Solar sail optimal maneuvers for heliocentric orbit apse line rotation

The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the fin...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Quarta, Alessandro A. [verfasserIn] Mengali, Giovanni [verfasserIn] Niccolai, Lorenzo [verfasserIn] Bianchi, Christian [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2022

Schlagwörter:	Solar sail Apse line rotation Planet-following orbit Trajectory optimization

Übergeordnetes Werk:	Enthalten in: Acta astronautica - Amsterdam [u.a.] : Elsevier Science, 1974, 198, Seite 410-420
Übergeordnetes Werk:	volume:198 ; pages:410-420

DOI / URN:	10.1016/j.actaastro.2022.06.022

Katalog-ID:	ELV008204802

Internformat


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100	1		\|a Quarta, Alessandro A. \|e verfasserin \|0 (orcid)0000-0003-0811-0231 \|4 aut
245	1	0	\|a Solar sail optimal maneuvers for heliocentric orbit apse line rotation
264		1	\|c 2022
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337			\|a Computermedien \|b c \|2 rdamedia
338			\|a Online-Ressource \|b cr \|2 rdacarrier
520			\|a The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit.
650		4	\|a Solar sail
650		4	\|a Apse line rotation
650		4	\|a Planet-following orbit
650		4	\|a Trajectory optimization
700	1		\|a Mengali, Giovanni \|e verfasserin \|0 (orcid)0000-0002-4277-1765 \|4 aut
700	1		\|a Niccolai, Lorenzo \|e verfasserin \|0 (orcid)0000-0003-3143-2589 \|4 aut
700	1		\|a Bianchi, Christian \|e verfasserin \|0 (orcid)0000-0003-0577-8818 \|4 aut
773	0	8	\|i Enthalten in \|t Acta astronautica \|d Amsterdam [u.a.] : Elsevier Science, 1974 \|g 198, Seite 410-420 \|h Online-Ressource \|w (DE-627)320521273 \|w (DE-600)2014614-0 \|w (DE-576)255600372 \|x 0094-5765 \|7 nnns
773	1	8	\|g volume:198 \|g pages:410-420
912			\|a GBV_USEFLAG_U
912			\|a SYSFLAG_U
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912			\|a GBV_ILN_22
912			\|a GBV_ILN_23
912			\|a GBV_ILN_24
912			\|a GBV_ILN_31
912			\|a GBV_ILN_32
912			\|a GBV_ILN_40
912			\|a GBV_ILN_60
912			\|a GBV_ILN_62
912			\|a GBV_ILN_63
912			\|a GBV_ILN_65
912			\|a GBV_ILN_69
912			\|a GBV_ILN_70
912			\|a GBV_ILN_73
912			\|a GBV_ILN_74
912			\|a GBV_ILN_90
912			\|a GBV_ILN_95
912			\|a GBV_ILN_100
912			\|a GBV_ILN_105
912			\|a GBV_ILN_110
912			\|a GBV_ILN_150
912			\|a GBV_ILN_151
912			\|a GBV_ILN_224
912			\|a GBV_ILN_370
912			\|a GBV_ILN_602
912			\|a GBV_ILN_702
912			\|a GBV_ILN_2003
912			\|a GBV_ILN_2004
912			\|a GBV_ILN_2005
912			\|a GBV_ILN_2006
912			\|a GBV_ILN_2008
912			\|a GBV_ILN_2010
912			\|a GBV_ILN_2011
912			\|a GBV_ILN_2014
912			\|a GBV_ILN_2015
912			\|a GBV_ILN_2020
912			\|a GBV_ILN_2021
912			\|a GBV_ILN_2025
912			\|a GBV_ILN_2027
912			\|a GBV_ILN_2034
912			\|a GBV_ILN_2038
912			\|a GBV_ILN_2044
912			\|a GBV_ILN_2048
912			\|a GBV_ILN_2049
912			\|a GBV_ILN_2050
912			\|a GBV_ILN_2056
912			\|a GBV_ILN_2059
912			\|a GBV_ILN_2061
912			\|a GBV_ILN_2064
912			\|a GBV_ILN_2065
912			\|a GBV_ILN_2068
912			\|a GBV_ILN_2088
912			\|a GBV_ILN_2111
912			\|a GBV_ILN_2112
912			\|a GBV_ILN_2113
912			\|a GBV_ILN_2118
912			\|a GBV_ILN_2122
912			\|a GBV_ILN_2129
912			\|a GBV_ILN_2143
912			\|a GBV_ILN_2147
912			\|a GBV_ILN_2148
912			\|a GBV_ILN_2152
912			\|a GBV_ILN_2153
912			\|a GBV_ILN_2190
912			\|a GBV_ILN_2336
912			\|a GBV_ILN_2470
912			\|a GBV_ILN_2507
912			\|a GBV_ILN_2522
912			\|a GBV_ILN_4035
912			\|a GBV_ILN_4037
912			\|a GBV_ILN_4046
912			\|a GBV_ILN_4112
912			\|a GBV_ILN_4125
912			\|a GBV_ILN_4126
912			\|a GBV_ILN_4242
912			\|a GBV_ILN_4251
912			\|a GBV_ILN_4305
912			\|a GBV_ILN_4307
912			\|a GBV_ILN_4313
912			\|a GBV_ILN_4322
912			\|a GBV_ILN_4323
912			\|a GBV_ILN_4324
912			\|a GBV_ILN_4325
912			\|a GBV_ILN_4326
912			\|a GBV_ILN_4333
912			\|a GBV_ILN_4334
912			\|a GBV_ILN_4335
912			\|a GBV_ILN_4338
912			\|a GBV_ILN_4393
936	b	k	\|a 55.60 \|j Raumfahrttechnik
936	b	k	\|a 50.93 \|j Weltraumforschung
951			\|a AR
952			\|d 198 \|h 410-420

