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Propellant mass flow observation method for variable-thrust rocket engine

A rocket engine, mass flow technology, applied in the field of aerospace technology and control, to achieve the effect of reducing errors

Active Publication Date: 2021-08-24
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, for the complex mechanical structure of the rocket engine, the working process is accompanied by strong noise, such as the roar of the engine and various mechanical vibrations.

Method used

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  • Propellant mass flow observation method for variable-thrust rocket engine
  • Propellant mass flow observation method for variable-thrust rocket engine
  • Propellant mass flow observation method for variable-thrust rocket engine

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Embodiment Construction

[0061] 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.

[0062] refer to figure 1 As shown, this embodiment discloses a propellant mass flow observation method of a variable thrust rocket engine, and adopts an approximately linear control strategy to control the nonlinear system, mainly including the following steps:

[0063] Step S1. According to the dynamic equations of the motor and the pump, the state space expression of the electric pump system is obtained.

[0064] In this embodiment, the dynamic equation of the motor mainly includes three partial voltage balance equations, an electromagnetic torque equation and a motor torque balance equation.

[0065] The DC motor armature coil voltage balance...

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Abstract

The invention discloses a propellant mass flow observation method for a variable-thrust rocket engine, and the method comprises the steps: S1, obtaining a state space expression of an electric pump system according to the kinetic equations of a motor and a pump; S2, discretizing the state space expression of the electric pump system; S3, designing a Kalman filter through a program according to the discretization relational expression of the electric pump system; and S4, introducing the Kalman filter into the whole system pipeline, observing the mass flow of the liquid oxygen path and the methane path, judging whether a set filtering effect is achieved or not, if so, completing the design, otherwise, repeating the step S3, and adjusting the noise covariance and the initial prediction error covariance matrix in the Kalman filter design process, and the set filtering effect is achieved. According to the method, the error of mass flow measurement caused by environmental noise can be effectively reduced, and a real and reliable propellant mass flow value can be obtained.

Description

technical field [0001] The invention relates to the field of aerospace technology and control technology, and more specifically, to a propellant mass flow observation method of a variable-thrust rocket engine. Background technique [0002] With the development of the aerospace field, many countries have begun to devote themselves to the research of advanced technologies such as recyclable aircraft or soft landing on planetary surfaces. In order to achieve a soft landing, the deep variable thrust liquid rocket engine is an indispensable power device, especially for the soft landing on the surface of an atmosphere-free planet, the variable thrust liquid rocket engine is the only power device for achieving a soft landing. [0003] For a single liquid rocket engine, its thrust can be achieved by changing the propellant type, propellant flow rate, nozzle exit area, and nozzle throat. However, due to the limitations of physical structure and heat flow, it is difficult to change t...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/28G06F17/11G06F17/16F02K9/46G06F111/10G06F119/14
CPCG06F30/15G06F30/28G06F17/11G06F17/16F02K9/46G06F2111/10G06F2119/14
Inventor 胡润生吴建军程玉强杨述明刘育玮崔孟瑜戚元杰邓凌志石业辉
Owner NAT UNIV OF DEFENSE TECH
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