Parameterized design of abort trajectories with a lunar flyby for a crewed mission.
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| Title: | Parameterized design of abort trajectories with a lunar flyby for a crewed mission. |
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| Authors: | Dong, Tianshan1 (AUTHOR), Luo, Qinqin1 (AUTHOR), Han, Chao1 (AUTHOR) hanchao@buaa.edu.cn, Xu, Ming1 (AUTHOR) |
| Source: | Advances in Space Research. Mar2023, Vol. 71 Issue 6, p2550-2565. 16p. |
| Subjects: | Human space flight, Propellants, Trajectories (Mechanics) |
| Abstract: | • An analytical preliminary design method for abort trajectory with a lunar flyby is proposed based on pseudostate theory. • Two parameters in the design process are taken as variables, then an ergodic representation of the feasible abort trajectories with a certain abort time is developed. • The performances of these abort trajectories in an ergodic representation including duration time, injection propellant and re-entry points distribution are investigated. • The effects of abort time and the nominal mission trajectory on abort trajectories are evaluated. This article proposes an analytical preliminary design method for abort trajectory with a lunar flyby and the trajectory ergodic representation based on parameterization, as well as their application in studying the abort trajectories' characteristics. First, by introducing two parameters, the perilune altitude and the perilune transfer time, the preliminary solution is developed parametrically using pseudostate theory to connect two special Lambert processes. The fast convergence of the improved differential correction under the high-fidelity gravity field verifies the accuracy of the proposed preliminary design method. Next, the two parameters are regarded as a set of variables to define an abort trajectory. Based on this, an ergodic representation of the abort trajectory with a certain abort time is yielded using the proposed design method, which offers a global view of the feasible abort trajectories. In addition, the influences of some factors on the performance of these abort trajectories are investigated based on the proposed design method and ergodic representation. The simulation results show that the abort time and the transfer time of the nominal trajectory significantly affect the ergodic representation and characteristics of the abort trajectory. [ABSTRACT FROM AUTHOR] |
| Copyright of Advances in Space Research is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
| FullText | Text: Availability: 0 |
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| Header | DbId: egs DbLabel: Engineering Source An: 161990377 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
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| Items | – Name: Title Label: Title Group: Ti Data: Parameterized design of abort trajectories with a lunar flyby for a crewed mission. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Dong%2C+Tianshan%22">Dong, Tianshan</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Luo%2C+Qinqin%22">Luo, Qinqin</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Han%2C+Chao%22">Han, Chao</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> hanchao@buaa.edu.cn</i><br /><searchLink fieldCode="AR" term="%22Xu%2C+Ming%22">Xu, Ming</searchLink><relatesTo>1</relatesTo> (AUTHOR) – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Advances+in+Space+Research%22">Advances in Space Research</searchLink>. Mar2023, Vol. 71 Issue 6, p2550-2565. 16p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Human+space+flight%22">Human space flight</searchLink><br /><searchLink fieldCode="DE" term="%22Propellants%22">Propellants</searchLink><br /><searchLink fieldCode="DE" term="%22Trajectories+%28Mechanics%29%22">Trajectories (Mechanics)</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: • An analytical preliminary design method for abort trajectory with a lunar flyby is proposed based on pseudostate theory. • Two parameters in the design process are taken as variables, then an ergodic representation of the feasible abort trajectories with a certain abort time is developed. • The performances of these abort trajectories in an ergodic representation including duration time, injection propellant and re-entry points distribution are investigated. • The effects of abort time and the nominal mission trajectory on abort trajectories are evaluated. This article proposes an analytical preliminary design method for abort trajectory with a lunar flyby and the trajectory ergodic representation based on parameterization, as well as their application in studying the abort trajectories' characteristics. First, by introducing two parameters, the perilune altitude and the perilune transfer time, the preliminary solution is developed parametrically using pseudostate theory to connect two special Lambert processes. The fast convergence of the improved differential correction under the high-fidelity gravity field verifies the accuracy of the proposed preliminary design method. Next, the two parameters are regarded as a set of variables to define an abort trajectory. Based on this, an ergodic representation of the abort trajectory with a certain abort time is yielded using the proposed design method, which offers a global view of the feasible abort trajectories. In addition, the influences of some factors on the performance of these abort trajectories are investigated based on the proposed design method and ergodic representation. The simulation results show that the abort time and the transfer time of the nominal trajectory significantly affect the ergodic representation and characteristics of the abort trajectory. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Advances in Space Research is the property of Pergamon Press - An Imprint of Elsevier Science and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
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| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1016/j.asr.2022.10.068 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 16 StartPage: 2550 Subjects: – SubjectFull: Human space flight Type: general – SubjectFull: Propellants Type: general – SubjectFull: Trajectories (Mechanics) Type: general Titles: – TitleFull: Parameterized design of abort trajectories with a lunar flyby for a crewed mission. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Dong, Tianshan – PersonEntity: Name: NameFull: Luo, Qinqin – PersonEntity: Name: NameFull: Han, Chao – PersonEntity: Name: NameFull: Xu, Ming IsPartOfRelationships: – BibEntity: Dates: – D: 15 M: 03 Text: Mar2023 Type: published Y: 2023 Identifiers: – Type: issn-print Value: 02731177 Numbering: – Type: volume Value: 71 – Type: issue Value: 6 Titles: – TitleFull: Advances in Space Research Type: main |
| ResultId | 1 |
