Optimal V ∞ leveraging maneuvers using gray solar sail
The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the so...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Quarta, Alessandro A. [verfasserIn] |
|---|
| Format: |
E-Artikel |
|---|---|
| Sprache: |
Englisch |
| Erschienen: |
2022transfer abstract |
|---|
| Schlagwörter: |
|---|
| Übergeordnetes Werk: |
Enthalten in: Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience - Baysal, Birol ELSEVIER, 2015, Amsterdam [u.a.] |
|---|---|
| Übergeordnetes Werk: |
volume:126 ; year:2022 ; pages:0 |
| Links: |
|---|
| DOI / URN: |
10.1016/j.ast.2022.107619 |
|---|
| Katalog-ID: |
ELV058077944 |
|---|
| LEADER | 01000caa a22002652 4500 | ||
|---|---|---|---|
| 001 | ELV058077944 | ||
| 003 | DE-627 | ||
| 005 | 20230626050255.0 | ||
| 007 | cr uuu---uuuuu | ||
| 008 | 220808s2022 xx |||||o 00| ||eng c | ||
| 024 | 7 | |a 10.1016/j.ast.2022.107619 |2 doi | |
| 028 | 5 | 2 | |a /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica |
| 035 | |a (DE-627)ELV058077944 | ||
| 035 | |a (ELSEVIER)S1270-9638(22)00293-0 | ||
| 040 | |a DE-627 |b ger |c DE-627 |e rakwb | ||
| 041 | |a eng | ||
| 082 | 0 | 4 | |a 610 |q VZ |
| 082 | 0 | 4 | |a 600 |a 670 |q VZ |
| 084 | |a 51.00 |2 bkl | ||
| 100 | 1 | |a Quarta, Alessandro A. |e verfasserin |4 aut | |
| 245 | 1 | 0 | |a Optimal V ∞ leveraging maneuvers using gray solar sail |
| 264 | 1 | |c 2022transfer abstract | |
| 336 | |a nicht spezifiziert |b zzz |2 rdacontent | ||
| 337 | |a nicht spezifiziert |b z |2 rdamedia | ||
| 338 | |a nicht spezifiziert |b zu |2 rdacarrier | ||
| 520 | |a The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. | ||
| 520 | |a The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. | ||
| 650 | 7 | |a Gravity assist |2 Elsevier | |
| 650 | 7 | |a Leveraging maneuvers |2 Elsevier | |
| 650 | 7 | |a Solar sail |2 Elsevier | |
| 650 | 7 | |a Trajectory optimization |2 Elsevier | |
| 700 | 1 | |a Bianchi, Christian |4 oth | |
| 700 | 1 | |a Niccolai, Lorenzo |4 oth | |
| 700 | 1 | |a Mengali, Giovanni |4 oth | |
| 773 | 0 | 8 | |i Enthalten in |n Elsevier Science |a Baysal, Birol ELSEVIER |t Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience |d 2015 |g Amsterdam [u.a.] |w (DE-627)ELV013466232 |
| 773 | 1 | 8 | |g volume:126 |g year:2022 |g pages:0 |
| 856 | 4 | 0 | |u https://doi.org/10.1016/j.ast.2022.107619 |3 Volltext |
| 912 | |a GBV_USEFLAG_U | ||
| 912 | |a GBV_ELV | ||
| 912 | |a SYSFLAG_U | ||
| 912 | |a GBV_ILN_40 | ||
| 936 | b | k | |a 51.00 |j Werkstoffkunde: Allgemeines |q VZ |
| 951 | |a AR | ||
| 952 | |d 126 |j 2022 |h 0 | ||
| author_variant |
a a q aa aaq |
|---|---|
| matchkey_str |
quartaalessandroabianchichristianniccola:2022----:piaveeaigaevruig |
| hierarchy_sort_str |
2022transfer abstract |
| bklnumber |
51.00 |
| publishDate |
2022 |
| allfields |
10.1016/j.ast.2022.107619 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica (DE-627)ELV058077944 (ELSEVIER)S1270-9638(22)00293-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Quarta, Alessandro A. verfasserin aut Optimal V ∞ leveraging maneuvers using gray solar sail 2022transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Elsevier Bianchi, Christian oth Niccolai, Lorenzo oth Mengali, Giovanni oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:126 year:2022 pages:0 https://doi.org/10.1016/j.ast.2022.107619 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 126 2022 0 |
| spelling |
10.1016/j.ast.2022.107619 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica (DE-627)ELV058077944 (ELSEVIER)S1270-9638(22)00293-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Quarta, Alessandro A. verfasserin aut Optimal V ∞ leveraging maneuvers using gray solar sail 2022transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Elsevier Bianchi, Christian oth Niccolai, Lorenzo oth Mengali, Giovanni oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:126 year:2022 pages:0 https://doi.org/10.1016/j.ast.2022.107619 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 126 2022 0 |
| allfields_unstemmed |
10.1016/j.ast.2022.107619 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica (DE-627)ELV058077944 (ELSEVIER)S1270-9638(22)00293-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Quarta, Alessandro A. verfasserin aut Optimal V ∞ leveraging maneuvers using gray solar sail 2022transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Elsevier Bianchi, Christian oth Niccolai, Lorenzo oth Mengali, Giovanni oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:126 year:2022 pages:0 https://doi.org/10.1016/j.ast.2022.107619 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 126 2022 0 |
