An Algorithm for Minimum-Fuel Two-Impulse Rendezvous.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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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.
- Computer Programming and Software
- Spacecraft Trajectories and Reentry