摘要
为满足微小型卫星星载推进系统小型化、微推力、高精度的需求,研制了一种基于MEMS技术的固体化学微推进器。该推进器具有低功耗、低点火能量阈值、无可动部件的特点,理论上具有较高的工作可靠性。介绍了推进器的结构设计、工艺流程,以及推进剂加注方法,并给出了已经加工完成的6×6单元阵列原理样机的推力预测和点火性能初步测试结果。样机瞬时点火功率小于1W,平均点火电压低于40V,理论推力约1.7mN。与同量级推力的电推进器相比,工作电压大大降低。
A MEMS-based solid propellant propulsion array was developed to provide a miniature, highly accurate micro thrust impulse jet for a micro satellite propulsion system. The micro propulsion system has low power and energy thresholds for ignition and no moving parts, so they are expected to be highly reliable. The thruster design and fabrication process are described along with analysis of the propellant flow characteristics. Ignition and thrust tests were done on a prototype having a 6×6 array of micro thrusters. The ignition instantaneous power required for each unit is less than 1 W, the mean ignition voltage is less than 40 V, and the theoretical thrust force is about 1.7 mN. This working voltage is far less than that for electrical propulsion with the same order thrust.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2004年第11期1489-1492,共4页
Journal of Tsinghua University(Science and Technology)
基金
国家"八六三"高技术项目(863-701-2002AA715131)
关键词
微推进器
微机电系统
微型卫星
micro propulsion array
micro-electro-mechanical system MEMS
micro satellite
