摘要
设计一种基于立方星的星箭分离机构。首先,根据立方星的分离速度要求,设计了分离机构的机械结构和分离弹簧参数。在此基础上建立了星箭分离机构动力学模型,通过对动力学模型的数值计算确定满足无干涉分离条件的舱门扭簧弹性系数。根据分离机构的电气要求,设计了电路防短路措施、电磁铁保护电路和遥测电路。对星箭分离机构仿真和试验,校验了星箭分离机构的分离功能和遥测功能,立方星的分离速度和分离机构的遥测功能满足设计技术指标。
A separation device based on cubesat was designed. First of all, according to the requirements of the cubesat separation speed, the mechanical structure of separation mechanism and separation spring parameters were designed. And then, on the basis of above results, the dynamics model of separation mechanism was established through numerical calculation of the dynamics model to confirm the elasticity coefficient of the torsional spring which met the requirements of non-interference separation. Based on the electrical requirements of separation mechanism, short-circuit measures electromagnet protection circuit and telemetry circuit was designed. Simulation and test of cubesat and launch vehicle and the detection of separation and telemetry function of separation device showed that the initial velocity of cubesat and the telemetry function of separation mechanism completely satisfies designed technical indexes.
出处
《导弹与航天运载技术》
北大核心
2015年第5期20-24,共5页
Missiles and Space Vehicles
关键词
立方星
星箭分离装置
防干涉
遥测功能
Cubesat
Satellite and launch vehicle separation device
Anti-interference
Telemetry function
