Abstract
Fixed-time, continuous thrust, optimal-energy approach program was programmed by using optimal control theory. By setting various terminal conditions, the program could be used in the different multimode approach scenario. Besides, error of C-W equation was analyzed while the satellite runs at LEO. The affections of various initialization conditions on the energy and the characteristic of optimal trajectory were analyzed by simulations.
| Original language | English |
|---|---|
| Pages (from-to) | 2388-2391 |
| Number of pages | 4 |
| Journal | Xitong Fangzhen Xuebao / Journal of System Simulation |
| Volume | 19 |
| Issue number | 10 |
| State | Published - 20 May 2007 |
Keywords
- Concomitant orbit
- Multimode approach
- Orbit transfer
- Relative motion
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