Inter-orbital low-thrust transfers in an arbitrary field of forces
Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way o...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Sukhanov, A. A. [verfasserIn] |
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| Format: |
Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2013 |
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| Schlagwörter: |
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| Anmerkung: |
© Pleiades Publishing, Ltd. 2013 |
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| Übergeordnetes Werk: |
Enthalten in: Cosmic research - SP MAIK Nauka/Interperiodica, 1964, 51(2013), 2 vom: März, Seite 147-163 |
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| Übergeordnetes Werk: |
volume:51 ; year:2013 ; number:2 ; month:03 ; pages:147-163 |
| Links: |
|---|
| DOI / URN: |
10.1134/S0010952513020056 |
|---|
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OLC2027385819 |
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| 520 | |a Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. | ||
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10.1134/S0010952513020056 doi (DE-627)OLC2027385819 (DE-He213)S0010952513020056-p DE-627 ger DE-627 rakwb eng 520 620 VZ 16,12 ssgn Sukhanov, A. A. verfasserin aut Inter-orbital low-thrust transfers in an arbitrary field of forces 2013 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Pleiades Publishing, Ltd. 2013 Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. Body Problem Cosmic Research Suggested Method Reference Orbit Thrust Vector de A. Prado, A. F. B. aut Enthalten in Cosmic research SP MAIK Nauka/Interperiodica, 1964 51(2013), 2 vom: März, Seite 147-163 (DE-627)129361909 (DE-600)160891-5 (DE-576)014734443 0010-9525 nnns volume:51 year:2013 number:2 month:03 pages:147-163 https://doi.org/10.1134/S0010952513020056 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-AST SSG-OPC-AST SSG-OPC-GEO SSG-OPC-GGO GBV_ILN_40 GBV_ILN_70 AR 51 2013 2 03 147-163 |
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10.1134/S0010952513020056 doi (DE-627)OLC2027385819 (DE-He213)S0010952513020056-p DE-627 ger DE-627 rakwb eng 520 620 VZ 16,12 ssgn Sukhanov, A. A. verfasserin aut Inter-orbital low-thrust transfers in an arbitrary field of forces 2013 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Pleiades Publishing, Ltd. 2013 Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. Body Problem Cosmic Research Suggested Method Reference Orbit Thrust Vector de A. Prado, A. F. B. aut Enthalten in Cosmic research SP MAIK Nauka/Interperiodica, 1964 51(2013), 2 vom: März, Seite 147-163 (DE-627)129361909 (DE-600)160891-5 (DE-576)014734443 0010-9525 nnns volume:51 year:2013 number:2 month:03 pages:147-163 https://doi.org/10.1134/S0010952513020056 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-AST SSG-OPC-AST SSG-OPC-GEO SSG-OPC-GGO GBV_ILN_40 GBV_ILN_70 AR 51 2013 2 03 147-163 |
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10.1134/S0010952513020056 doi (DE-627)OLC2027385819 (DE-He213)S0010952513020056-p DE-627 ger DE-627 rakwb eng 520 620 VZ 16,12 ssgn Sukhanov, A. A. verfasserin aut Inter-orbital low-thrust transfers in an arbitrary field of forces 2013 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Pleiades Publishing, Ltd. 2013 Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. Body Problem Cosmic Research Suggested Method Reference Orbit Thrust Vector de A. Prado, A. F. B. aut Enthalten in Cosmic research SP MAIK Nauka/Interperiodica, 1964 51(2013), 2 vom: März, Seite 147-163 (DE-627)129361909 (DE-600)160891-5 (DE-576)014734443 0010-9525 nnns volume:51 year:2013 number:2 month:03 pages:147-163 https://doi.org/10.1134/S0010952513020056 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-AST SSG-OPC-AST SSG-OPC-GEO SSG-OPC-GGO GBV_ILN_40 GBV_ILN_70 AR 51 2013 2 03 147-163 |
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10.1134/S0010952513020056 doi (DE-627)OLC2027385819 (DE-He213)S0010952513020056-p DE-627 ger DE-627 rakwb eng 520 620 VZ 16,12 ssgn Sukhanov, A. A. verfasserin aut Inter-orbital low-thrust transfers in an arbitrary field of forces 2013 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Pleiades Publishing, Ltd. 2013 Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. Body Problem Cosmic Research Suggested Method Reference Orbit Thrust Vector de A. Prado, A. F. B. aut Enthalten in Cosmic research SP MAIK Nauka/Interperiodica, 1964 51(2013), 2 vom: März, Seite 147-163 (DE-627)129361909 (DE-600)160891-5 (DE-576)014734443 0010-9525 nnns volume:51 year:2013 number:2 month:03 pages:147-163 https://doi.org/10.1134/S0010952513020056 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-AST SSG-OPC-AST SSG-OPC-GEO SSG-OPC-GGO GBV_ILN_40 GBV_ILN_70 AR 51 2013 2 03 147-163 |
