Navigation and Coordination Control System for Formation Flying Satellites
This paper presents the design of a guidance, navigation and control (GNC) system for formation flying satellites in low Earth orbit. An innovative estimation approach employs a common extended Kalman filter (EKF) for the spaceborne autonomous control mode, which includes the J2 perturbations. A nonlinear least squares method is adopted for the ground-in-the-loop control mode. As a result, the navigation system can provide relative orbit information with a position accuracy of 3cm and a velocity accuracy of 0.2mm/s. The coordination control concept is detailed based on the relative orbital elements. Therefore, a three impulse method for configuration control is put forward which is simple and easy for engineer implement. Finally, an overview of the processor-in-the-loop testbed is given, which enables a seamless transition to real-time software simulations as well as hardware-in-the-loop simulations. The validation shows the simplicity and effectiveness of the navigation and control algorithms.
formation flying relative orbit determination EFK nonlinear least squares estimate relative orbital element coordination control processor-in-the-loop simulation system
Hu Min Zeng Guoqiang Song Junling
The Academy of Equipment Command & Technolog Beijing, 101416, China Institute of Aerospace and Material Engineering National University of Defense Technology Changsha,
国际会议
太原
英文
95-99
2010-10-22（万方平台首次上网日期，不代表论文的发表时间）