Abstract
It is a trend that the high orbit and high performance satellites are applied to on-orbit service. There are some advantages for tracking spacecraft to use proportional navigation timely in autonomous homing phase of rendezvous docking. In this paper, proportional navigation is derived from inertial coordinate system using optimal control method. The approximate treatment of C-W equation shows that proportional navigation is suitable for high orbit. The simulation results of proportional navigation and trajectory planning show that the fuel optimal effect of proportional navigation is good. There is no accumulated error in proportional navigation, which results in a good accuracy of reaching the target point. Because the terminal velocity cannot be effectively controlled, it is suitable for long-distance autonomous homing phase. Timely use of proportional navigation has certain advantages.
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References
Zhu R (2007) Rendezvous and docking techniques of spacecraft. National Defense Industry Press
Zhu R, Tang Y (2005) Design methods for the closing and fly-around of space rendezvous. Chinese Space Sci Technol 25(1)
Cheng Y (2014) Study on relative navigation and flying-around of non-cooperative spacecrafts. Harbin Institute of Technology
Tang G, Luo Y, Zhang J (2007) Rendezvous and docking the mission planning for space flight. Science Press, Beijing
Zhou L (2011) Design and optimization of orbit transfer and flying trajectory of spacecraft. Harbin Institute of Technology
Wu S (2012) Research on control of chaser spacecraft with proximity to space target. Harbin Institute of Technology
Chen T, Xu S (2008) Research on guidance law of autonomous approach for spacecrafts flying in elliptical orbits. J Astronaut 29(6)
Wang C, Qu Y (2013) Trajectory optimization method for spacecraft orbit transfer with finite thrust. J Southwest Jiaotong Univ 48(2)
Lei T (2009) Study on optimal orbit design for spacecraft with finite thrust. Harbin Institute of Technology
Qi Z (2018) Design of missile guidance and control system. China Astronautic Publishing House
Li J, Li H (2009) Homing mission design of space rendezvous based on proportional guidance. Flight Dyn 27(4)
Li X (2011) Guidance method of fast fly-around relative to target spacecraft. Harbin Institute of Technology
Tian Y (2010) Study on guidance methods of fly-by approaching observation of space target. Graduate School of National University of Defense Technology
Tang Y (2006) Research on method of spacecraft’s rendezvous with maneuvering target based on sight coordinate system. Harbin Institute of Technology
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Song, Q., Chen, X., Chen, Q., Ren, Y., Zhu, M. (2020). Research on Tracking Guidance Method for On-orbit Service Autonomous Homing Based on Proportional Guidance and Trajectory Planning. In: Jia, Y., Du, J., Zhang, W. (eds) Proceedings of 2019 Chinese Intelligent Systems Conference. CISC 2019. Lecture Notes in Electrical Engineering, vol 593. Springer, Singapore. https://doi.org/10.1007/978-981-32-9686-2_31
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DOI: https://doi.org/10.1007/978-981-32-9686-2_31
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