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Repeated starting rocket engine and starting method

A technology for starting rockets and engines, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc. It can solve the problems of complex starting structure, unstable rocket engine multiple starts, etc., and achieve the effect of simplifying the starting structure

Inactive Publication Date: 2019-07-12
BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Therefore, the technical problem to be solved in the present invention is to overcome the technical defects of rocket motor multiple start instability and complex starting structure in the prior art, thereby providing a multiple start rocket motor and engine start method

Method used

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Effect test

Embodiment 1

[0040] Such as figure 1As shown, the present embodiment provides a multiple-start rocket engine, which includes: a thrust chamber 1; pump gas inlet and turbopump exhaust port, wherein the turbopump fuel outlet and the turbopump oxidant outlet are respectively communicated with the thrust chamber 1; the gas generator 15 has a generator oxidizer inlet and a generator fuel inlet, And the gas outlet of the generator, wherein the gas outlet of the generator communicates with the gas inlet of the turbo pump, and drives the turbo pump 2 to run by providing gas in the turbo pump 2; the first pump 16, whose inlet is connected with the gas inlet of the turbo pump The oxidant outlet of the turbo pump is communicated with the oxidant inlet of the generator, and the first pump 16 is used to open before the operation of the turbo pump 2 to provide oxidant to the gas generator 15; the second pump 17, the inlet of which communicates with the fuel outlet of the turbo pump, and the outlet of w...

Embodiment 2

[0055] This embodiment provides a rocket, which has the multiple-start rocket engine described in Embodiment 1. The rocket engine it uses is the gas generator pumping medium to realize the start of the turbopump, which can realize multiple stable starts of the rocket engine, and because no additional high-pressure gas starter or gunpowder starting device is required, it simplifies the start of the rocket. Starter structure.

Embodiment 3

[0057] The present embodiment provides a method for starting a rocket engine, which includes the following steps: when starting, the first pump 16 is used to introduce the oxidizer and the fuel from the outlet of the turbo pump to the gas generator 15 through the first pump 16; After the gas generator 15 ignites and burns to generate gas to drive the turbine pump 2 to rotate, stop the work of the first pump and the second pump; the turbo pump 2 works to supply oxidant and fuel to the thrust chamber 1 and the gas generator 15; the thrust chamber 1 ignites and burns to generate Thrust completes rocket motor start.

[0058] In the method for starting a rocket engine provided in this embodiment, the medium is drawn from behind the turbopump 2 to supply the generator, and the generator is ignited and burned to generate a certain pressure of gas to drive the turbopump 2 to rotate. The turbopump works until the engine reaches a certain working condition, and the turbopump is The gene...

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Abstract

The invention relates to the technical field of aerospace propulsion, in particular to a repeated starting rocket engine and a starting method. According to the repeated starting rocket engine, an oxidizing agent and fuel are led out of the rear end of a turbopump, a generator is ignited to generate flue gas at a certain pressure so as to drive the turbopump to rotate, and repeated starting of therocket engine is achieved. The turbopump can be started in the mode of pumping media to the fuel gas generator, repeated stable starting of the rocket engine can be realized and the starting structure is simplified.

Description

technical field [0001] The invention relates to the field of aerospace propulsion technology, in particular to a multiple-start rocket engine and a start method. Background technique [0002] The pump-pressed rocket engine needs to start the turbo pump before reaching a stable working state to make the turbo pump start to rotate. Generally, the engine uses high-pressure air to blow the turbine or gunpowder to generate gas to make the turbo pump start to rotate. This is not a problem for a single-use launch vehicle, but for a reusable launch vehicle, a high-pressure gas starter is used, and the number of starts is limited, so repeated starts cannot be realized. [0003] For example, patent document RU2545613C1 discloses a liquid rocket engine with multiple starts, which includes a thrust chamber, a turbine for supplying fuel and oxidant to the thrust chamber; the engine starting method is to use high-pressure gas in a gas container to start the turbine. In the above-mention...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/95F02K9/94F02K9/60
CPCF02K9/95F02K9/94F02K9/60
Inventor 不公告发明人
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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