会议专题

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

2012 2nd International conference on Machinery Electronics and Control Engineering (2012年第二届国际机械电子与控制工程会议(ICMECE 2012))

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)