A pumping and extrusion integrated fuel system for rbcc engines based on hydrogen peroxide

Abstract

The invention provides a hydrogen peroxide-based RBCC engine pumping and extruding integrated fuel system, comprising a supercharging unit, a supply unit, an engine body and a connecting pipeline unit; the supercharging unit is used to supercharge the supply unit; The supply unit is connected with the engine body through the connection pipeline unit and supplies propellant to the engine body. The present invention overcomes the disadvantages of complex and bulky systems caused by separate supply of fuel for rocket thrust chambers and ram combustion chambers, integrates the respective advantages of hydrogen peroxide and kerosene propellants, and has a high density ratio, meeting the requirements of integrated fuel supply and integration of combined engines. The integrated cooling structure design requires that the system use and maintenance technology is mature, and the system composition is relatively simple and easy to implement.

Description

technical field [0001] The invention belongs to the field of mechanical engines and relates to an engine fuel system, in particular to a hydrogen peroxide-based RBCC engine pumping and extruding integrated fuel system suitable for long-time work. Background technique [0002] The Rocket Based Combined Cycle (RBCC) engine is an advanced propulsion system based on a reusable single-stage orbiting vehicle. It combines the high thrust-to-weight ratio of the rocket engine and the high specific impulse of the ramjet engine. The ability to work in the full-speed domain has been researched with the support of the General Armament Department. [0003] At present, the RBCC engine is mainly composed of the air inlet, the rocket thrust chamber, the ram combustion chamber, the tail nozzle, and the fuel supply and regulation system; The components are supplied separately. On the one hand, the system is complex and huge, which greatly restricts the engineering application of the engine; o...

AI Technical Summary

Problems solved by technology

[0003] At present, the RBCC engine is mainly composed of the air inlet, the rocket thrust chamber, the ram combustion chamber, the tail nozzle, and the fuel supply and regulation system; The components are supplied separately. On the one hand, the system is complex and huge, which greatly restricts the engineering application of the engine; on the other hand, for the combined engine, under the limited propellant flow rate, the cooling of the overall structure cannot be achieved by supplying it separately. , the cooling structure of the overall design must be considered, in this case, the use of an integrated fuel supply system is the only option

[0004] Therefore be badly in need of a kind of RBCC engine pump pressure that can overcome the fuel supply and adjustment system that existing combined engine rocket thrust chamber and ram-combustion chamber are provided separately and solve the deficiencies of separate supply and adjustment, complex system and inability to carry out integrated cooling. pressure integrated fuel system

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