Indexfelder

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publishDate	2022
allfields	10.1016/j.actaastro.2022.06.022 doi (DE-627)ELV008204802 (ELSEVIER)S0094-5765(22)00312-5 DE-627 ger DE-627 rda eng 520 DE-600 55.60 bkl 50.93 bkl Quarta, Alessandro A. verfasserin (orcid)0000-0003-0811-0231 aut Solar sail optimal maneuvers for heliocentric orbit apse line rotation 2022 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit. Solar sail Apse line rotation Planet-following orbit Trajectory optimization Mengali, Giovanni verfasserin (orcid)0000-0002-4277-1765 aut Niccolai, Lorenzo verfasserin (orcid)0000-0003-3143-2589 aut Bianchi, Christian verfasserin (orcid)0000-0003-0577-8818 aut Enthalten in Acta astronautica Amsterdam [u.a.] : Elsevier Science, 1974 198, Seite 410-420 Online-Ressource (DE-627)320521273 (DE-600)2014614-0 (DE-576)255600372 0094-5765 nnns volume:198 pages:410-420 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 55.60 Raumfahrttechnik 50.93 Weltraumforschung AR 198 410-420
spelling	10.1016/j.actaastro.2022.06.022 doi (DE-627)ELV008204802 (ELSEVIER)S0094-5765(22)00312-5 DE-627 ger DE-627 rda eng 520 DE-600 55.60 bkl 50.93 bkl Quarta, Alessandro A. verfasserin (orcid)0000-0003-0811-0231 aut Solar sail optimal maneuvers for heliocentric orbit apse line rotation 2022 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit. Solar sail Apse line rotation Planet-following orbit Trajectory optimization Mengali, Giovanni verfasserin (orcid)0000-0002-4277-1765 aut Niccolai, Lorenzo verfasserin (orcid)0000-0003-3143-2589 aut Bianchi, Christian verfasserin (orcid)0000-0003-0577-8818 aut Enthalten in Acta astronautica Amsterdam [u.a.] : Elsevier Science, 1974 198, Seite 410-420 Online-Ressource (DE-627)320521273 (DE-600)2014614-0 (DE-576)255600372 0094-5765 nnns volume:198 pages:410-420 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 55.60 Raumfahrttechnik 50.93 Weltraumforschung AR 198 410-420
allfields_unstemmed	10.1016/j.actaastro.2022.06.022 doi (DE-627)ELV008204802 (ELSEVIER)S0094-5765(22)00312-5 DE-627 ger DE-627 rda eng 520 DE-600 55.60 bkl 50.93 bkl Quarta, Alessandro A. verfasserin (orcid)0000-0003-0811-0231 aut Solar sail optimal maneuvers for heliocentric orbit apse line rotation 2022 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit. Solar sail Apse line rotation Planet-following orbit Trajectory optimization Mengali, Giovanni verfasserin (orcid)0000-0002-4277-1765 aut Niccolai, Lorenzo verfasserin (orcid)0000-0003-3143-2589 aut Bianchi, Christian verfasserin (orcid)0000-0003-0577-8818 aut Enthalten in Acta astronautica Amsterdam [u.a.] : Elsevier Science, 1974 198, Seite 410-420 Online-Ressource (DE-627)320521273 (DE-600)2014614-0 (DE-576)255600372 0094-5765 nnns volume:198 pages:410-420 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 55.60 Raumfahrttechnik 50.93 Weltraumforschung AR 198 410-420
allfieldsGer	10.1016/j.actaastro.2022.06.022 doi (DE-627)ELV008204802 (ELSEVIER)S0094-5765(22)00312-5 DE-627 ger DE-627 rda eng 520 DE-600 55.60 bkl 50.93 bkl Quarta, Alessandro A. verfasserin (orcid)0000-0003-0811-0231 aut Solar sail optimal maneuvers for heliocentric orbit apse line rotation 2022 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit. Solar sail Apse line rotation Planet-following orbit Trajectory optimization Mengali, Giovanni verfasserin (orcid)0000-0002-4277-1765 aut Niccolai, Lorenzo verfasserin (orcid)0000-0003-3143-2589 aut Bianchi, Christian verfasserin (orcid)0000-0003-0577-8818 aut Enthalten in Acta astronautica Amsterdam [u.a.] : Elsevier Science, 1974 198, Seite 410-420 Online-Ressource (DE-627)320521273 (DE-600)2014614-0 (DE-576)255600372 0094-5765 nnns volume:198 pages:410-420 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 55.60 Raumfahrttechnik 50.93 Weltraumforschung AR 198 410-420
