Thrust vector control continuous detonation air-breathing engine and aircraft

Abstract

The invention provides a thrust vector control continuous detonation air-breathing engine and an aircraft, and relates to the technical field of aviation. The engine comprises an inner core body, a outer cylinder body, a flow guide cone, an outer ring end cover, a fuel storage tank and at least two adjustable venturi tubes, wherein the outer cylinder body is provided with a hollow cavity which isaxially through; a first gap is formed between the outer wall of the inner core body and the inner wall of the outer cylinder body; at least one pre-detonation pipe structure is arranged on the outercylinder body; the flow guide cone is arranged at the head end of the inner core body, and is connected with the inner core body; the outer ring end cover is arranged at the head end of the outer cylinder body, and is connected with the outer cylinder body; a first stamping gap communicated with a annular combustion chamber is formed between the outer wall of the flow guide cone and the inner wallof the outer ring end cover; a fuel inlet is formed in the side wall of the outer ring end cover, and an annular fuel cavity is formed in the outer ring end cover, and the annular fuel cavity is divided into at least two fuel unit cavities in the circumferential direction; and the fuel inlet communicated with the first stamping gap through the fuel unit cavity; the fuel storage tank is connectedwith each fuel cell cavity through the adjustable venturi tubes.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a thrust vector controlled continuous detonation air-breathing engine and an aircraft. Background technique [0002] The rocket launcher is used to send artificial earth satellites, manned spacecraft, space stations or interplanetary probes into predetermined orbits. The last stage has an instrument cabin, which houses the guidance and control system, telemetry system and launch site safety system. [0003] In the design and manufacture of launch vehicles, reasonable adjustment of engine thrust is a necessary means to achieve active control capabilities such as flight environment control and flight trajectory optimization of launch vehicles. Not only liquid engines must have thrust adjustment capabilities, but solid engines must also pass reasonable design. for thrust control. [0004] However, in the prior art, among various engines used on aircraft such as launch vehicles, ...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a continuous detonation air-breathing engine and aircraft with thrust vector control, so as to solve the technical problems of poor propulsion performance and complex structure of the engine in the prior art

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