Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit
The analysis of the optimal strategies for the deployment of a spacecraft into a highly elliptic orbit is carried out by means of an indirect optimization procedure, which is based on the theory of optimal control. The orbit peculiarities require that several perturbations are taken into account: an...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Hindawi Limited
2012-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2012/152683 |
| Summary: | The analysis of the optimal strategies for the deployment of a spacecraft into a highly elliptic orbit is carried out by means of an indirect optimization procedure, which is based
on the theory of optimal control. The orbit peculiarities require that several perturbations
are taken into account: an 8 × 8 model of the Earth potential is adopted and gravitational
perturbations from Moon and Sun together with solar radiation pressure are considered.
A procedure to guarantee convergence and define the optimal switching structure is outlined. Results concerning missions with up to 4.5 revolutions around the Earth are given, and
significant features of this kind of deployment are highlighted. |
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| ISSN: | 1687-5966 1687-5974 |