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Liquid rocket thrust control system and liquid rocket

A technology of thrust control and liquid rocket, which is applied in the field of aerospace, can solve the problems of dragging the thrust-to-weight ratio of the engine, and achieve the effect of improving the thrust-to-weight ratio, ensuring accuracy, and realizing precise adjustment

Inactive Publication Date: 2020-04-14
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] On the other hand, the existing launch vehicle usually needs to be equipped with multiple engines. The existing Falcon Heavy rocket is equipped with 27 Merlin engines in only one stage, and each engine needs to be matched with a turbo pump, which seriously drags down Thrust-to-weight ratio of the engine

Method used

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  • Liquid rocket thrust control system and liquid rocket

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Embodiment 1

[0038] Such as figure 1 As shown, it is a schematic diagram of a liquid rocket thrust control system provided in this embodiment, which includes a pumping device 1, the inlet of the pumping device 1 communicates with the fuel supply system or the oxidant supply system, and several regulating branches are arranged in parallel at the outlet. Road 3; regulating branch 3 is provided with metering valve 31; constant pressure difference throttle valve 32 connected in series at both ends of metering valve 31; The road 3 acts on at least one power plant 4 .

[0039]First of all, it needs to be explained that the object used by the rocket thrust control system in this embodiment is a liquid rocket, and the liquid rocket is a rocket with a liquid rocket engine as a power device, and generally consists of a power device, a rocket body structure, and a control system. The chemical propellant usually used in the liquid rocket engine is composed of fuel and oxidant. In this embodiment, it ...

Embodiment 2

[0053] This embodiment provides a liquid rocket, which includes the liquid rocket propulsion control system mentioned above, and has all its technical advantages, which will not be repeated here.

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PUM

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Abstract

The invention provides a liquid rocket thrust control system and a liquid rocket. The liquid rocket thrust control system comprises a pumping device, an inlet of the pumping device is communicated with a fuel supply system or an oxidant supply system, and an outlet of the pumping device is provided with a plurality of adjusting branches in parallel; the adjusting branches are provided with metering valves, constant-pressure-difference throttling valves connected to the two ends of the metering valves in series, and on-off valves; the on-off valves are used for controlling the on-off of the adjusting branches; the plurality of adjusting branches act on at least one power device. According to the liquid rocket thrust control system, the thrust-weight ratio of a rocket can be effectively increased, and meanwhile, accurate adjustment of the rocket thrust can be achieved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a liquid rocket thrust control system and a liquid rocket. Background technique [0002] With the intensification of commercial aerospace competition, the requirements for the reliability and economy of launch vehicle engines are becoming more and more stringent. To reduce the cost of a single launch, the rocket is licensed for reuse. Therefore, it is necessary to recover the rocket. During the rocket recovery process, the thrust of the engine must be precisely adjusted to ensure that the launch vehicle can land smoothly and be reused. [0003] On the other hand, the existing launch vehicle usually needs to be equipped with multiple engines. The existing Falcon Heavy rocket is equipped with 27 Merlin engines in only one stage, and each engine needs to be matched with a turbo pump, which seriously drags down Thrust-to-weight ratio of the engine. Contents of the invention ...

Claims

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Application Information

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IPC IPC(8): F02K9/58F02K9/46
CPCF42B15/00
Inventor 彭小波刘中祥张玺魏一
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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