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...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2012-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2012/152683 |
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| _version_ | 1849395956249788416 |
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| author | Francesco Simeoni Lorenzo Casalino Alessandro Zavoli Guido Colasurdo |
| author_facet | Francesco Simeoni Lorenzo Casalino Alessandro Zavoli Guido Colasurdo |
| author_sort | Francesco Simeoni |
| collection | DOAJ |
| description | 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. |
| format | Article |
| id | doaj-art-b54a4283b5ca40efb2e8106cf96a96b4 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2012-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-b54a4283b5ca40efb2e8106cf96a96b42025-08-20T03:39:28ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742012-01-01201210.1155/2012/152683152683Indirect Optimization of Satellite Deployment into a Highly Elliptic OrbitFrancesco Simeoni0Lorenzo Casalino1Alessandro Zavoli2Guido Colasurdo3Dipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDipartimento di Ingegneria Meccanica e Aerospaziale, Politecnico di Torino, Corso Duca degli Abruzzi 24, 10129 Torino, ItalyDipartimento di Ingegneria Meccanica e Aerospaziale, Sapienza Università di Roma, Via Eudossiana 18, 00184 Roma, ItalyDipartimento di Ingegneria Meccanica e Aerospaziale, Sapienza Università di Roma, Via Eudossiana 18, 00184 Roma, ItalyThe 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.http://dx.doi.org/10.1155/2012/152683 |
| spellingShingle | Francesco Simeoni Lorenzo Casalino Alessandro Zavoli Guido Colasurdo Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit International Journal of Aerospace Engineering |
| title | Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit |
| title_full | Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit |
| title_fullStr | Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit |
| title_full_unstemmed | Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit |
| title_short | Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit |
| title_sort | indirect optimization of satellite deployment into a highly elliptic orbit |
| url | http://dx.doi.org/10.1155/2012/152683 |
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