Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation

This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without cha...
Ausführliche Beschreibung

Gespeichert in:

Autor*in:	Qiao, Qiao [verfasserIn] Yuan, Jianping [verfasserIn] Wang, Mingming [verfasserIn] Ning, Xin [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2017

Schlagwörter:	PhoneSat Shape actuation Attitude control Particle swarm optimization

Übergeordnetes Werk:	Enthalten in: Aerospace science and technology - Amsterdam [u.a.] : Elsevier Science, 1997, 71, Seite 62-67
Übergeordnetes Werk:	volume:71 ; pages:62-67

DOI / URN:	10.1016/j.ast.2017.09.011

Katalog-ID:	ELV000609153

Internformat


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100	1		\|a Qiao, Qiao \|e verfasserin \|4 aut
245	1	0	\|a Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation
264		1	\|c 2017
336			\|a nicht spezifiziert \|b zzz \|2 rdacontent
337			\|a Computermedien \|b c \|2 rdamedia
338			\|a Online-Ressource \|b cr \|2 rdacarrier
520			\|a This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method.
650		4	\|a PhoneSat
650		4	\|a Shape actuation
650		4	\|a Attitude control
650		4	\|a Particle swarm optimization
700	1		\|a Yuan, Jianping \|e verfasserin \|4 aut
700	1		\|a Wang, Mingming \|e verfasserin \|4 aut
700	1		\|a Ning, Xin \|e verfasserin \|4 aut
773	0	8	\|i Enthalten in \|t Aerospace science and technology \|d Amsterdam [u.a.] : Elsevier Science, 1997 \|g 71, Seite 62-67 \|h Online-Ressource \|w (DE-627)320521486 \|w (DE-600)2014638-3 \|w (DE-576)255630425 \|x 1626-3219 \|7 nnns
773	1	8	\|g volume:71 \|g pages:62-67
912			\|a GBV_USEFLAG_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_34
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_2001
912			\|a GBV_ILN_2003
912			\|a GBV_ILN_2004
912			\|a GBV_ILN_2005
912			\|a GBV_ILN_2006
912			\|a GBV_ILN_2007
912			\|a GBV_ILN_2008
912			\|a GBV_ILN_2009
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_2026
912			\|a GBV_ILN_2027
912			\|a GBV_ILN_2031
912			\|a GBV_ILN_2034
912			\|a GBV_ILN_2037
912			\|a GBV_ILN_2038
912			\|a GBV_ILN_2039
912			\|a GBV_ILN_2044
912			\|a GBV_ILN_2048
912			\|a GBV_ILN_2049
912			\|a GBV_ILN_2050
912			\|a GBV_ILN_2055
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_2070
912			\|a GBV_ILN_2086
912			\|a GBV_ILN_2088
912			\|a GBV_ILN_2098
912			\|a GBV_ILN_2106
912			\|a GBV_ILN_2108
912			\|a GBV_ILN_2111
912			\|a GBV_ILN_2112
912			\|a GBV_ILN_2113
912			\|a GBV_ILN_2116
912			\|a GBV_ILN_2118
912			\|a GBV_ILN_2119
912			\|a GBV_ILN_2122
912			\|a GBV_ILN_2129
912			\|a GBV_ILN_2143
912			\|a GBV_ILN_2144
912			\|a GBV_ILN_2147
912			\|a GBV_ILN_2148
912			\|a GBV_ILN_2152
912			\|a GBV_ILN_2153
912			\|a GBV_ILN_2188
912			\|a GBV_ILN_2190
912			\|a GBV_ILN_2232
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_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 55.50 \|j Luftfahrzeugtechnik
936	b	k	\|a 55.60 \|j Raumfahrttechnik
936	b	k	\|a 55.60 \|j Raumfahrttechnik
951			\|a AR
952			\|d 71 \|h 62-67

