Real-time testing system for attitude control software of micro-nano satellite

DONG Kai-chen; ZHAO Kai-chun; ZHAO Peng-fei; YOU Zheng

doi:10.3788/OPE.20132108.2008

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Real-time testing system for attitude control software of micro-nano satellite

更新时间：2020-08-12

- Real-time testing system for attitude control software of micro-nano satellite
- Optics and Precision Engineering Vol. 21, Issue 8, Pages: 2008-2015(2013)
- 作者机构：
  
  清华大学精密仪器系北京,100084
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20132108.2008
  CLC： TP311.5;V448.22
- Received：11 January 2013，
  
  Revised：07 March 2013，
  
  Published Online：20 August 2013，
  
  Published：15 August 2013
- 稿件说明：
移动端阅览
董恺琛赵开春赵鹏飞尤政. 微纳卫星姿控软件实时测试系统[J]. 光学精密工程, 2013,21(8): 2008-2015

DONG Kai-chen ZHAO Kai-chun ZHAO Peng-fei YOU Zheng. Real-time testing system for attitude control software of micro-nano satellite[J]. Editorial Office of Optics and Precision Engineering, 2013,21(8): 2008-2015
董恺琛赵开春赵鹏飞尤政. 微纳卫星姿控软件实时测试系统[J]. 光学精密工程, 2013,21(8): 2008-2015 DOI： 10.3788/OPE.20132108.2008.

DONG Kai-chen ZHAO Kai-chun ZHAO Peng-fei YOU Zheng. Real-time testing system for attitude control software of micro-nano satellite[J]. Editorial Office of Optics and Precision Engineering, 2013,21(8): 2008-2015 DOI： 10.3788/OPE.20132108.2008.

摘要

为了在硬件有限的条件下测试微纳卫星姿态控制软件的实时控制性能，建立了微纳卫星姿态控制软件实时测试系统，并使用该系统对微纳卫星姿态控制软件进行了测试实验。根据卫星姿态动力学与运动学、轨道环境信息与姿态控制算法数学模型，在PC机上设计开发了微纳卫星模拟飞行平台。使用控制器局域网络（CAN）和串口建立了连接星载计算机与PC机微纳卫星模拟飞行平台的高效通讯链路，并对姿态控制软件主程序进行必要的修改。最后，基于该实时测试系统，完成了星载计算机上姿态控制软件的实时控制性能测试实验。实验结果表明：姿态控制软件在星箭分离后18 446 s完成初始控制阶段并进入偏置对地三轴稳定模式，实现了微纳卫星的稳态控制目标。偏置对地三轴稳定模式中卫星最低单轴姿态精度与角速度稳定度分别优于1.86和0.048()/s，满足该模式控制精度与收敛时间的要求。

Abstract

To test the control performance of attitude control software in real time for a micro-nano satellite under hardware limited

a real-time testing system for the attitude control software of micro-nano satellite was established and the control software was tested with the proposed system. Based on the dynamics and kinematics of satellite attitude

the environment information of satellite trajectory

and the mathematical model of an attitude control algorithm

a flight imitation platform for the micro-nano satellite was developed on a PC. Then

the efficient communication link between on-board computer and PC was established by a Controller Area Network(CAN) and serial communication. The main program of the attitude control software was also modified as required. Finally

the real-time control performance of the attitude control software for on-board computer was tested with the real-time testing system. Experimental results indicate that the attitude control software can complete the initial control stage and enter the bias three-axis stabilization mode by 18 446 s after the separation of satellite and rocket

which achieves the stabilization control of micro-nano satellite attitude. In the bias three-axis stabilization mode

the minimum one-axis attitude accuracy and the angular velocity stability of the satellite are within 1.86and 0.048()/s

respectively

which meets the requirements of attitude accuracy and converge time of the control mode.

关键词

Keywords

references

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