| allfieldsGer |
10.1016/j.ast.2022.107619 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica (DE-627)ELV058077944 (ELSEVIER)S1270-9638(22)00293-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Quarta, Alessandro A. verfasserin aut Optimal V ∞ leveraging maneuvers using gray solar sail 2022transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Elsevier Bianchi, Christian oth Niccolai, Lorenzo oth Mengali, Giovanni oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:126 year:2022 pages:0 https://doi.org/10.1016/j.ast.2022.107619 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 126 2022 0 |
| allfieldsSound |
10.1016/j.ast.2022.107619 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica (DE-627)ELV058077944 (ELSEVIER)S1270-9638(22)00293-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Quarta, Alessandro A. verfasserin aut Optimal V ∞ leveraging maneuvers using gray solar sail 2022transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Elsevier Bianchi, Christian oth Niccolai, Lorenzo oth Mengali, Giovanni oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:126 year:2022 pages:0 https://doi.org/10.1016/j.ast.2022.107619 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 126 2022 0 |
| language |
English |
| source |
Enthalten in Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience Amsterdam [u.a.] volume:126 year:2022 pages:0 |
| sourceStr |
Enthalten in Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience Amsterdam [u.a.] volume:126 year:2022 pages:0 |
| format_phy_str_mv |
Article |
| bklname |
Werkstoffkunde: Allgemeines |
| institution |
findex.gbv.de |
| topic_facet |
Gravity assist Leveraging maneuvers Solar sail Trajectory optimization |
| dewey-raw |
610 |
| isfreeaccess_bool |
false |
| container_title |
Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience |
| authorswithroles_txt_mv |
Quarta, Alessandro A. @@aut@@ Bianchi, Christian @@oth@@ Niccolai, Lorenzo @@oth@@ Mengali, Giovanni @@oth@@ |
| publishDateDaySort_date |
2022-01-01T00:00:00Z |
| hierarchy_top_id |
ELV013466232 |
| dewey-sort |
3610 |
| id |
ELV058077944 |
| language_de |
englisch |
| fullrecord |
<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">ELV058077944</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230626050255.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">220808s2022 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1016/j.ast.2022.107619</subfield><subfield code="2">doi</subfield></datafield><datafield tag="028" ind1="5" ind2="2"><subfield code="a">/cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)ELV058077944</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(ELSEVIER)S1270-9638(22)00293-0</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">610</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">600</subfield><subfield code="a">670</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="084" ind1=" " ind2=" "><subfield code="a">51.00</subfield><subfield code="2">bkl</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Quarta, Alessandro A.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Optimal V ∞ leveraging maneuvers using gray solar sail</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2022transfer abstract</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">nicht spezifiziert</subfield><subfield code="b">zzz</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">nicht spezifiziert</subfield><subfield code="b">z</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">nicht spezifiziert</subfield><subfield code="b">zu</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time.</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time.</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Gravity assist</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Leveraging maneuvers</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Solar sail</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Trajectory optimization</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Bianchi, Christian</subfield><subfield code="4">oth</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Niccolai, Lorenzo</subfield><subfield code="4">oth</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Mengali, Giovanni</subfield><subfield code="4">oth</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="n">Elsevier Science</subfield><subfield code="a">Baysal, Birol ELSEVIER</subfield><subfield code="t">Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience</subfield><subfield code="d">2015</subfield><subfield code="g">Amsterdam [u.a.]