Indexfelder

author_variant	q q qq j y jy m w mw x n xn
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publishDate	2017
allfields	10.1016/j.ast.2017.09.011 doi (DE-627)ELV000609153 (ELSEVIER)S1270-9638(16)30270-X DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Qiao, Qiao verfasserin aut Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation 2017 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method. PhoneSat Shape actuation Attitude control Particle swarm optimization Yuan, Jianping verfasserin aut Wang, Mingming verfasserin aut Ning, Xin verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 71, Seite 62-67 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:71 pages:62-67 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_34 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_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 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_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 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 71 62-67
spelling	10.1016/j.ast.2017.09.011 doi (DE-627)ELV000609153 (ELSEVIER)S1270-9638(16)30270-X DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Qiao, Qiao verfasserin aut Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation 2017 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method. PhoneSat Shape actuation Attitude control Particle swarm optimization Yuan, Jianping verfasserin aut Wang, Mingming verfasserin aut Ning, Xin verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 71, Seite 62-67 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:71 pages:62-67 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_34 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_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 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_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 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 71 62-67
allfields_unstemmed	10.1016/j.ast.2017.09.011 doi (DE-627)ELV000609153 (ELSEVIER)S1270-9638(16)30270-X DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Qiao, Qiao verfasserin aut Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation 2017 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method. PhoneSat Shape actuation Attitude control Particle swarm optimization Yuan, Jianping verfasserin aut Wang, Mingming verfasserin aut Ning, Xin verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 71, Seite 62-67 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:71 pages:62-67 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_34 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_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 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_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 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 71 62-67
allfieldsGer	10.1016/j.ast.2017.09.011 doi (DE-627)ELV000609153 (ELSEVIER)S1270-9638(16)30270-X DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Qiao, Qiao verfasserin aut Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation 2017 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method. PhoneSat Shape actuation Attitude control Particle swarm optimization Yuan, Jianping verfasserin aut Wang, Mingming verfasserin aut Ning, Xin verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 71, Seite 62-67 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:71 pages:62-67 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_34 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_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 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_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 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 71 62-67
allfieldsSound	10.1016/j.ast.2017.09.011 doi (DE-627)ELV000609153 (ELSEVIER)S1270-9638(16)30270-X DE-627 ger DE-627 rda eng 620 DE-600 55.50 bkl 55.60 bkl 55.60 bkl Qiao, Qiao verfasserin aut Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation 2017 nicht spezifiziert zzz rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method. PhoneSat Shape actuation Attitude control Particle swarm optimization Yuan, Jianping verfasserin aut Wang, Mingming verfasserin aut Ning, Xin verfasserin aut Enthalten in Aerospace science and technology Amsterdam [u.a.] : Elsevier Science, 1997 71, Seite 62-67 Online-Ressource (DE-627)320521486 (DE-600)2014638-3 (DE-576)255630425 1626-3219 nnns volume:71 pages:62-67 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_34 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_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2070 GBV_ILN_2086 GBV_ILN_2088 GBV_ILN_2098 GBV_ILN_2106 GBV_ILN_2108 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2116 GBV_ILN_2118 GBV_ILN_2119 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 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_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 55.50 Luftfahrzeugtechnik 55.60 Raumfahrttechnik 55.60 Raumfahrttechnik AR 71 62-67
language	English
source	Enthalten in Aerospace science and technology 71, Seite 62-67 volume:71 pages:62-67
sourceStr	Enthalten in Aerospace science and technology 71, Seite 62-67 volume:71 pages:62-67
format_phy_str_mv	Article
bklname	Luftfahrzeugtechnik Raumfahrttechnik
institution	findex.gbv.de
topic_facet	PhoneSat Shape actuation Attitude control Particle swarm optimization
dewey-raw	620
isfreeaccess_bool	false
container_title	Aerospace science and technology
authorswithroles_txt_mv	Qiao, Qiao @@aut@@ Yuan, Jianping @@aut@@ Wang, Mingming @@aut@@ Ning, Xin @@aut@@
publishDateDaySort_date	2017-01-01T00:00:00Z
hierarchy_top_id	320521486
dewey-sort	3620
id	ELV000609153
language_de	englisch
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author	Qiao, Qiao
spellingShingle	Qiao, Qiao ddc 620 bkl 55.50 bkl 55.60 misc PhoneSat misc Shape actuation misc Attitude control misc Particle swarm optimization Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation
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topic_title	620 DE-600 55.50 bkl 55.60 bkl Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation PhoneSat Shape actuation Attitude control Particle swarm optimization
topic	ddc 620 bkl 55.50 bkl 55.60 misc PhoneSat misc Shape actuation misc Attitude control misc Particle swarm optimization
topic_unstemmed	ddc 620 bkl 55.50 bkl 55.60 misc PhoneSat misc Shape actuation misc Attitude control misc Particle swarm optimization
topic_browse	ddc 620 bkl 55.50 bkl 55.60 misc PhoneSat misc Shape actuation misc Attitude control misc Particle swarm optimization
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title	Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation
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title_full	Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation
author_sort	Qiao, Qiao
journal	Aerospace science and technology
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author_browse	Qiao, Qiao Yuan, Jianping Wang, Mingming Ning, Xin
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format_se	Elektronische Aufsätze
author-letter	Qiao, Qiao
doi_str_mv	10.1016/j.ast.2017.09.011
dewey-full	620
author2-role	verfasserin
title_sort	attitude control of a picosatellite named npu-phonesat based on shape actuation
title_auth	Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation
abstract	This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method.
abstractGer	This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method.
abstract_unstemmed	This paper investigates the attitude control of a modular picosatellite named NPU-PhoneSat based on shape actuation. The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method.
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title_short	Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation
remote_bool	true
author2	Yuan, Jianping Wang, Mingming Ning, Xin
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doi_str	10.1016/j.ast.2017.09.011
up_date	2024-07-06T18:33:09.576Z
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The PhoneSat is composed of multiple blocks connected by active joints. Much like a falling cat can reorient itself in mid-air, this modular PhoneSat could reorient itself without changes in net angular momentum by altering the shape and instantaneous mass distribution during attitude maneuvers. Given size and cost constraints, the number of actuators should be limited. Thus, this paper focuses on the under-actuated case. Optimal attitude control method to steer the PhoneSat to the desired posture is proposed in this paper. The inequality constraints are established based on the capacity of the actuator. Particle Swarm Optimization algorithm is employed to search the optimal control input to achieve the reorientation while satisfying the imposed constraints. The input torque is parameterized by the spline to guarantee that initial and final values of control input are zero. Simulation results of zero-angular-momentum reorientation of the PhoneSat are presented which confirm the effectiveness of the proposed method.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">PhoneSat</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Shape actuation</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Attitude control</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Particle swarm optimization</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Yuan, Jianping</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Wang, Mingming</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Ning, Xin</subfield><subfield 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Attitude control of a picosatellite named NPU-PhoneSat based on shape actuation

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