Autonomous Lunar Orbit Rendezvous Guidance based on a High order Perturbed State Transition Matrix
- Paper number
IAC-15,A3,2C,14,x30598
- Author
Mr. Jingyang Li, Tsinghua University School of Aerospace, China
- Coauthor
Mr. Mingwei Yin, Tsinghua University, China
- Coauthor
Dr. Hexi Baoyin, Tsinghua University, China
- Year
2015
- Abstract
This paper affirms that a high order perturbed relative motion state transition matrix (STM) can be adopted for the real-time optimization of multi-impulse rendezvous guidance of a lunar lander. The first few non-spherical gravitational perturbation terms J2, C22, J4, and J6 are considered analytically in this STM. A curvilinear coordinate system is used to minimize linearization errors in the transformation between the relative state and the corresponding differential orbital elements. The novel optimization method allows for a systematic design and refinement of the number of thrust impulses, their application times, and the mission duration. The gradients of the objective function and constraints are developed analytically by using a linear perturbation theory. Numerical examples are presented to demonstrate the accuracy and application of this approach in conjunction with a high-fidelity gravitational model. A performance comparison between the impulsive and finite-burn models is also presented. The results indicate that the use of the high order perturbed STM provides an accurate initial solution which can be further optimized on a high-fidelity and finite-burn models, leading to fast convergence of the optimization process. This procedure is well-suited for onboard, real-time control of lunar rendezvous missions.
- Abstract document
- Manuscript document
(absent)