Variable thrust sequential detonation rocket-based engine and aircraft

Abstract

The invention provides a variable-thrust continuous detonation rocket-based engine and an aircraft, and relates to the technical field of aviation. The variable-thrust continuous detonation rocket-based engine comprises an inner core body; an outer cylinder body is provided with a hollow cavity which is axially through, and the hollow cavity is used for being arranged on the outer side of the inner core body in a sleeving manner; a first gap is formed between the outer wall of the inner core and the inner wall of the outer cylinder, and the first gap is used for forming an annular combustion chamber; at least one pre-detonation pipe structure is arranged on the outer cylinder body; an air collection cavity end cover is arranged at the head end of the inner core body and the head end of theouter cylinder body and is connected with the inner core body and the outer cylinder body; a fuel inlet is formed in the side wall of the air collecting cavity end cover, and the fuel inlet is connected with the annular combustion chamber; an oxidant inlet is formed in the end surface of the air collection cavity end cover, and the oxidant inlet is connected with the annular combustion chamber; afuel storage tank is connected with the fuel inlet through a first adjustable venturi tube and is used for adjusting the amount of fuel entering the annular combustion chamber; and an oxidant storagetank is connected with the oxidant inlet through a second adjustable venturi tube and is used for adjusting the amount of the oxidant entering the annular combustion chamber.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a variable-thrust continuous detonation rocket-based 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, the propulsion performance is poor and the structure is complex in various...

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Problems solved by technology

[0005] The purpose of the present invention is to provide a variable thrust continuous detonation rocket-based engine and aircraft to solve technical problems such as poor propulsion performance and complex structure of the engine in the prior art

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