The Dynamic Model and Acceleration Compensation for the Thrust Measurement System of Attitude/Orbit Rocket

Base on the great demand of defense and aerospace for measuring pulse thrust of attitude/orbit rocket, the dynamic measurement system has been developed. This paper is mainly about the dynamic model and acceleration compensation of the system. Through improving the experimental modal analysis, the theoretical model was built. By comparing the actual frequency response curve with the theoretical dynamic model, it proves the method practical and the dynamic model accurate. According to the model, the step response is obtained by Laplace definite integral, so as to the dynamic performance. During studying the capability to measure the dynamic pulse thrust, there are dynamic errors although the static accuracy satisfies the demand already. Due to the acceleration plays a major role in all the factors, according to the dynamic model, an expression is derived for acceleration compensation. And the compensation curve is in accord with the error. Some attentions are referred in the end to ensure the compensation accurate.