کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
1765286 1020094 2013 15 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Integrated orbit and attitude hardware-in-the-loop simulations for autonomous satellite formation flying
کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه علوم زمین و سیارات علوم فضا و نجوم
پیش نمایش صفحه اول مقاله
Integrated orbit and attitude hardware-in-the-loop simulations for autonomous satellite formation flying
چکیده انگلیسی


• An integrated hardware simulator is developed for satellite formation flying.
• The simulator involves orbit and attitude determination and control.
• Integrated simulations are performed for formation reconfiguration.
• The system can be used in a real-time to validate formation flying algorithms.

Development and experiment of an integrated orbit and attitude hardware-in-the-loop (HIL) simulator for autonomous satellite formation flying are presented. The integrated simulator system consists of an orbit HIL simulator for orbit determination and control, and an attitude HIL simulator for attitude determination and control. The integrated simulator involves four processes (orbit determination, orbit control, attitude determination, and attitude control), which interact with each other in the same way as actual flight processes do. Orbit determination is conducted by a relative navigation algorithm using double-difference GPS measurements based on the extended Kalman filter (EKF). Orbit control is performed by a state-dependent Riccati equation (SDRE) technique that is utilized as a nonlinear controller for the formation control problem. Attitude is determined from an attitude heading reference system (AHRS) sensor, and a proportional-derivative (PD) feedback controller is used to control the attitude HIL simulator using three momentum wheel assemblies. Integrated orbit and attitude simulations are performed for a formation reconfiguration scenario. By performing the four processes adequately, the desired formation reconfiguration from a baseline of 500–1000 m was achieved with meter-level position error and millimeter-level relative position navigation. This HIL simulation demonstrates the performance of the integrated HIL simulator and the feasibility of the applied algorithms in a real-time environment. Furthermore, the integrated HIL simulator system developed in the current study can be used as a ground-based testing environment to reproduce possible actual satellite formation operations.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Advances in Space Research - Volume 52, Issue 12, 15 December 2013, Pages 2052–2066
نویسندگان
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