| 引用本文: | 绳涛,白玉铸,何亮,等.微纳卫星姿态确定与控制半实物仿真系统设计.[J].国防科技大学学报,2016,38(5):72-77.[点击复制] |
| SHENG Tao,BAI Yuzhu,HE Liang,et al.Semi-physical simulation system design for attitude determination and control of micro/nano-satellite[J].Journal of National University of Defense Technology,2016,38(5):72-77[点击复制] |
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| 微纳卫星姿态确定与控制半实物仿真系统设计 |
| 绳涛, 白玉铸, 何亮, 冉德超, 赵勇 |
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(国防科技大学 航天科学与工程学院， 湖南 长沙 410073)
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| 摘要: |
| 航天器姿态控制系统需要特殊的运行环境，在地面很难考核，这给系统可靠性带来一定的风险。针对微纳卫星的特点，设计并研制了一套面向微纳卫星的姿态确定与控制半实物仿真系统。该系统通过数字化模型模拟卫星姿态轨道运动、敏感器模型产生敏感器测量数据、执行器模型生成控制力矩、敏感器模拟器实现通信协议，最终实现姿态控制系统的全系统仿真。这套系统可以接入卫星控制系统回路，实现对姿控系统软件、硬件的考核，同时验证算法的性能。基于该系统，对天拓三号卫星姿控系统进行地面半实物仿真，并对比在轨试验数据，结果表明系统设计合理，仿真结果可信。 |
| 关键词: 微纳卫星 姿态控制系统 半实物仿真 天拓三号 |
| DOI：10.11887/j.cn.201605012 |
| 投稿日期：2016-01-20 |
| 基金项目:国家自然科学基金资助项目（11302253）；国防科学技术大学科研计划资助项目（ZK16-03-20） |
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| Semi-physical simulation system design for attitude determination and control of micro/nano-satellite |
| SHENG Tao, BAI Yuzhu, HE Liang, RAN Dechao, ZHAO Yong |
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(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| Attitude control system requires special working environment, so it is hard to actualize on the ground, which has brought a certain reliability risk to satellite. According to the characteristics of micro/nano-satellite, a set of semi-physical simulation system for attitude determination and control was designed and implemented. A digital model simulated the satellite attitude and orbit motion, a sensor model generated the measured data, an actuator model generated the control torque, a sensor simulator realized the communication protocol and finally this system realized the whole simulation of attitude control system. The system can be connected in the satellite control system loop to assess software and hardware of the attitude control system, and to verify the performance of the algorithm. The system was applied to validate the attitude control system of TianTuo-3 in ground simulation. The comparison with the on-orbit test data shows that the design of system is reasonable and the result of simulation is credible. |
| Keywords: micro/nano-satellite attitude control system semi-physical simulation TianTuo-3 |
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