Optimization of Tri-impulsive Trajectories to the Moon in Two Restricted Three-Body Systems
- Paper number
IAC-07-A3.I.A.04
- Author
Mr. Hui Yu, Tsinghua University, China
- Coauthor
Dr. Gong Shengping, Tsinghua University, China
- Coauthor
Dr. Hexi Baoyin, Tsinghua University, China
- Coauthor
Mr. Junfeng Li, Tsinghua University, China
- Year
2007
- Abstract
The problem is about the development of transferring a spacecraft from an earth parking orbit to a low orbit of Moon in the Sun-Earth and Earth-Moon frameworks, two planner circular restricted three-body systems. Invariant manifolds of the two systems are connected at a certain patching point, and a ΔV0 maneuver is needed there, and then ΔV1 and ΔV2 are given at the launch and arrival point respectively. Two approximate expressions for the required velocity variation are studied together in order to obtain the minimum ΔV tri-impulsive maneuvers. Genetic algorithm and unconstrained nonlinear optimization are employed to reach the minimum value accurately on the condition that the transfer time could be shorten to the greatest extent. Considering a set of data from previous missions using traditional or fresh methods, it is found that ΔV and transfer times could not reach their minimum at the same time, so the former one is our prime object under the constraint that a giving transfer time is not surpassed. Mathematical preliminaries and mission analysis are presented for the preparation for the solution of the problem. Strategy of minimizing ΔV, including the selection of patching point and the employment of genetic algorithm and unconstrained nonlinear optimization, is given for the computation of the final results. Further, several samples are given in order to pprove the advantage and feasibility of this method. What is the most important is that an effective method is proposed for future work of deeper space exploration in the solar system.
- Abstract document