Autonomous Lunar Orbit Rendezvous Guidance Based on J(2)-Perturbed State Transition Matrix
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A precise, convenient optimization method is proposed for vehicle rendezvous guidance in a lunar orbit by using the simplified GA-STM (SGA-STM), obtained by retaining only the O(e) non-J2 terms and neglecting the O(e)J2 terms. It is adopted for propagating the relative motion states with respect to a near-circular lunar parking reference orbit in a curvilinear coordinate system. Numerical simulations are provided to evaluate the accuracy of the relative states propagated by SGA-STM. The results show that the predicted relative states are in good agreement with the results obtained from a numerical integration approach.
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS
author list (cited authors)
Li, J., Vadali, S. R., & Hexi, B.
complete list of authors
Li, Jingyang||Vadali, Srinivas R||Hexi, Baoyin