摘要
为建立全电推进卫星的精确模型、设计全电推卫星的姿轨控方法及提高卫星的控制精度,针对一种配置可展开矢量调节机构的全电推卫星开展动力学模型研究.建立四关节可展开矢量调节机构的模型,推导基于可展开式矢量调节机构构型的全电推卫星的电推力及力矩模型,在此基础上建立全电推卫星的姿态轨道动力学方程.利用此模型描述全电推进卫星的姿态运动状态及轨道变化,能够准确反映出卫星的运动性能,该模型已应用于我国亚太6E卫星研制中,应用该模型对卫星进行的动力学仿真结果符合测试及分析结果,且该卫星在轨控制效果与预期一致,验证了模型的有效性.
In order to establish an accurate model of the all-electric propulsion satellite,design an attitude orbit control method and improve the satellite control accuracy,the dynamics modeling of the all-electric propulsion satellite with deployable thruster point assembly mechanism(TPAM)is studied.The model of the four-joint deployable TPAM is established,and the electric thrust and torque models based on the configuration of TPAM are derived.On this basis,the attitude orbit dynamics equation of the satellite is established.The model can be used to describe the attitude motion state and orbit change of the all-electric propulsion satellite,which can accurately reflect the motion performance of the satellite.The model has been applied in the development of the APSTAR-6E satellite.The simulation results show that the dynamic simulation results of all-electric propulsion satellite via the model accord with the test and analysis results,and the control effect of the APSTAR-6E in orbit is consistent with the expectation,which verifies the validity of the model.
作者
耿洁
文闻
李巍
刘蕊
王玉峰
GENG Jie;WEN Wen;LI Wei;LIU Rui;WANG Yufeng(Beijing Institute of Control Engineering,Beijing 100094,China)
出处
《空间控制技术与应用》
CSCD
北大核心
2024年第1期17-24,共8页
Aerospace Control and Application
基金
十四五民用航天技术预先研究项目(D030301)。
关键词
全电推进
矢量调节机构
动力学模型
亚太6E
all-electric propulsion
thruster point assembly mechanism
dynamic model
APSTAR-6E
