Guidance algorithm for satellite formation reconfiguration based on relative orbit elements

In the full paper, we explain our guidance algorithm in detail. In this abstract, we just add some pertinent remarks to listing the three topics of explanation. The first topic is: relative orbit elements. In topic one, we review briefly those contents of the conference paper by Lovell et al^[4] that are useful to us in developing our guidance algorithm. The second topic is: the guidance algorithm for satellite formation reconfiguration based on relative orbit elements. Topic two adopts two-thrust control model to compute the incremental velocity ΔV. The third topic is: numerical simulation example and the analysis of simulation results. Topic three considers three different situations; (1) with reconfiguration transfer angle fixed at 10°, 30°, 50°, 70° or 90°, the variation of ΔV with transfer time; (2) the variation of ΔV with transfer angle under certain conditions; (3) with relative trajectory radius fixed at 100, 200, 300, 400 or 500 m, the variation of ΔV with transfer angle. The simulation results for these three situations are given respectively in three figures in the full paper. The simulation results indicate preliminarily that our algorithm can take into account the flying state, the restricting conditions, the transfer program, and the impulse requirements simultaneously and satisfactorily.