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Liquid-propellant rocket engine, thrust control method and device thereof and carrier rocket

A thrust control, liquid rocket technology, applied in the aerospace field, can solve the problems of launch vehicle trajectory optimization, inability to adjust the thrust, and high launch costs.

Pending Publication Date: 2020-09-22
安徽九州云箭航天技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the thrust of the current liquid rocket engines can only output constant thrust, and the thrust cannot be adjusted to optimize the trajectory of the launch vehicle and recover the rocket body, so that the launch cost of the current space launch remains high

Method used

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  • Liquid-propellant rocket engine, thrust control method and device thereof and carrier rocket
  • Liquid-propellant rocket engine, thrust control method and device thereof and carrier rocket
  • Liquid-propellant rocket engine, thrust control method and device thereof and carrier rocket

Examples

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Effect test

Embodiment 1

[0053] image 3 It is a flow chart of a thrust control method in the embodiment of this application

[0054] Such as image 3 As shown, the thrust control method provided in this embodiment is applied to the liquid rocket engine described above, and specifically includes the following steps:

[0055] S1. Obtain the current pressure of the liquid rocket motor.

[0056] That is, when the carrier rocket equipped with a liquid rocket engine is normally ignited and is in flight, the current thrust of the liquid rocket engine should be obtained, but generally speaking, the thrust cannot be actually measured, so this application uses an indirect method to obtain the rocket engine current pressure.

[0057] S2. Calculating an opening adjustment parameter based on the current pressure.

[0058] The opening adjustment parameter here refers to the parameter required for adjusting the thrust regulating valve set on the first branch road. When the gas flow of the gas changes, the turb...

Embodiment 2

[0076] Figure 5 It is a block diagram of a thrust control device according to an embodiment of the present application

[0077] Such as Figure 5 As shown, the thrust control device provided in this embodiment is applied to the liquid rocket engine described above, and specifically includes a pressure acquisition module 10 , a parameter calculation module 20 and a control execution module 30 .

[0078] The pressure acquisition module is used to acquire the current pressure of the liquid rocket motor.

[0079] That is, when the carrier rocket equipped with a liquid rocket engine is normally ignited and is in flight, the current thrust of the liquid rocket engine should be obtained, but generally speaking, the thrust cannot be actually measured, so this application uses an indirect method to obtain the rocket engine current pressure.

[0080] The parameter calculation module is used to calculate the opening adjustment parameter based on the current pressure.

[0081] The op...

Embodiment 3

[0099] This embodiment provides a liquid rocket engine, the liquid rocket engine such as figure 2 As shown, and provided with the thrust control device provided by the above embodiment.

[0100] The thrust control device is specifically used to obtain the current pressure of the liquid rocket engine; calculate according to the current pressure and the current required target pressure to obtain the opening adjustment parameter; adjust the opening of the thrust adjustment valve according to the opening adjustment parameter, so as to Make the opening of the thrust regulating valve reach the target opening. By adjusting the opening of the thrust regulating valve, it is possible to control the flow of oxidant entering the gas generator, so that the flow of gas output by the gas generator will change, and the speed of the turbo pump will change accordingly, and the speed of the turbo pump will change accordingly. The change of the engine flow leads to the change of the engine flow...

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Abstract

The invention discloses a rocket engine, a thrust control method and device thereof and a carrier rocket. The method and the device are applied to the liquid-propellant rocket engine. The liquid-propellant rocket engine is provided with a turbine pump, a gas generator, a thrust chamber, a valve and other assemblies, and a thrust adjusting valve is arranged on a first branch for conveying an oxidant to the gas generator. The thrust control method specifically comprises the steps of obtaining the current pressure of the thrust chamber of the liquid-propellant rocket engine; carrying out calculation according to the current pressure of the thrust chamber and the current required target pressure to obtain an opening adjusting parameter of the thrust adjusting valve; and adjusting the opening degree of the thrust adjusting valve according to the opening degree adjusting parameter so as to enable the opening degree of the thrust adjusting valve to reach the target opening degree. By adjusting the opening degree of the thrust adjusting valve, the flow of the engine can be adjusted, so that the thrust can be adjusted, and trajectory optimization and rocket body recovery can be realized forthe carrier rocker by adjusting the thrust.

Description

technical field [0001] The present application relates to the field of aerospace technology, and more specifically, relates to a liquid rocket engine and its thrust control method, device and launch vehicle. Background technique [0002] At present, the main high-thrust rocket transmitters at home and abroad generally use liquid rocket engines, which realize thrust output through the combustion of binary liquid fuel. However, the thrust of the current liquid rocket engines can only output constant thrust, and the thrust cannot be adjusted to optimize the trajectory of the launch vehicle and recover the rocket body, so that the launch cost of the current space launch remains high. Contents of the invention [0003] In view of this, the present application provides a liquid rocket engine and its thrust control method, device and launch vehicle, which are used to adjust the thrust of the liquid rocket engine on the launch vehicle, and realize the ballistic optimization and ar...

Claims

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Application Information

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IPC IPC(8): F02K9/46F02K9/56F02K9/58
CPCF02K9/46F02K9/563F02K9/58
Inventor 黄仕启马海宁付军锋周伟卢明刘洋金富贵李旭升季凤来隗合成
Owner 安徽九州云箭航天技术有限公司
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