</subfield><subfield code="w">(DE-627)ELV013466232</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:126</subfield><subfield code="g">year:2022</subfield><subfield code="g">pages:0</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://doi.org/10.1016/j.ast.2022.107619</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_U</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ELV</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_U</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_40</subfield></datafield><datafield tag="936" ind1="b" ind2="k"><subfield code="a">51.00</subfield><subfield code="j">Werkstoffkunde: Allgemeines</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">126</subfield><subfield code="j">2022</subfield><subfield code="h">0</subfield></datafield></record></collection>
|
| author |
Quarta, Alessandro A. |
| spellingShingle |
Quarta, Alessandro A. ddc 610 ddc 600 bkl 51.00 Elsevier Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Optimal V ∞ leveraging maneuvers using gray solar sail |
| authorStr |
Quarta, Alessandro A. |
| ppnlink_with_tag_str_mv |
@@773@@(DE-627)ELV013466232 |
| format |
electronic Article |
| dewey-ones |
610 - Medicine & health 600 - Technology 670 - Manufacturing |
| delete_txt_mv |
keep |
| author_role |
aut |
| collection |
elsevier |
| remote_str |
true |
| illustrated |
Not Illustrated |
| topic_title |
610 VZ 600 670 VZ 51.00 bkl Optimal V ∞ leveraging maneuvers using gray solar sail Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization Elsevier |
| topic |
ddc 610 ddc 600 bkl 51.00 Elsevier Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization |
| topic_unstemmed |
ddc 610 ddc 600 bkl 51.00 Elsevier Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization |
| topic_browse |
ddc 610 ddc 600 bkl 51.00 Elsevier Gravity assist Elsevier Leveraging maneuvers Elsevier Solar sail Elsevier Trajectory optimization |
| format_facet |
Elektronische Aufsätze Aufsätze Elektronische Ressource |
| format_main_str_mv |
Text Zeitschrift/Artikel |
| carriertype_str_mv |
zu |
| author2_variant |
c b cb l n ln g m gm |
| hierarchy_parent_title |
Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience |
| hierarchy_parent_id |
ELV013466232 |
| dewey-tens |
610 - Medicine & health 600 - Technology 670 - Manufacturing |
| hierarchy_top_title |
Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience |
| isfreeaccess_txt |
false |
| familylinks_str_mv |
(DE-627)ELV013466232 |
| title |
Optimal V ∞ leveraging maneuvers using gray solar sail |
| ctrlnum |
(DE-627)ELV058077944 (ELSEVIER)S1270-9638(22)00293-0 |
| title_full |
Optimal V ∞ leveraging maneuvers using gray solar sail |
| author_sort |
Quarta, Alessandro A. |
| journal |
Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience |
| journalStr |
Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience |
| lang_code |
eng |
| isOA_bool |
false |
| dewey-hundreds |
600 - Technology |
| recordtype |
marc |
| publishDateSort |
2022 |
| contenttype_str_mv |
zzz |
| container_start_page |
0 |
| author_browse |
Quarta, Alessandro A. |
| container_volume |
126 |
| class |
610 VZ 600 670 VZ 51.00 bkl |
| format_se |
Elektronische Aufsätze |
| author-letter |
Quarta, Alessandro A. |
| doi_str_mv |
10.1016/j.ast.2022.107619 |
| dewey-full |
610 600 670 |
| title_sort |
optimal v ∞ leveraging maneuvers using gray solar sail |
| title_auth |
Optimal V ∞ leveraging maneuvers using gray solar sail |
| abstract |
The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. |
| abstractGer |
The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. |
| abstract_unstemmed |
The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time. |
| collection_details |
GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 |
| title_short |
Optimal V ∞ leveraging maneuvers using gray solar sail |
| url |
https://doi.org/10.1016/j.ast.2022.107619 |
| remote_bool |
true |
| author2 |
Bianchi, Christian Niccolai, Lorenzo Mengali, Giovanni |
| author2Str |
Bianchi, Christian Niccolai, Lorenzo Mengali, Giovanni |
| ppnlink |
ELV013466232 |
| mediatype_str_mv |
z |
| isOA_txt |
false |
| hochschulschrift_bool |
false |
| author2_role |
