Research On Dynamic Characteristics Of A Double Range Pressure Sensor

Large thrust ratio solid rocket motors are widely used in the field of aerospace, its’ thrust testing is an extremely important technical work in the experiment study, it provides original parameters for engine performance analysis, and provides basis for adjusting the charging parameters and improving performance of propellant to meet the design requirements. Accurate measurement of the thrust parameters of solid rocket motor is the key to the development of rocket motors, A thrust test problem of the Large thrust ratio solid rocket motors thrust is that the two stage thrust ratio is large, the switch of engine thrust in the work process of the engine made the system’s dynamic characteristics complex. The transient change of thrust brought the thrust test dynamic error, make it difficult to handle the test data of the transition section. Using a traditional single sensor in the whole engine measurement process, the accuracy of the low thrust segment is very poor. How to improve the test accuracy of large thrust ratio small range section, solve lag phenomenon of conversion process of thrust, improve and perfect the data processing method, the above contents are worthy of study in the testing technology of large thrust ratio solid rocket motors.This paper firstly introduced structure and working principle of double range pressure sensor, and described the strength checking for determining the structural size in some detail, gave the component diagram and assembly drawings. Secondly, conduct the static loading test of double range pressure sensor, gathered the input data and output data, fitted out relation between input and output, according to the related theory to calculate the indicators of static calibration. And then get the natural frequency of small range sensor through sweep frequency experiments, conduct hammer test for each sensor and get the frequency response function curve through the Fourier transform of the experimental results. Get k, m, c, Amplitude frequency characteristic and Phase frequency characteristic curves of each sensor by mechanism analysis, established two freedom degree vibration model by Adams software, and model’s parameters are k, m and c of each sensor, evaluate dynamic characteristics of dual range pressure sensor according to the simulation results, the double range pressure sensor can accurately measure the dynamic force of thrust ratio less than 5:1. Finally proposed a double range pressure sensor dynamic measurement error compensation algorithm, and derived that this algorithm is a good way to compensate the dynamic measurement error with Adams.This design of this paper could realize Large thrust ratio solid rocket engine thrust‘slarge range and high precision measurement, the error compensation algorithm could make full use of double range pressure sensor’s two outputs to compensate the output of small range sensor, is supplementary and perfection of current sensor measurement data processing method.