Research On Design And Optimization Of Transfer Trajectory Based On Invariant Manifold

Three-body libration points has a very important value in deep space explorationmissions.They have not only ideal locations for some special science exploration missions,butalso perfect gateways for the interplanetary exploration.This have aroused great interest andintent ever since this century began.In this dissertation,the design and optimization of transfertrajectory for space missions is studied.The main contents of this dissertation are as follow:1. The history and development of transfer trajectory design and optimization and recentresearch at home and aborad are summarized. Libration point mission representative is currentlycompleted or in progress.2. The aircraft dynamics equations are derived in the precision ephemeris orbital dynamicsmodel. The motion equations of the aircraft are derived in the circular restricted three-bodymodel(CRTBP). Important concepts such as libration point, Jacobi integral, Zeor-velocitysurface and state transfer matrix were gived. The invariant manifold theory and method forcomputing manifold was introduced. The type and stability of periodic orbit around the librationpoints were analyzed.Finally, the meaning of orbit optimization design is gived. Discuss thelatest research methods and results of optimization theory,providing the preliminary knowledgefor trajectory design and optimization.3. This paper put forward a new method to design transfer trajectory based on thecombination of the three-body model and two-body model and the theory of sphere ofinfluence(SOI). Transfer orbit design can be roughly divided into a rough design and preciseoptimization of the design. First, this chapter give the definition of squi-SOI, based on the theoryof two-body’s SOI, discuss the design of trajectory in CRTBP. According to the intersection ofinvariant manifolds and the primary body, transfer trajectory design can be divided into twocases, single-impulse when they can intersection and two-impulse when they can’t intersection.Second give the definition of poincare plane, improve the shortcomings of computationalcomplexity. Finally a low-energy trajectory from the moon’s parking orbit to earth-moon systemL1point is designed using this methods.4. This chapter discuss the multi-objective global optimization algorithm base on geneticalgorithm(GA), and the general principles of GA’s control parameters. The precise optimizationof transfer trajectory design often need to consider many-sided constraints such as feul,time andso on.This problem is an nonlinear multi-objective optimization problem with the constraints.Traditional optimization methods is difficult to get a global minimize of this problem. Thischapter analyzes the GA,PSO,DE,SA’s performance in optimizinig the multi-objective optimization problem.Given the general description of transfer trajectory optimizeproblem,discuss the global optimization methods in trajectory design.And using GA forexample,given the general methods to setting the parameter of GA in the applicationprocess.Finally,an earth-mars transfer trajectory was designed using this methods.And discussedthe application of GA in this optimization process,the simulation results shows the method isefficient and reliable.5. Combination of low-thrust theory and invariant manifolds theory.Given the mathematicalmodels and the general steps of the design and optimize of low-thrust manifolds transfertrajectory.Providing the foundation for future research and applications.