Optimal On-Orbit Inspection of Satellite Formation
In a formation-flying mission where multiple spacecraft must cooperate and maintain a prescribed relative separation, the early detection of possible anomalies is a primary requirement. This is possible, for example, by employing an inspector spacecraft whose aim is to monitor the condition of the f...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-10-01
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| Series: | Remote Sensing |
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| Online Access: | https://www.mdpi.com/2072-4292/14/20/5192 |
| _version_ | 1797470066262933504 |
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| author | Andrea Caruso Alessandro A. Quarta Giovanni Mengali Marco Bassetto |
| author_facet | Andrea Caruso Alessandro A. Quarta Giovanni Mengali Marco Bassetto |
| author_sort | Andrea Caruso |
| collection | DOAJ |
| description | In a formation-flying mission where multiple spacecraft must cooperate and maintain a prescribed relative separation, the early detection of possible anomalies is a primary requirement. This is possible, for example, by employing an inspector spacecraft whose aim is to monitor the condition of the formation members with an on-orbit inspection. This paper analyzes a rest-to-rest multiple-impulse transfer that the inspector spacecraft must accomplish to visit all of the formation members. The problem is studied using the linearized Hill–Clohessy–Wiltshire equations and is solved in an optimal framework by minimizing the total velocity variation along the transfer trajectory. The solution algorithm implements a two-step procedure that combines differential evolution algorithms and Nelder–Mead simplex method-based routines. A case study is thoroughly investigated where a formation of six satellites covers a circular orbit of altitude <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>300</mn><mspace width="0.166667em"></mspace><mi>km</mi></mrow></semantics></math></inline-formula> over Earth. The proposed algorithm could efficiently find a solution and with reduced computational times. |
| first_indexed | 2024-03-09T19:31:33Z |
| format | Article |
| id | doaj.art-41380491a90c47c29c6f7d908282e860 |
| institution | Directory Open Access Journal |
| issn | 2072-4292 |
| language | English |
| last_indexed | 2024-03-09T19:31:33Z |
| publishDate | 2022-10-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Remote Sensing |
| spelling | doaj.art-41380491a90c47c29c6f7d908282e8602023-11-24T02:20:56ZengMDPI AGRemote Sensing2072-42922022-10-011420519210.3390/rs14205192Optimal On-Orbit Inspection of Satellite FormationAndrea Caruso0Alessandro A. Quarta1Giovanni Mengali2Marco Bassetto3Department of Industrial Engineering, University of Bologna, I-47121 Forlì, ItalyDepartment of Civil and Industrial Engineering, University of Pisa, I-56122 Pisa, ItalyDepartment of Civil and Industrial Engineering, University of Pisa, I-56122 Pisa, ItalyDepartment of Civil and Industrial Engineering, University of Pisa, I-56122 Pisa, ItalyIn a formation-flying mission where multiple spacecraft must cooperate and maintain a prescribed relative separation, the early detection of possible anomalies is a primary requirement. This is possible, for example, by employing an inspector spacecraft whose aim is to monitor the condition of the formation members with an on-orbit inspection. This paper analyzes a rest-to-rest multiple-impulse transfer that the inspector spacecraft must accomplish to visit all of the formation members. The problem is studied using the linearized Hill–Clohessy–Wiltshire equations and is solved in an optimal framework by minimizing the total velocity variation along the transfer trajectory. The solution algorithm implements a two-step procedure that combines differential evolution algorithms and Nelder–Mead simplex method-based routines. A case study is thoroughly investigated where a formation of six satellites covers a circular orbit of altitude <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mn>300</mn><mspace width="0.166667em"></mspace><mi>km</mi></mrow></semantics></math></inline-formula> over Earth. The proposed algorithm could efficiently find a solution and with reduced computational times.https://www.mdpi.com/2072-4292/14/20/5192satellite formationCubeSat mission designon-orbit inspectiontrajectory optimization |
| spellingShingle | Andrea Caruso Alessandro A. Quarta Giovanni Mengali Marco Bassetto Optimal On-Orbit Inspection of Satellite Formation Remote Sensing satellite formation CubeSat mission design on-orbit inspection trajectory optimization |
| title | Optimal On-Orbit Inspection of Satellite Formation |
| title_full | Optimal On-Orbit Inspection of Satellite Formation |
| title_fullStr | Optimal On-Orbit Inspection of Satellite Formation |
| title_full_unstemmed | Optimal On-Orbit Inspection of Satellite Formation |
| title_short | Optimal On-Orbit Inspection of Satellite Formation |
| title_sort | optimal on orbit inspection of satellite formation |
| topic | satellite formation CubeSat mission design on-orbit inspection trajectory optimization |
| url | https://www.mdpi.com/2072-4292/14/20/5192 |
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