Satellite-borne micro-thruster thrust response time measuring method based on digital filter

Abstract

The invention belongs to the technical field of aerospace satellite propulsion, and particularly relates to a satellite-borne micro-thruster thrust response time measuring method based on a digital filter. The thrust response time measurement method comprises the following steps: S1, performing zero returning processing on a non-zero initial condition of a torsional pendulum thrust measurement system to obtain an oscillatory differential equation of the thrust measurement system after variable substitution; s2, connecting a digital filter in series behind the thrust measurement system after variable substitution to obtain an equivalent sensitivity high-frequency thrust measurement system; s3, determining the system response of the equivalent sensitivity high-frequency thrust measurement system; s4, interpreting thrust response time of the satellite-borne micro-thruster from system response; s5, the thrust to be measured is calculated through system response inversion, and thrust response time is further confirmed. According to the equivalent sensitivity high-frequency thrust measurement system, the inherent frequency is greatly improved, the steady state entering time is greatly shortened, and measurement of the fast-change thrust response time is achieved.

Description

technical field [0001] The invention relates to the technical field of aerospace satellite propulsion, in particular to a method for measuring thrust response time of a spaceborne micro-thruster based on a digital filter. Background technique [0002] In the case of precise satellite control, the micro thruster is required to quickly adjust the thrust, and the thrust response time needs to be controlled within the specified range. Thrust response time can be expressed by thrust rising time and thrust falling time. When the thrust changes from a small stable thrust to a large stable thrust, the thrust response time is expressed by thrust rising time; when the thrust changes from a large stable thrust to a small stable thrust When , the thrust response time is represented by the thrust drop time, and at this time, the thrust response time is one of the evaluation indicators of the micro thruster. [0003] The difficulty in measuring thrust response time is that the frequency ...

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Problems solved by technology

[0006] (2) The dynamic thrust calculation method for fast-changing thrust response time is immature, and it is difficult to reflect the accurate thrust rising process or thrust falling process

In the dynamic thrust calculation, the difference quotient is used as the approximate value of the derivative to solve the vibration differential equation inversely (solution of the inverse problem of the vibration equation). The second is poor convergence: the truncation error increases when the step size is large, and the rounding error increases when the step size is small

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