Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit
This paper studies the formidable challenges posed by space debris during spacecraft operations, specifically focusing on the potential threats arising from the disintegration of a proximate satellite. The disintegration of a satellite could spawn debris fragments that may acquire diverse velocities...
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| Format: | Article |
| Language: | English |
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American Association for the Advancement of Science (AAAS)
2025-01-01
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| Series: | Space: Science & Technology |
| Online Access: | https://spj.science.org/doi/10.34133/space.0266 |
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| _version_ | 1849731646068097024 |
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| author | Ming Wen Shaozhao Lu Yao Zhang Hongbo Wang Ji Ye |
| author_facet | Ming Wen Shaozhao Lu Yao Zhang Hongbo Wang Ji Ye |
| author_sort | Ming Wen |
| collection | DOAJ |
| description | This paper studies the formidable challenges posed by space debris during spacecraft operations, specifically focusing on the potential threats arising from the disintegration of a proximate satellite. The disintegration of a satellite could spawn debris fragments that may acquire diverse velocities, markedly complicating the avoidance maneuvers essential for the active spacecraft to sustain its original orbit. To address this issue, the principle of maneuvering reachable domain is introduced to model the debris swarm incorporating uncertainties in both velocity and trajectory following disintegration. Based on this model, a 3-impulse maneuver strategy is proposed to facilitate the active spacecraft through the debris swarm, enabling its safe return to the original orbit. To demonstrate the efficacy of this approach, 2 distinct types of orbital scenarios are simulated: one with a short rendezvous period and the other characterized by an extended hovering duration. These simulation results indicate that the propagation model of debris swarm with the maneuver strategy enables the active spacecraft to maneuver through the debris swarm along with an optimal evasion trajectory, thereby ensuring its safe return to the original orbit. |
| format | Article |
| id | doaj-art-69f593db84754b17ba18ee2e775f50e7 |
| institution | DOAJ |
| issn | 2692-7659 |
| language | English |
| publishDate | 2025-01-01 |
| publisher | American Association for the Advancement of Science (AAAS) |
| record_format | Article |
| series | Space: Science & Technology |
| spelling | doaj-art-69f593db84754b17ba18ee2e775f50e72025-08-20T03:08:28ZengAmerican Association for the Advancement of Science (AAAS)Space: Science & Technology2692-76592025-01-01510.34133/space.0266Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original OrbitMing Wen0Shaozhao Lu1Yao Zhang2Hongbo Wang3Ji Ye4School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China.Institute of Telecommunication and Navigation Satellite, China Academy of Space Technology, Beijing 100094, China.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China.This paper studies the formidable challenges posed by space debris during spacecraft operations, specifically focusing on the potential threats arising from the disintegration of a proximate satellite. The disintegration of a satellite could spawn debris fragments that may acquire diverse velocities, markedly complicating the avoidance maneuvers essential for the active spacecraft to sustain its original orbit. To address this issue, the principle of maneuvering reachable domain is introduced to model the debris swarm incorporating uncertainties in both velocity and trajectory following disintegration. Based on this model, a 3-impulse maneuver strategy is proposed to facilitate the active spacecraft through the debris swarm, enabling its safe return to the original orbit. To demonstrate the efficacy of this approach, 2 distinct types of orbital scenarios are simulated: one with a short rendezvous period and the other characterized by an extended hovering duration. These simulation results indicate that the propagation model of debris swarm with the maneuver strategy enables the active spacecraft to maneuver through the debris swarm along with an optimal evasion trajectory, thereby ensuring its safe return to the original orbit.https://spj.science.org/doi/10.34133/space.0266 |
| spellingShingle | Ming Wen Shaozhao Lu Yao Zhang Hongbo Wang Ji Ye Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit Space: Science & Technology |
| title | Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit |
| title_full | Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit |
| title_fullStr | Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit |
| title_full_unstemmed | Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit |
| title_short | Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit |
| title_sort | three impulse model for spacecraft to avoid space debris and return to the original orbit |
| url | https://spj.science.org/doi/10.34133/space.0266 |
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