微纳卫星固体火箭推进器推力矢量测量方法

doi:10.3969/j.issn.1001-506X.2020.06.19

Abstract

Abstract:

Solid rocket thruster has many advantages when applied to micro-nano satellites, but the thrust vector of such a kind of small solid rocket thruster is difficult to measure. A method for mapping the thrust vector by using the inertial sensor measurement value through the ground dynamic flight test is proposed to solve the problem. Firstly, the dynamics model of the ground test system is established by the Newton-Euler method and the variable mass theory, and the dynamics and kinematics characteristics of the satellite are analysed. Then the measurement equation of the inertial measurement unit (IMU) is constructed, and the thrust measurement model is deduced by the mapping relationship between the thrust vector and the measurement value of the inertial sensor. Finally, the error sources affecting the measurement accuracy of the thrust vector are analyzed by simulations, and the installation configuration of the inertial sensor is optimized. Through numerical simulation experiments, the measurement method after optimization can ensure that the measurement accuracy of the main thrust and the lateral thrust is better than 0.3%.

Key words: micro-nano satellite, solid rocket thruster, variable mass, dynamic model, thrust measurement

CLC Number:

V448.22-2

Pengjun QIAN, Zhengliang LU, Wenhe LIAO. Thrust vector measurement method of micro-nano satellite solid rocket thruster[J]. Systems Engineering and Electronics, 2020, 42(6): 1348-1357.

Figures/Tables 12

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参数	值
卫星壳体质量/kg	1.8
卫星壳体转动惯量/kg·m²	[8, 0, 0;0, 8, 0;0, 0, 3]×10^-3
推进剂质量/kg	0.2
推进剂尺寸/mm×mm	50×50
推进器工作时间/s	5

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Thrust vector measurement method of micro-nano satellite solid rocket thruster

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