oth oth oth |
| doi_str |
10.1016/j.ast.2022.107619 |
| up_date |
2024-07-06T17:59:59.667Z |
| _version_ |
1803853548401721344 |
| fullrecord_marcxml |
<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">ELV058077944</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230626050255.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">220808s2022 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1016/j.ast.2022.107619</subfield><subfield code="2">doi</subfield></datafield><datafield tag="028" ind1="5" ind2="2"><subfield code="a">/cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001889.pica</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)ELV058077944</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(ELSEVIER)S1270-9638(22)00293-0</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">610</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">600</subfield><subfield code="a">670</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="084" ind1=" " ind2=" "><subfield code="a">51.00</subfield><subfield code="2">bkl</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Quarta, Alessandro A.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Optimal V ∞ leveraging maneuvers using gray solar sail</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2022transfer abstract</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">nicht spezifiziert</subfield><subfield code="b">zzz</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">nicht spezifiziert</subfield><subfield code="b">z</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">nicht spezifiziert</subfield><subfield code="b">zu</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time.</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">The aim of this paper is to analyze the performance of a solar sail-based spacecraft in a heliocentric V ∞ leveraging maneuver. Assuming a circular restricted three-body framework, and using an optical force model for the description of the propulsive acceleration vector, this work quantifies the solar sail performance with an optimal approach, that is, by looking for the sail steering law that maximizes the hyperbolic excess velocity of the spacecraft relative to the [Earth+Moon] system. Such an optimized parameter is calculated in a number of mission scenarios to obtain a parametric analysis of the problem. The numerical simulations show that a solar sail with performance characteristics that comply with the state-of-the-art technology, is able to significantly enhance the launch hyperbolic excess velocity at the expense of a moderate increase in mission flight time.</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Gravity assist</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Leveraging maneuvers</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Solar sail</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="650" ind1=" " ind2="7"><subfield code="a">Trajectory optimization</subfield><subfield code="2">Elsevier</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Bianchi, Christian</subfield><subfield code="4">oth</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Niccolai, Lorenzo</subfield><subfield code="4">oth</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Mengali, Giovanni</subfield><subfield code="4">oth</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="n">Elsevier Science</subfield><subfield code="a">Baysal, Birol ELSEVIER</subfield><subfield code="t">Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience</subfield><subfield code="d">2015</subfield><subfield code="g">Amsterdam [u.a.]</subfield><subfield code="w">(DE-627)ELV013466232</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:126</subfield><subfield code="g">year:2022</subfield><subfield code="g">pages:0</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://doi.org/10.1016/j.ast.2022.107619</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_U</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ELV</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_U</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_40</subfield></datafield><datafield tag="936" ind1="b" ind2="k"><subfield code="a">51.00</subfield><subfield code="j">Werkstoffkunde: Allgemeines</subfield><subfield code="q">VZ</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">126</subfield><subfield code="j">2022</subfield><subfield code="h">0</subfield></datafield></record></collection>
|
| score |
7.397217 |