| 微纳卫星姿态确定与控制半实物仿真系统设计 |
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| 引用本文： | 绳涛,白玉铸,何亮,冉德超,赵勇.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. |
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| 作者姓名： | 绳涛 白玉铸 何亮 冉德超 赵勇 |
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| 作者单位： | 国防科技大学 航天科学与工程学院,国防科技大学 航天科学与工程学院,国防科技大学 航天科学与工程学院,国防科技大学 航天科学与工程学院,国防科技大学 航天科学与工程学院 |
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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。
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| 关 键 词： | 微纳卫星 姿态控制系统 半实物仿真 设计 |
| 收稿时间： | 2016/1/20 0:00:00 |
| 修稿时间： | 7/6/2016 12:00:00 AM |
Design of semi-physical simulation for micro/nano-satellite attitude determination and control |
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| SHENG Tao,BAI Yuzhu,HE Liang,RAN Dechao and ZHAO Yong.Design of semi-physical simulation for micro/nano-satellite attitude determination and control[J].Journal of National University of Defense Technology,2016,38(5):72-77. |
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| Authors: | SHENG Tao BAI Yuzhu HE Liang RAN Dechao and ZHAO Yong |
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| Institution: | College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China and College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China |
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| Abstract: | Performance of Attitude Control System is an important indicator and can directly affects performance of satellite. As Attitude Control System requires special operating environment, it is hard to assess on the ground, which has brought a certain risk of satellite design. In this paper, a set of semi-physical simulation system for attitude determination and control of micro/nano-satellites is designed and implemented according to the characteristics of micro/nano-satellite. Digital model simulates satellite motion and orbit environment, sensor model generates measured data, actuator model generates control torque, sensor simulator realizes communication protocol and finally realizes whole system simulation. The system can be connected to the satellite control system loop to assess software and hardware of the attitude control system and verify the performance of the algorithm. The system has been applied and comprehensively assessed software and hardware of attitude control system in ground simulation of satellite TT-3, and has been proved reasonable and credible. |
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| Keywords: | micro/nano-satellite attitude control system semi-physical simulation design |
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