A reduction method for micro steady-state thrust based on dynamic compensation technique

被引：0
|
作者：
Zhou W. [1 ]
Hong Y. [1 ]
Ye J. [1 ]
Li N. [1 ]
Chang H. [1 ]
机构：
[1] State key Laboratory of Laser Propulsion & Application, Space Engineering University, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2018年 / 39卷 / 07期
基金：
中国国家自然科学基金;
关键词：
Dynamic compensation; Horizontal torsional pendulum; Measurement; Micro thruster; Thrust;
D O I：
10.7527/S1000-6893.2018.21885
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
New micro thrusters are vital force of micro/nano satellites in the future. Thrust measurement is very important support in the design, development and application of micro thrusters. In the design stage, the steady-state force working time of the thruster is sometimes difficult to match the setting time of the mechanical and direct measurement system. Therefore, the steady-state force cannot be obtained by the steady-state response. A reduction method for micro steady-state thrust is proposed based on the dynamic compensation technique. The relation between the working time and value of the steady-state thrust and the steady-state response of the measurement is analyzed. The design principles of the compensation filter and the steady-state thrust reduction steps are provided. Experiments are carried out to verify the method. The results show that when the working time of the steady-state thrust is longer than 0.25 times of the natural period of the measurement system and shorter than the setting time of the measurement system, the final output of the equivalent measurement system using the compensation filter can reach a steady state, and the range of the steady-state thrust can be obtained through the final steady-state output. © 2018, Press of Chinese Journal of Aeronautics. All right reserved.
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