Abstract
In this paper, the minimum-fuel, time-fixed optimal multiple-impulse rendezvous between non-coplanar elliptic orbits considering the J2 perturbation effects was mainly studied. Based on the perturbation theory, the kinetic equation of spacecraft rendezvous considering the J2 perturbation effects was deduced. The nonlinear programming model of optimal multi-impulse rendezvous was set up, and the optimization results of three-impulse and four-impulse were presented, the times, magnitudes and directions of optimal impulses were individually obtained. Finally, a great lot of simulations were done to investigate the fuel consumption with different time and impulses restraint.
| Original language | English |
|---|---|
| Pages (from-to) | 472-475 |
| Number of pages | 4 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 29 |
| Issue number | 2 |
| State | Published - Mar 2008 |
Keywords
- J2 perturbation
- Multiple-impulse maneuver
- Nonlinear programming
- Space rendezvous
- Trajectory optimization
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