Maneuver Design Using Relative Orbital Elements
Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-hori...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Spencer, David A. [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2015 |
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| Schlagwörter: |
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| Anmerkung: |
© American Astronautical Society 2015 |
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| Übergeordnetes Werk: |
Enthalten in: The Journal of the Astronautical Sciences - Springer-Verlag, 2006, 62(2015), 4 vom: Dez., Seite 315-350 |
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| Übergeordnetes Werk: |
volume:62 ; year:2015 ; number:4 ; month:12 ; pages:315-350 |
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| DOI / URN: |
10.1007/s40295-015-0072-y |
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| 520 | |a Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. | ||
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10.1007/s40295-015-0072-y doi (DE-627)SPR036457086 (SPR)s40295-015-0072-y-e DE-627 ger DE-627 rakwb eng Spencer, David A. verfasserin (orcid)0000-0003-0799-7491 aut Maneuver Design Using Relative Orbital Elements 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society 2015 Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. Orbital mechanics (dpeaa)DE-He213 Relative motion (dpeaa)DE-He213 Proximity operations (dpeaa)DE-He213 Lovell, Thomas A. aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 62(2015), 4 vom: Dez., Seite 315-350 (DE-627)SPR036426385 nnns volume:62 year:2015 number:4 month:12 pages:315-350 https://dx.doi.org/10.1007/s40295-015-0072-y lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 62 2015 4 12 315-350 |
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10.1007/s40295-015-0072-y doi (DE-627)SPR036457086 (SPR)s40295-015-0072-y-e DE-627 ger DE-627 rakwb eng Spencer, David A. verfasserin (orcid)0000-0003-0799-7491 aut Maneuver Design Using Relative Orbital Elements 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society 2015 Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. Orbital mechanics (dpeaa)DE-He213 Relative motion (dpeaa)DE-He213 Proximity operations (dpeaa)DE-He213 Lovell, Thomas A. aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 62(2015), 4 vom: Dez., Seite 315-350 (DE-627)SPR036426385 nnns volume:62 year:2015 number:4 month:12 pages:315-350 https://dx.doi.org/10.1007/s40295-015-0072-y lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 62 2015 4 12 315-350 |
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10.1007/s40295-015-0072-y doi (DE-627)SPR036457086 (SPR)s40295-015-0072-y-e DE-627 ger DE-627 rakwb eng Spencer, David A. verfasserin (orcid)0000-0003-0799-7491 aut Maneuver Design Using Relative Orbital Elements 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society 2015 Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. Orbital mechanics (dpeaa)DE-He213 Relative motion (dpeaa)DE-He213 Proximity operations (dpeaa)DE-He213 Lovell, Thomas A. aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 62(2015), 4 vom: Dez., Seite 315-350 (DE-627)SPR036426385 nnns volume:62 year:2015 number:4 month:12 pages:315-350 https://dx.doi.org/10.1007/s40295-015-0072-y lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 62 2015 4 12 315-350 |
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10.1007/s40295-015-0072-y doi (DE-627)SPR036457086 (SPR)s40295-015-0072-y-e DE-627 ger DE-627 rakwb eng Spencer, David A. verfasserin (orcid)0000-0003-0799-7491 aut Maneuver Design Using Relative Orbital Elements 2015 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society 2015 Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. Orbital mechanics (dpeaa)DE-He213 Relative motion (dpeaa)DE-He213 Proximity operations (dpeaa)DE-He213 Lovell, Thomas A. aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 62(2015), 4 vom: Dez., Seite 315-350 (DE-627)SPR036426385 nnns volume:62 year:2015 number:4 month:12 pages:315-350 https://dx.doi.org/10.1007/s40295-015-0072-y lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 62 2015 4 12 315-350 |
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Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. © American Astronautical Society 2015 |
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Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. © American Astronautical Society 2015 |
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Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit. © American Astronautical Society 2015 |
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<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">SPR036457086</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230328165753.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">201007s2015 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/s40295-015-0072-y</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)SPR036457086</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(SPR)s40295-015-0072-y-e</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Spencer, David A.</subfield><subfield code="e">verfasserin</subfield><subfield code="0">(orcid)0000-0003-0799-7491</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Maneuver Design Using Relative Orbital Elements</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2015</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© American Astronautical Society 2015</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract Relative orbital elements provide a geometric interpretation of the motion of a deputy spacecraft about a chief spacecraft. The formulation yields an intuitive understanding of how the relative motion evolves with time, and by incorporating velocity changes in the local-vertical, local-horizontal component directions, the change in relative motion due to impulsive maneuvers can be evaluated. This paper utilizes a relative orbital element formulation that characterizes relative motion where the chief spacecraft is assumed to be in a circular orbit. Expressions are developed for changes to the relative orbital elements as a function of the impulsive maneuver components in each coordinate direction. A general maneuver strategy is developed for targeting a set of relative orbital elements, and this strategy is applied to scenarios that are relevant for close proximity operations, including establishing a stationary relative orbit, natural motion circumnavigation, and station-keeping in a leading or trailing orbit.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Orbital mechanics</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Relative motion</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Proximity operations</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Lovell, Thomas A.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">The Journal of the Astronautical Sciences</subfield><subfield code="d">Springer-Verlag, 2006</subfield><subfield code="g">62(2015), 4 vom: Dez., Seite 315-350</subfield><subfield code="w">(DE-627)SPR036426385</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:62</subfield><subfield code="g">year:2015</subfield><subfield code="g">number:4</subfield><subfield code="g">month:12</subfield><subfield code="g">pages:315-350</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://dx.doi.org/10.1007/s40295-015-0072-y</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_SPRINGER</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">62</subfield><subfield code="j">2015</subfield><subfield code="e">4</subfield><subfield code="c">12</subfield><subfield code="h">315-350</subfield></datafield></record></collection>
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