allfieldsSound	10.1016/j.actaastro.2022.06.022 doi (DE-627)ELV008204802 (ELSEVIER)S0094-5765(22)00312-5 DE-627 ger DE-627 rda eng 520 DE-600 55.60 bkl 50.93 bkl Quarta, Alessandro A. verfasserin (orcid)0000-0003-0811-0231 aut Solar sail optimal maneuvers for heliocentric orbit apse line rotation 2022 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit. Solar sail Apse line rotation Planet-following orbit Trajectory optimization Mengali, Giovanni verfasserin (orcid)0000-0002-4277-1765 aut Niccolai, Lorenzo verfasserin (orcid)0000-0003-3143-2589 aut Bianchi, Christian verfasserin (orcid)0000-0003-0577-8818 aut Enthalten in Acta astronautica Amsterdam [u.a.] : Elsevier Science, 1974 198, Seite 410-420 Online-Ressource (DE-627)320521273 (DE-600)2014614-0 (DE-576)255600372 0094-5765 nnns volume:198 pages:410-420 GBV_USEFLAG_U SYSFLAG_U GBV_ELV SSG-OPC-AST GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_150 GBV_ILN_151 GBV_ILN_224 GBV_ILN_370 GBV_ILN_602 GBV_ILN_702 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2008 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2027 GBV_ILN_2034 GBV_ILN_2038 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2190 GBV_ILN_2336 GBV_ILN_2470 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4338 GBV_ILN_4393 55.60 Raumfahrttechnik 50.93 Weltraumforschung AR 198 410-420
language	English
source	Enthalten in Acta astronautica 198, Seite 410-420 volume:198 pages:410-420
sourceStr	Enthalten in Acta astronautica 198, Seite 410-420 volume:198 pages:410-420
format_phy_str_mv	Article
bklname	Raumfahrttechnik Weltraumforschung
institution	findex.gbv.de
topic_facet	Solar sail Apse line rotation Planet-following orbit Trajectory optimization
dewey-raw	520
isfreeaccess_bool	false
container_title	Acta astronautica
authorswithroles_txt_mv	Quarta, Alessandro A. @@aut@@ Mengali, Giovanni @@aut@@ Niccolai, Lorenzo @@aut@@ Bianchi, Christian @@aut@@
publishDateDaySort_date	2022-01-01T00:00:00Z
hierarchy_top_id	320521273
dewey-sort	3520
id	ELV008204802
language_de	englisch
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author	Quarta, Alessandro A.
spellingShingle	Quarta, Alessandro A. ddc 520 bkl 55.60 bkl 50.93 misc Solar sail misc Apse line rotation misc Planet-following orbit misc Trajectory optimization Solar sail optimal maneuvers for heliocentric orbit apse line rotation
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topic_title	520 DE-600 55.60 bkl 50.93 bkl Solar sail optimal maneuvers for heliocentric orbit apse line rotation Solar sail Apse line rotation Planet-following orbit Trajectory optimization
topic	ddc 520 bkl 55.60 bkl 50.93 misc Solar sail misc Apse line rotation misc Planet-following orbit misc Trajectory optimization
topic_unstemmed	ddc 520 bkl 55.60 bkl 50.93 misc Solar sail misc Apse line rotation misc Planet-following orbit misc Trajectory optimization
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title	Solar sail optimal maneuvers for heliocentric orbit apse line rotation
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title_full	Solar sail optimal maneuvers for heliocentric orbit apse line rotation
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title_sort	solar sail optimal maneuvers for heliocentric orbit apse line rotation
title_auth	Solar sail optimal maneuvers for heliocentric orbit apse line rotation
abstract	The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit.
abstractGer	The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit.
abstract_unstemmed	The aim of this work is to investigate the performance of a solar sail-based spacecraft in an optimal apse line rotation maneuver. Considering a heliocentric two-body motion and a low-performance solar sail with an ideal force model, this study derives the optimal steering law that maximizes the final rotation angle of the osculating orbit apse line. Starting from an approximated (Gaussian) form of the Lagrange’s planetary equations, the achievable argument of periapsis and the required flight times are obtained in a parametric way, for given values of parking orbit eccentricity and sail (reference) propulsive acceleration, as the solutions of an optimal control problem. The numerical simulations show that, for sufficiently large values of the orbit eccentricity, the maximum argument of periapsis is roughly proportional to the sail (reference) propulsive acceleration. An approximate locally-optimal steering law is also derived, and the results of the optimization problem are applied to Earth- and Venus-following orbits, where the planets trajectories are assumed to be circular and coplanar with the spacecraft parking orbit.
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title_short	Solar sail optimal maneuvers for heliocentric orbit apse line rotation
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author2	Mengali, Giovanni Niccolai, Lorenzo Bianchi, Christian
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up_date	2024-07-06T18:54:17.611Z
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Solar sail optimal maneuvers for heliocentric orbit apse line rotation

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