Indirect optimization for finite-thrust Orbital Interception Problem
The nonlinear programming method is used to study the finite-thrust minimum-time orbital interception problem.Considering the spacecraft with fixed impulse,the Modified Equinoctial Elements are used to describe the movement of the spacecraft in the attached coordinate,and the model of the orbital interception problem is established.Then the trajectory optimization problem is solved by the nonlinear programming method.The simulations demonstrate that the minimum time orbital interception mission is well accomplished,and the spacecraft fly around the earth with maximum thrust magnitude at whole time history.
Finite-thrust spacecraft Minimum time Orbital interception Nonlinear programming
Yanyi Huang Guodong Chen
The first aeronautical engineering institute of PLA Air Force,Xinyang City,P.R.China
国际会议
济南
英文
1051-1054
2012-12-29(万方平台首次上网日期,不代表论文的发表时间)