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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

Inactive Publication Date: 2016-08-31
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] The purpose of the present invention is to provide a RBCC liquid rocket engine propellant supply system with a large adjustment ratio to solve the problem that the existing propellant supply system cannot be integrated into the RBCC, and the propellant flow rate and mixing ratio cannot be adjusted in a large range at the same time

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

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Embodiment Construction

[0021] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0022] The present invention provides a kind of RBCC liquid rocket engine propellant supply system with large adjustment ratio, see figure 1 , including an oxidizer supply system A, a fuel supply system B and a gas blow-off system D respectively connected to the thrust chamber of the engine, and the fuel supply system B is also connected to a fuel pressurization system C;

[0023] The fuel supply system B includes a fuel tank 1 for supplying fuel to the thrust chamber, and a fuel flow regulating system for regulating the propellant flow and its mixing ratio is arranged on the output pipeline of the fuel tank 1, and the fuel flow regulating system includes a column The plunger pump 2 is connected with a motor drive device for controlling its action.

[0024] Wherein, the fuel storage tank 1 is connected to the plunger pump 2 through the filte...

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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.

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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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/46F02K9/56F02K9/60
CPCF02K9/46F02K9/566F02K9/605
Inventor 何国强白晶晶刘洋
Owner NORTHWESTERN POLYTECHNICAL UNIV
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