Journal of Systems Engineering and Electronics ›› 2021, Vol. 32 ›› Issue (5): 1200-1211.doi: 10.23919/JSEE.2021.000102

• SYSTEMS ENGINEERING • Previous Articles     Next Articles

An integrated simulation system for operating solar sail spacecraft

Yaru ZHENG(), Qinglong LI(), Ming XU*(), Yunfeng DONG()   

  1. 1 School of Astronautics, Beihang University, Beijing 100191, China
  • Received:2020-08-08 Online:2021-10-18 Published:2021-11-04
  • Contact: Ming XU E-mail:zheng_yaru@outlook.com;liqnlong@buaa.edu.cn;xuming@buaa.edu.cn;sinosat@buaa.edu.cn
  • About author:|ZHENG Yaru was born in 1995. She received her B.S. degree in automation engineering from the Ocean University of China in 2017, and her M.S. degree in aerospace engineering from Beihang University in 2020. Her research interests include computational mission analysis and system design in satellite/rocket engineering, and trajectory design for rockets. E-mail: zheng_yaru@outlook.com||LI Qinglong was born in 1998. He received his B.S. degree in aerospace engineering from Beihang University in 2018. He is currently working toward his M.S. degree in aerospace engineering in the School of Astronautics, Beihang University. His research interests include satellite formation flying, sequential and batch estimations of orbital elements, and flight control. E-mail: liqnlong@buaa.edu.cn||XU Ming was born in 1981. He received his Ph.D. degree in aerospace engineering from Beihang University in 2008. He worked for China Academy of Space Technology as a system engineer until joining School of Astronautics, BUAA in 2011. He has been a professor in aerospace engineering since 2020. His research interests include computational mission analysis and system design in satellite engineering, Hamiltonian system, and its application into astrodynamics. E-mail: xuming@buaa.edu.cn||DONG Yunfeng was born in 1965. He received his B.S., M.S., and Ph.D. degrees in aerospace engineering from Beihang University in 1987, 1990, and 2005 respectively. He is a professor in aerospace engineering in the School of Astronautics, Beihang University. His research interests include aerospace mission design, astrodynamics, and control. E-mail: sinosat@buaa.edu.cn
  • Supported by:
    This work was supported by the National Natural Science Foundation of China (11772024)

Abstract:

An integrated simulation system for solar sail spacecraft with individually controllable elements (SSICE) is investigated in this paper, including the modelling of power management, thermal control, attitude control, umbra prediction, and orbit prediction subsystems. Considering the self-control and reactivity subsystems, an agent based method is applied to develop the subsystem models. Each subsystem is an individual agent component, which manages itself autonomously and reacts to the requirements from other agents. To reduce computing burden on a specified computer and improve the suitability and flexibility of the integrated simulation system, a distributed framework is employed in the system by deploying agent components on different computers. The data transmission among agents is based on the transmission control protocol/Internet protocol (TCP/IP). A practical example of sun pointing is used to test the operating effect of the integrated system and the working condition of subsystems. The simulation results verify that the integrated system has higher sun pointing accuracy, quicker dynamical response to variations of the lighting, attitude and temperature and fewer computing resources with effective and accurate subsystems. The integrated system proposed in this paper can be applied to solar sail design, operation, and mission planning.

Key words: solar sail spacecraft, integrated system, agent, distributed simulation, individually controllable element