| Spacecraft motion analysis about rapid rotating small body |
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| 作者姓名： | 史雪岩 崔祜涛 崔平远 栾恩杰 |
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| 作者单位： | Deep Space Exploration Research Center，Harbin Institute of Technology，Deep Space Exploration Research Center，Harbin Institute of Technology，Deep Space Exploration Research Center，Harbin Institute of Technology，China National Space Adminstration Harbin 150001，China，Harbin 150001，China，Harbin 150001，China，Beijing 100037，China |
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| 摘 要： | 0 INTRODUCTIONExploringsmallbodiessuchascometsandasteroidsisoneofthemostsophisticatedmissionscurrentlybeinginvestigatedindeepspaceexploration .Butinformationofasmallbodysuchasshape ,mass ,densitycompositionandrotationaldynamicislittleknown .Soit’sachallengetoanalysisthestabilityoforbitaroundasmallbody .NEARmissionofAPLandROSETTAplanofESAre quiredtoanalysisstabilityoforbitaroundasmallbody .Thisattractedalotofresearcherstostudyonthedynami calenvironment ,orbitalstablecharacterizati…
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Spacecraft motion analysis about rapid rotating small body |
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| SHI Xue-yan.Spacecraft motion analysis about rapid rotating small body[J].Journal of Harbin Institute of Technology,2003,10(4). |
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| Authors: | SHI Xue-yan |
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| Affiliation: | 1. Deep Space Exploration Research Center, Harbin Institute of Technology, Harbin 150001, China
2. China National Space Adminstration, Beijing 100037,China |
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| Abstract: | The orbital dynamics equation of a spacecraft around an irregular sphere small body is established based on the small body' s gravitational potential approximated with a tri-axial ellipsoid. According to the Jacobi integral constant, the spacecraft zero-velocity curves in the vicinity of the small body is described and feasible motion region is analyzed. The limited condition and the periapsis radius corresponding to different eccentricity against impact surface are presented. The stability of direct and retrograde equator orbits is analyzed based on the perturbation solutions of mean orbit elements. |
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| Keywords: | spacecraft orbital dynamics small body |
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