Propellant supply system for RBCC large regulating-ratio liquid-propellant rocket engine

A liquid rocket and supply system technology, applied in the direction of rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems that the propellant supply system cannot be integrated, and the propellant flow rate and mixing ratio cannot be adjusted in a wide range, so as to achieve reduction Small negative mass, reduce system cost, ensure stable work effect
CN105909424AInactive Publication Date: 2016-08-31NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
NORTHWESTERN POLYTECHNICAL UNIV
Publication Date
2016-08-31
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention aims to provide a propellant supply system for an RBCC large regulating-ratio liquid-propellant rocket engine. The system comprises an oxidizing agent supply system, a fuel supply system and a gas blowing-down system, and the systems communicate with the engine respectively, wherein the fuel supply system is also connected to a fuel pressurization system. The fuel supply system comprises a fuel storage tank used to provide fuel to the engine, wherein a fuel flow regulating system used to adjust a flow rate and a mixing rate of a propellant is disposed on an output pipeline of the fuel storage tank; and the fuel flow regulating system comprises a plunger pump, and the plunger pump is connected to a motor drive device used to control actions of the engine. The system solves the problems that an existing propellant supply system cannot be integrated in an RBCC, and the flow rate and the mixing rate of the propellant cannot be adjusted within a large scope simultaneously.
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Description

technical field

[0001] The invention belongs to the technical field of propellant supply systems, and relates to a propellant supply system for RBCC liquid rocket engines with a large adjustment ratio. Background technique

[0002] At present, there are relatively few studies on the large-scale adjustment of the propellant flow rate and mixing ratio of liquid rocket engines. The general research methods for such problems are mainly (1) designing a full-extrusion propellant supply system with an adjustable cavitation venturi (flow regulating valve) and a variable cross-section adjustable injector; (2) ) In the pump-pressed propellant supply system, a large number of pneumatic valves, pressure stabilizers and flow regulators that can preset working conditions are used to increase the adaptability of liquid rocket engines to variable working conditions.

[0003] The typical supply system design method for this kind of problem is mainly the lunar module descent engine (LMDE) de...

Claims

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