A Propellant Mass Flow Observation Method for Variable Thrust Rocket Engine

Abstract

The invention discloses a propellant mass flow observation 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, obtaining the state space expression of the electric pump system The expressions are discretized; S3. According to the discretization relational expression of the electric pump system, the Kalman filter is designed through the program; S4. The Kalman filter is brought into the whole system pipeline, for the liquid oxygen circuit and the methane circuit. Observe the mass flow rate to judge whether the set filtering effect is achieved, if so, complete the design, otherwise repeat step S3 and adjust the noise covariance and initial prediction error covariance matrix in the Kalman filter design process until the set filtering effect is achieved . The invention can effectively reduce the error caused by the environmental noise to the mass flow measurement, and can obtain the true and reliable propellant mass flow value.

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 depth 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 ...

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.

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