MEMS固体化学微推进阵列的微冲量测试技术  

Micro-Impulse Measurement of MEMS Solid Propellant Thruster Array

作　　者：李创新[1,2] 余协正[1,3] 叶迎华[1] 沈瑞琪[1] 王成玲[1] 朱莹[1] 

机构地区：[1]南京理工大学化工学院,江苏南京210094 [2]武汉军械士官学校,湖北武汉430075 [3]中国航天科工集团三十一研究所,北京100074

出　　处：《推进技术》2013年第4期572-576,共5页Journal of Propulsion Technology

基　　金：航天科技创新基金项目(CASC201105)

摘　　要：为了评价MEMS(Micro Electro Mechanical Systems)固体化学微推进阵列的推进性能,对其单元微冲量的精确测试显得尤为重要。在传统冲击摆的基础上,考虑微推进器推力和燃气射流冲击力之间的比例关系,设计了一套适用于MEMS固体化学微推进阵列单元微冲量的间接测试装置,并成功用于6×6规格(单元集成度为36个/cm2)微推进阵列的实际测试中。结果表明:典型实验数据下的待测微冲量为2.5442×10-4N.s,相对误差小于5%;实测8个单元的微冲量平均值为2.5574×10-4N.s,相对偏差较小,具有很好的重复性。In order to evaluate the propulsion performance of MEMS （Micro Electro Mechanical Systems） solid propellant thruster array, accurate measurement of unit micro-impulse is particularly important. Based on the traditional ballistic pendulum, as well as considering the relationship between the thrust and the impact of the gas jet, an indirect micro-impulse measuring device was designed. It was successfully used in the measurement of 6mm x 6ram （integration density is 36/cm^2） MEMS solid propellant thruster array. The results show that the unknown micro-impulse is 2. 5442 × 10^-4N. s under typical experimental datum, and the measurement accuracy meets the requirement of ballistic pendulum system in which the relative error is below 5%. The average impulse of 8 test units is 2. 5574 × 10^-4 N. s with small relative deviation and good reproducibility.

关 键 词：微推进器 冲量 冲击摆 转动惯量 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]