摘要
地面仿真验证是小卫星研制过程的重要组成部分,仿真验证充分与否直接决定了小卫星的研制成功率和在轨运行的可靠性。就小卫星技术特点,结合某型号的地面仿真需求,建立基于HLA的小卫星半物理仿真系统,给出系统的组成结构、联邦间交互数据表、硬件接口单元和联邦成员设计流程等。利用设计与实现的半物理仿真系统,进行了某型号小卫星的仿真验证,结果表明,设计的基于HLA的小卫星半物理仿真系统能够较好地完成动力学与控制分系统、电源分系统和有效载荷分系统的仿真,能够较好地实现控制分系统物理设备的接入,具有较好的实际应用价值。
The ground simulation is an important part of small satellite development process, the small satellite development success rate and orbit operation reliability is directly determined by the simulation and verification is full or not. In this paper, the hardwire- in- loop simulation system is established base- on HLA,according to the technique characteristics of small satellite, combined with the ground simulation needs. The main design process is done including system structure, the interaction data sheet, hardware interface unit and federate design process. Finally, a small satellite is simulated based- on the hardwire- in - loop simulation system designed and implemented here. The simulation results show that, the satellite hardwire- in- loop simulation system can be used to complete the dynamics and control subsystem, power subsystem and payload subsystem simulation, to better achieve the control subsystem physical device access, which has better application value.
出处
《航空计算技术》
2012年第6期80-84,共5页
Aeronautical Computing Technique
基金
国家自然科学基金青年基金项目资助(60904051)
关键词
小卫星
半物理
系统仿真
HLA
micro- satellite
hardwire- in- loop
simulation system
HLA
