Hydrogen-peroxide-based RBCC (Rocket Based Combined Cycle) engine pressure pumping and squeezing integrated fuel system

Abstract

The invention provides a hydrogen-peroxide-based RBCC (Rocket Based Combined Cycle) engine pressure pumping and squeezing integrated fuel system. The hydrogen-peroxide-based RBCC engine pressure pumping and squeezing integrated fuel system comprises a pressurization unit, a supplying unit, an engine body and a connecting pipeline unit; the pressurization unit is used for performing pressurization on the supplying unit; the supplying unit which is connected with the engine body through the connecting pipeline unit supplies propellant to the engine body. The hydrogen-peroxide-based RBCC engine pressure pumping and squeezing integrated fuel system has the advantages of overcoming disadvantages of a complex and huge system due to the fact that a rocket thrust chamber and a stamping combustion chamber separately supply fuel, synthesizing respective advantages of the hydrogen peroxide and kerosene propellant, being high in density specific impulse, satisfying combination engine design requirements for integrated fuel supplying and an integrated cooling structure and being mature in utilization and maintenance technology, relatively simple in system composition and easy to achieve.

Description

technical field [0001] The invention belongs to the field of mechanical engines and relates to an engine fuel system, in particular to an RBCC engine pumping / extruding integrated fuel system suitable for long-time work and based on hydrogen peroxide. Background technique [0002] The Rocket Based Combined Cycle (RBCC) engine is an advanced propulsion system based on a reusable single-stage orbiting vehicle, which 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 airspace and 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 app...

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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, there is an urgent need for a RBCC engine pumping / squeezing system that can overcome the separate fuel supply and regulation system of the existing combined engine rocket thrust chamber and ram combustion chamber, and solve the shortcomings of separate supply and regulation, complex systems, and inability to perform integrated cooling. pressure integrated fuel system

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