Continuous detonation air-breathing engine with variable thrust and aircraft

Abstract

The invention provides a variable-thrust continuous detonation suction type engine and an aircraft, and relates to the technical field of aviation. The variable-thrust continuous detonation suction type 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, 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; a flow guide cone is arranged at the head end of the inner core body, and is connected with the inner core body;an outer ring end cover is arranged at the head end of the outer cylinder body and is connected with the outer cylinder body, and the outer ring end cove is used for being arranged on the outer side of the flow guide cone in a sleeved mode; a first stamping gap connected with the annular combustion chamber is formed between the outer wall of the flow guide cone and the inner wall of the outer ringend cover; and a fuel inlet is connected with the first stamping gap. The variable-thrust continuous detonation suction type engine further comprises a fuel storage tank and an adjustable venturi tube, the fuel storage tank is connected with the fuel inlet through an adjustable venturi tube and is used for adjusting the amount of fuel 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 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, the propulsion performance is poor and the structure is complex in variou...

AI Technical Summary

Problems solved by technology

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

Images