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10.1134/S0010952513020056 doi (DE-627)OLC2027385819 (DE-He213)S0010952513020056-p DE-627 ger DE-627 rakwb eng 520 620 VZ 16,12 ssgn Sukhanov, A. A. verfasserin aut Inter-orbital low-thrust transfers in an arbitrary field of forces 2013 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Pleiades Publishing, Ltd. 2013 Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. Body Problem Cosmic Research Suggested Method Reference Orbit Thrust Vector de A. Prado, A. F. B. aut Enthalten in Cosmic research SP MAIK Nauka/Interperiodica, 1964 51(2013), 2 vom: März, Seite 147-163 (DE-627)129361909 (DE-600)160891-5 (DE-576)014734443 0010-9525 nnns volume:51 year:2013 number:2 month:03 pages:147-163 https://doi.org/10.1134/S0010952513020056 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC SSG-OLC-AST SSG-OPC-AST SSG-OPC-GEO SSG-OPC-GGO GBV_ILN_40 GBV_ILN_70 AR 51 2013 2 03 147-163 |
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Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. © Pleiades Publishing, Ltd. 2013 |
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Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. © Pleiades Publishing, Ltd. 2013 |
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Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples. © Pleiades Publishing, Ltd. 2013 |
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1803570908259942400 |
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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">OLC2027385819</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230503033713.0</controlfield><controlfield tag="007">tu</controlfield><controlfield tag="008">200819s2013 xx ||||| 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1134/S0010952513020056</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)OLC2027385819</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-He213)S0010952513020056-p</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="082" ind1="0" ind2="4"><subfield code="a">520</subfield><subfield code="a">620</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="084" ind1=" " ind2=" "><subfield code="a">16,12</subfield><subfield code="2">ssgn</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Sukhanov, A. A.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Inter-orbital low-thrust transfers in an arbitrary field of forces</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2013</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">ohne Hilfsmittel zu benutzen</subfield><subfield code="b">n</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Band</subfield><subfield code="b">nc</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© Pleiades Publishing, Ltd. 2013</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract Low-thrust transfers between preset orbits are considered in the presence of perturbations of different origin. A simple method of finding the transfer trajectory is suggested, based on linearization of motion near reference orbits. The required accuracy of calculations is achieved by way of increasing the number of reference orbits. The method can also be used in the case of a large number of revolutions around the attracting center: no averaging of motion is required in this case. The suggested method is applicable as well, when the final orbit is specified partially and when there are constraints on the thrust direction. The optimal solution to the linearized problem is not optimal for the original problem; closeness of solutions to these two problems is estimated using a numerical example. Capabilities of the method are also illustrated by examples.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Body Problem</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Cosmic Research</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Suggested Method</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Reference Orbit</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Thrust Vector</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">de A. Prado, A. F. B.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Cosmic research</subfield><subfield code="d">SP MAIK Nauka/Interperiodica, 1964</subfield><subfield code="g">51(2013), 2 vom: März, Seite 147-163</subfield><subfield code="w">(DE-627)129361909</subfield><subfield code="w">(DE-600)160891-5</subfield><subfield code="w">(DE-576)014734443</subfield><subfield code="x">0010-9525</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:51</subfield><subfield code="g">year:2013</subfield><subfield code="g">number:2</subfield><subfield code="g">month:03</subfield><subfield code="g">pages:147-163</subfield></datafield><datafield tag="856" ind1="4" ind2="1"><subfield code="u">https://doi.org/10.1134/S0010952513020056</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_OLC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-TEC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-AST</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OPC-AST</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OPC-GEO</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OPC-GGO</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_40</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_70</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">51</subfield><subfield code="j">2013</subfield><subfield code="e">2</subfield><subfield code="c">03</subfield><subfield code="h">147-163</subfield></datafield></record></collection>
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