Fuel cell feeding system for rocket engine

A rocket engine and fuel cell technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of short development cycle and high flexibility requirements of small launch vehicles, and achieve slow start-up speed and reduce system complexity speed, easy to control the effect

Pending Publication Date: 2019-12-20
HARBIN INST OF TECH
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problem that the existing rocket engine supply system cannot meet the short development cycle and high flexibility requirements for small launch vehicles, and further provides a fuel cell supply system for rocket engines

Method used

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  • Fuel cell feeding system for rocket engine

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specific Embodiment approach 1

[0014] Specific implementation mode one: combine figure 1 Describe this embodiment, a fuel cell supply system for a rocket engine, which includes a fuel tank 1, an electric fuel pump 2, an oxidant tank 3, an electric oxidant pump 4, a solid oxide fuel cell 5, an electric energy control distribution system 6, Motor 7, accumulator 8, combustion chamber 9 and main nozzle 10, the outer wall of main nozzle 10 is provided with some cooling passages 11, and described combustion chamber 9 comprises fuel injector and oxidant injector,

[0015] The inlet of the electric fuel pump 2 communicates with the fuel tank 1, and the outlet of the electric fuel pump 2 communicates with the inlets of a plurality of cooling channels 11 respectively, and the outlet of each cooling channel 11 is connected with the inlet of the anode 5-1 of the solid oxide fuel cell 5 and The fuel injector communicates; the inlet of the electric oxidizer pump 4 communicates with the oxidant tank 3, and the outlet of t...

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Abstract

The invention discloses a fuel cell feeding system for a rocket engine, belongs to the technical field of rocket engines, and solves the problems that existing feeding systems for rocket engines cannot meet requirements for shorter development period and higher flexibility of small carrier rockets. An inlet of an electric fuel pump communicates with a fuel tank, an outlet of the electric fuel pumpcommunicates with inlets of multiple cooling channels, and an outlet of each cooling channel communicates with an anode inlet of a solid oxide fuel cell and a fuel injector; and an inlet of an electric oxidizing agent pump communicates with an oxidizing agent tank, an outlet of the electric oxidizing agent pump communicates with a cathode inlet of the solid oxide fuel cell and an oxidizing agentinjector separately, the solid oxide fuel cell is electrically connected with an electric energy control distribution system, the electric energy control distribution system is electrically connectedwith a storage battery and a motor separately, and the motor, the electric oxidizing agent pump and the electric fuel pump are coaxially and fixedly connected.

Description

technical field [0001] The invention relates to a fuel cell supply system for a rocket engine, which belongs to the technical field of rocket engines. Background technique [0002] In recent years, there has been an upsurge in micro-satellite application research at home and abroad, and the world's aerospace industry has begun to develop low-cost, high-reliability, and more flexible small launch vehicles for the micro-satellite launch service market. The supply system is an important part of the rocket engine, and the conventional supply methods are extrusion and pump systems. The extrusion system is relatively simple, but requires high-pressure gas / gas cylinders / tanks, so the structural quality of the system is relatively large, and it is generally suitable for propulsion systems with small thrust and low demand for total impulse. The structural mass of the pump-pressed propulsion system is relatively small, but the engine requires a complex turbopump system, which require...

Claims

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Application Information

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IPC IPC(8): F02K9/46F02K9/56F02K9/60
CPCF02K9/46F02K9/563F02K9/60
Inventor 秦江郭发福党朝磊姬志行章思龙
Owner HARBIN INST OF TECH
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