摘要
为了将固体微型推力器阵列应用于姿轨控,需要对点火相关技术进行研究。分析了点火电路在姿态、轨道控制上的应用问题;设计了适用于大规模阵列的驱动电路,通断可控,能够满足点火需要;研究了点火延迟时间以及单次多组点火的间隔时间,当点火功率为2 W时,点火延迟时间经测试最大为7.6 ms,而点火间隔时间经测试最小为50μs。经过综合测试实验,点火成功率能够达到100%,验证了点火系统相关模块的可靠性和匹配性;经过控制仿真,验证了该系统能够满足卫星姿轨控需要。
To apply solid propellant micro-thruster array to attitude and orbit control,it is necessary to study the relevant ignition techniques.The application of ignition circuit in the attitude and orbital control was analyzed,and the driver circuit was designed to meet the requirement of ignition.The ignition delay time and the interval time of multi-group ignition were studied.When the ignition power was 2 W,the maximum of ignition delay time was 7.6 ms.The test results show that the minimum interval time is 50 μs.The experiment and simulation have proved that the ignition system is reliable and compatible;the success rate of ignition can be 100%,and the system meets the need of the attitude and orbit control for the satellite.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第2期183-187,192,共6页
Journal of Solid Rocket Technology
基金
"十一五"民用航天科研预先研究项目
关键词
固体微型推力器阵列
姿轨控
点火系统
逻辑控制
点火延迟时间
solid propellant micro-thruster array
attitude and orbit control
ignition system
logic control
ignition delay time
