摘要: A computational algorithm is developed for finding the minimum-fuel two-impulse rendezvous trajectory between an interceptor and a target spacecraft whose orbits are initially specified. The parametric optimization is based on res... 展开 A computational algorithm is developed for finding the minimum-fuel two-impulse rendezvous trajectory between an interceptor and a target spacecraft whose orbits are initially specified. The parametric optimization is based on restricted two-body dynamics and is applicable to rendezvous between non-coplanar ellipses. A minimum allowable perigee radius constraint is incorporated to insure the resulting two-body trajectory does not inadvertently lead to re-entry. The algorithm is implemented in a Fortran 4 computer program and some typical results are included. 收起