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A thrust control method of a variable thrust rocket engine

A rocket engine and thrust control technology, which is applied in the field of aerospace technology and control, can solve problems such as reduced reliability and complex mechanical structure, and achieve the effect of reducing fuel consumption

Active Publication Date: 2022-03-04
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As we all know, the turbopump propellant supply system greatly reduces the weight of the entire propulsion system, but due to the complexity of the mechanical structure, the reliability is reduced (most launch failures are caused by turbopump failure)

Method used

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  • A thrust control method of a variable thrust rocket engine
  • A thrust control method of a variable thrust rocket engine
  • A thrust control method of a variable thrust rocket engine

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Embodiment Construction

[0038] The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, so as to define the protection scope of the present invention more clearly.

[0039] refer to figure 1 As shown, the present embodiment discloses a thrust control method of a variable thrust rocket engine, comprising the following steps:

[0040] Step S1, according to the dynamic equations of the motor and the pump, the state space expression of the electric pump system is obtained.

[0041] The dynamic equations of the motor mainly include three partial voltage balance equations, electromagnetic torque equations and motor torque balance equations.

[0042] The DC motor armature coil voltage balance equation is:

[0043]

[0044] where U m is the motor voltage, R m is the coil resistance, i m is the current, L m i...

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Abstract

The invention discloses a thrust control method of a variable thrust rocket engine, comprising: S1, obtaining the state space expression of the electric pump system according to the dynamic equation of the motor and the pump; S2, linearizing the state space expression of the electric pump system According to the incremental linearization equation of the electric pump system, S3, according to the linearization equation of the incremental form, according to the control strategy adopted, the controller gain can be determined by the method of setting; S4, the obtained controller gain Bring it into the whole system, carry out the simulation calculation for the liquid oxygen circuit and the methane circuit with thrust and mixing ratio as the control targets respectively, judge whether the controller gain is feasible according to the simulation results, if feasible, the controller design is completed; if the control effect reaches If the set requirement is not met, repeat step S3 and adjust the calculation of the controller gain according to the adopted method until the set control effect is achieved. The invention can well control the thrust of the engine in the thrust changing process.

Description

technical field [0001] The present invention relates to the field of aerospace technology and control technology, and more specifically relates to a thrust control method of a variable-thrust rocket engine. Background technique [0002] Liquid rocket engines are the main power devices for space transportation systems and aircraft propulsion and maneuvering. Thrust-adjustable liquid rocket engines have received extensive attention in recent years, and their diversified development has put forward new requirements for the aviation field. The thrust-adjustable liquid rocket engine is a better power choice for missions such as deep space exploration, transportation, and soft landing on planetary surfaces, because it can adjust the thrust according to mission requirements. In order to meet the requirements of a soft landing on the planetary surface, the descent stage engine must have the ability to adjust the depth. Variable-thrust liquid rocket engines play an important role i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/80F02K9/56
CPCF02K9/80F02K9/56F02K9/563F05D2260/81F05D2270/701F05D2270/71
Inventor 胡润生吴建军程玉强杨述明刘育玮戚元杰崔孟瑜邓凌志石业辉
Owner NAT UNIV OF DEFENSE TECH