Autonomous Lunar Orbit Rendezvous Guidance Based on J(2)-Perturbed State Transition Matrix Academic Article

abstract

• 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.

authors

• Vadali, Srinivas

published proceedings

• JOURNAL OF GUIDANCE CONTROL AND DYNAMICS

author list (cited authors)

• Li, J., Vadali, S. R., & Hexi, B.

citation count

• 2

complete list of authors

• Li, Jingyang||Vadali, Srinivas R||Hexi, Baoyin

publication date

• February 2015

publisher

• American Institute of Aeronautics and Astronautics (AIAA)  Publisher

published in

• Journal of Guidance, Control, and Dynamics  Journal

keywords

• 40 Engineering
• 4001 Aerospace Engineering
• 4007 Control Engineering, Mechatronics And Robotics
• 4017 Mechanical Engineering

Digital Object Identifier (DOI)

• 10.2514/1.G000813

start page

• 315

end page

• 321

volume

• 38

issue

• 2

URL

• http://dx.doi.org/10.2514/1.g000813