RU2704639C1 - Aircraft - Google Patents

Abstract

FIELD: aerospace engineering.

SUBSTANCE: aircraft consists of rigidly connected to housing control unit and two jet engines, bent and turned in different sides of exhaust pipes for outlet of inflamed fuel, which also goes through exhaust nozzle arranged in front of this nozzle and rigidly connected to it cone-shaped combustion chamber with cone-shaped ledge in front, rigidly coupled with said exhaust pipes and having hydraulic connection with control unit. Apparatus uses a control unit which increases the repetition rate of successive fuel portions, which stores a certain amount of fuel output in each portion and increases its ignition in said combustion chamber. Unit of bent cone-shaped combustion chambers is introduced, the period of doses of fuel from which also does not exceed the time of passage of one dose inside the said central combustion chamber and having hydraulic connection with the side chambers. There is a nozzle in the rear part of the central chamber.

EFFECT: increased acceleration.

1 cl, 1 dwg

Description

The invention relates to the field of aerospace engineering, in particular to the propulsion systems of aircraft for flights in the atmosphere and space. Known aircraft described in patent No. 2363625 author Chasovskaya A.A. It increases acceleration without reducing reliability and increasing bulkiness. Two exhaust pipes bent and turned in different directions, through which ignited fuel passes, also passing through the exhaust nozzle, are rigidly connected to the body. The fuel comes from the control unit and then ignites. However, increasing acceleration is not always enough. Known aircraft, described in patent No. 2494020 by Chasovskaya A.A. In it, in contrast to the aforementioned, a block of curved conical combustion chambers is introduced. However, it also does not always increase acceleration. Using the proposed device provides a sufficient increase in acceleration. This is achieved by introducing a block of curved cone-shaped combustion chambers, the period of the following doses of fuel from which also does not exceed the transit time of the previous dose inside the central combustion chamber during successive periods of these doses and having a hydraulic connection behind the side chambers.

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

1 - housing;

2 - control unit;

3 - a block of curved conical combustion chambers; 4.5. - jet engines;

6 - a central conical combustion chamber;

7 - an exhaust nozzle, while the housing 1 is rigidly connected with jet engines 4, 5 and a control unit 2, a central cone-shaped combustion chamber 6 with a cone-shaped protrusion in front, a block of curved cone-shaped combustion chambers 3, an exhaust nozzle 7 having a hydraulic connection with the chamber 6 and block 3.

The device operates as follows. The initial movement of the aircraft is attached using jet engines 4,5. For further acceleration using the control unit 2 provides an increased repetition rate of the metered fuel in a cone-shaped combustion chamber 6 with a cone-shaped protrusion in front. This arrangement ensures optimal flow of ignited gases inside the chamber. After ignition of the fuel, it begins to exit from the curved cone-shaped combustion chambers 3, turned in different directions and through an exhaust nozzle 7 located at the end of the combustion chamber 6. The period of following doses of fuel entering the combustion chambers does not exceed the time of passing the previous dose of fuel from the combustion chamber . Therefore, before the end of the release of the ignited part of the fuel from the combustion chamber, the next portion of fuel begins to flow from the control unit 2, hydraulically connected to the combustion chamber 6. As a result, after ignition of this portion of the fuel, it begins to interact with the previously ignited first portion of the fuel. As a result, the exit of ignited gas through the block of curved cone-shaped combustion chambers 3 is accelerated and, consequently, the movement of the housing 1 is accelerated. As the next portion of the fuel flows, the acceleration increases and the traction and repulsive forces of the apparatus increase with an increased repetition rate of the portion of fuel, i.e. during the next after other periods of these doses. And the higher this frequency, the greater the repulsive force while maintaining reliability. This increases the rate of exit of flammable gases through the exhaust nozzle 7 and increases the speed.

This ensures an increase in the economic effect. This is explained by the fact that there is a relative motion of the housing 1 and the new ignited mass relative to the previous ignited mass. The movement of the housing 1 is ensured by the release of ignited fuel through a curved block of cone-shaped combustion chambers 3. At the same time, the acceleration of the mass and the casing increases in the process of new fuel flows following one after another and enhances the ignition of the mass, while maintaining the reliability of the combustion chamber.

The proposed device can be used when flying in the atmosphere and in space. An increase in flight speed will reduce the time for the delivery of passengers and goods to specified areas without increasing fuel consumption and compromising reliability. Thus, the use of the proposed device expands the functionality of aircraft and provides sufficient acceleration, which reduces the time of interplanetary flights.

Claims (1)

Aircraft consisting of rigidly connected to the control unit body and two jet engines bent and turned in different directions of the exhaust pipes to exit the ignited fuel, which also exits through the exhaust nozzle located in front of this nozzle and the cone-shaped combustion chamber rigidly connected to it protrusion in front, rigidly connected also with the aforementioned exhaust pipes and having a hydraulic connection with the control unit, characterized in that the control unit is used, increasing corresponding to the frequency of successive portions of fuel, preserving a certain amount of fuel delivered in each portion and providing an increase in its ignition in the aforementioned combustion chamber, a block of curved cone-shaped combustion chambers is introduced, the period of following doses of fuel from which also does not exceed the passage time of one dose inside the aforementioned central combustion chamber and having hydraulic communication with side chambers, and at the end of the Central chamber there is a nozzle, placed a pose di cameras.

Images