The Optimal Transfer Trajectory Design Based On Intelligent Optimization Algorithm

Nowadays, the aerospace industry is an important symbol to measure the level of countries’ technology. The development of the aerospace industry is complex and difficult and involves almost all over the field of industry, which has been attracted increasingly attention. As the one of three important aerospace technologies, the importance of the space rendezvous technology is evident. Although many countries have achieved rendezvous and docking mission, the technology is not mature yet due to its complexity and high risk. In addition, considering high cost and consumption of the aerospace industry, it is worth to study and discuss how to design an orbital transfer process to achieve saving fuel and reducing transfer time. In this paper, Lambert problem of the spacecraft rendezvous theory is investigated. Meanwhile, models are established at the earth inertial coordinate system according to the spacecraft’s orbital elements and orbital position and velocity vector. Three intelligent optimization algorithms, such as enumeration method, genetic algorithm and harmony search algorithm, are applied to trajectory optimization. The main sections are as follows.Firstly, establish the orbital model and kinematics of target and spacecraft. In order to clearly descript spacecraft rendezvous process, the characteristics of satellite problems are introduced. And the relational equation of orbital elements and position and velocity vectors is established, which lays the foundation for the Lambert problems and optimization design.Secondly, for non-co-planar transfer trajectory of space rendezvous based on Lambert problem, three methods including Bisection by iterating semi-major axis, Battin-Vaughan algorithm and Graphic Semi-major axis iteration algorithm are proposed to solve the Lambert problem. The core ideas and steps of the three algorithms are presented. Using two examples to demonstrate the effectiveness of the three algorithms, and the efficiency and accuracy of the three algorithms are compared to analysis the conclusion.Finally, this paper investigates transfer orbital trajectory optimization problem from constraints analysis, parameter selection, objective function definition and optimization algorithm selection four aspects. First of all, analyze space constraints. Investigate the effluence of the true anomaly and the transfer time on fuel consumption. Then, single-objective and multi-objective optimization for transfer orbit rendezvous based on the fuel consumption and transfer time is designed. Thirdly, use enumeration method, genetic algorithm and harmony search algorithm as the main optimization methods. The core and design ideas of the three methods are discussed. Combined with process constraints, the simulation of the three optimization algorithms is taken to prove the accuracy. This paper provides reference and basis for the transfer orbit optimization.