber 3 during the ignition of gases exiting through the curves at the end of the spring valves acting as nozzles. In connection with the foregoing, the amount of residual fuel in the shock absorber decreases, since the amount of output of ignited gases increases, without increasing the amount of incoming fuel from the control unit. This, as already noted, is provided by an increase in the force and time of pressing the valves to the walls of the chamber. In addition, the movement of the housing 1 is relative to the spring valves, enhancing repulsion. The speed of movement before a new repulsion exceeds the speed of movement before the previous repulsion, and the higher the speed, the greater the magnitude of repulsion, that is, the speed at the end of repulsion must exceed the speed before repulsion. Thus, we can conclude that the speed with a pulse outflow of fuel will be higher than with a continuous one. The flow of ignited fuel is smooth due to the rounded ends of the valves 4, 5. With a smaller valve size, the force required for its attraction is reduced, and therefore, the voltage to the electromagnets can be reduced. With a constant voltage from the control unit supplied to the electromagnets, a continuous outflow of ignited fuel can be carried out, where, as in the pulsed mode, it is possible to provide flight both with an increased and a reduced amount of incoming fuel to the shock absorber. It is possible to perform a pulsed mode with a constant voltage to the electromagnets, which will provide fuel economy, with an increased acceleration time, where further the speed will also be increased more intensively than with a continuous expiration, which will provide an economic effect. In addition, the reliability increases with an increased amount of fuel in the shock absorber, the divergence between the valves increases, and therefore, the safety of the outflow of ignited gases is also ensured.

The proposed method can be used in other products, including those set forth in the patents of the author. It is possible to use pulsating fuel outflows during the ignition period in the shock absorber with a frequency of, for example, 100-500 Hz. This creates the opportunity to increase the amount of incoming fuel between the pulsations, and hence the acceleration. Thus, the introduction of the proposed device will improve the tactical and technical characteristics of aircraft.

Claims (1)

Aircraft comprising a hull, two jet engines rigidly connected to the hull, a control unit located inside the hull, a rectangular chamber with a shock absorber inside, two spring valves with rounded ends, rigidly connected to the walls of the rectangular chamber, characterized in that it is used: the possibility of issuing pulsed and continuous voltages, a rectangular chamber with a shock absorber inside with curves between the walls at the end of the chamber, as well as two semicircular electromagnets at the end chambers rigidly connected with its side walls behind the spring of the spring valves with rounded ends located in front of these curves between the walls of the shock absorber of the chamber, and the inputs of the semicircular electromagnets are connected to the output of the said control unit.

Images