Hits:

Indexed by:期刊论文

Date of Publication:2014-07-01

Journal:NONLINEAR DYNAMICS

Included Journals:SCIE、EI

Volume:77

Issue:1-2

Page Number:321-338

ISSN No.:0924-090X

Key Words:Multi-objective optimization; Nonlinear optimal control; Symplectic algorithm; Circular restricted three-body problem; Low-thrust transfer; Invariant manifold

Abstract:The multi-objective optimization of transfer trajectories from an orbit near Earth to a periodic libration-point orbit in the Sun-Earth system using the mixed low-thrust and invariant-manifold approach is investigated in this paper. A two-objective optimization model is proposed based on the mixed low-thrust and invariant-manifold approach. The circular restricted three-body model (CRTBP) is utilized to represent the motion of a spacecraft in the gravitational field of the Sun and Earth. The transfer trajectory is broken down into several segments; both low-thrust propulsion and stable manifolds are utilized based on the CRTBP in different segments. The fuel cost, which is generated only by the low-thrust trajectory for transferring the spacecraft from an orbit near Earth to a stable manifold, is minimized. The total flight time, which includes the time during which the spacecraft is controlled by the low-thrust trajectory and the time during which the spacecraft is moving on the stable manifold, is also minimized. Using the nondominated sorting genetic algorithm for the resulting multi-objective optimization problem, highly promising Pareto-optimal solutions for the transfer of the spacecraft are found. Via numerical simulations, it is shown that tradeoffs between time of flight and fuel cost can be quickly evaluated using this approach. Furthermore, for the same time of flight, transfer trajectories based on the mixed-transfer method can save a larger amount of fuel than the low-thrust method alone.