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
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[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.
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