Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1
This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Iakubivskyi, Iaroslav [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2020transfer abstract |
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| Schlagwörter: |
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| Umfang: |
13 |
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| Übergeordnetes Werk: |
Enthalten in: Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? - Al-Hamid, Hussein ELSEVIER, 2016, journal of the International Academy of Astronautics, Amsterdam [u.a.] |
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| Übergeordnetes Werk: |
volume:177 ; year:2020 ; pages:771-783 ; extent:13 |
| Links: |
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| DOI / URN: |
10.1016/j.actaastro.2019.11.030 |
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| Katalog-ID: |
ELV05239817X |
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| 245 | 1 | 0 | |a Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 |
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| 520 | |a This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. | ||
| 520 | |a This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. | ||
| 650 | 7 | |a Electric solar wind sail |2 Elsevier | |
| 650 | 7 | |a ESTCube-2 |2 Elsevier | |
| 650 | 7 | |a Space debris |2 Elsevier | |
| 650 | 7 | |a Coulomb drag propulsion |2 Elsevier | |
| 650 | 7 | |a Deorbiting |2 Elsevier | |
| 650 | 7 | |a FORESAIL-1 |2 Elsevier | |
| 650 | 7 | |a Plasma brake |2 Elsevier | |
| 650 | 7 | |a Space sustainability |2 Elsevier | |
| 700 | 1 | |a Janhunen, Pekka |4 oth | |
| 700 | 1 | |a Praks, Jaan |4 oth | |
| 700 | 1 | |a Allik, Viljo |4 oth | |
| 700 | 1 | |a Bussov, Kadri |4 oth | |
| 700 | 1 | |a Clayhills, Bruce |4 oth | |
| 700 | 1 | |a Dalbins, Janis |4 oth | |
| 700 | 1 | |a Eenmäe, Tõnis |4 oth | |
| 700 | 1 | |a Ehrpais, Hendrik |4 oth | |
| 700 | 1 | |a Envall, Jouni |4 oth | |
| 700 | 1 | |a Haslam, Sean |4 oth | |
| 700 | 1 | |a Ilbis, Erik |4 oth | |
| 700 | 1 | |a Jovanovic, Nemanja |4 oth | |
| 700 | 1 | |a Kilpua, Emilia |4 oth | |
| 700 | 1 | |a Kivastik, Joosep |4 oth | |
| 700 | 1 | |a Laks, Jürgen |4 oth | |
| 700 | 1 | |a Laufer, Philipp |4 oth | |
| 700 | 1 | |a Merisalu, Maido |4 oth | |
| 700 | 1 | |a Meskanen, Matias |4 oth | |
| 700 | 1 | |a Märk, Robert |4 oth | |
| 700 | 1 | |a Nath, Ankit |4 oth | |
| 700 | 1 | |a Niemelä, Petri |4 oth | |
| 700 | 1 | |a Noorma, Mart |4 oth | |
| 700 | 1 | |a Mughal, Muhammad Rizwan |4 oth | |
| 700 | 1 | |a Nyman, Samuli |4 oth | |
| 700 | 1 | |a Pajusalu, Mihkel |4 oth | |
| 700 | 1 | |a Palmroth, Minna |4 oth | |
| 700 | 1 | |a Paul, Aditya Savio |4 oth | |
| 700 | 1 | |a Peltola, Tatu |4 oth | |
| 700 | 1 | |a Plans, Mathias |4 oth | |
| 700 | 1 | |a Polkko, Jouni |4 oth | |
| 700 | 1 | |a Islam, Quazi Saimoon |4 oth | |
| 700 | 1 | |a Reinart, Anu |4 oth | |
| 700 | 1 | |a Riwanto, Bagus |4 oth | |
| 700 | 1 | |a Sammelselg, Väino |4 oth | |
| 700 | 1 | |a Sate, Janis |4 oth | |
| 700 | 1 | |a Sünter, Indrek |4 oth | |
| 700 | 1 | |a Tajmar, Martin |4 oth | |
| 700 | 1 | |a Tanskanen, Eija |4 oth | |
| 700 | 1 | |a Teras, Hans |4 oth | |
| 700 | 1 | |a Toivanen, Petri |4 oth | |
| 700 | 1 | |a Vainio, Rami |4 oth | |
| 700 | 1 | |a Väänänen, Mika |4 oth | |
| 700 | 1 | |a Slavinskis, Andris |4 oth | |
| 773 | 0 | 8 | |i Enthalten in |n Elsevier Science |a Al-Hamid, Hussein ELSEVIER |t Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? |d 2016 |d journal of the International Academy of Astronautics |g Amsterdam [u.a.] |w (DE-627)ELV014615371 |
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10.1016/j.actaastro.2019.11.030 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001230.pica (DE-627)ELV05239817X (ELSEVIER)S0094-5765(19)31425-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Iakubivskyi, Iaroslav verfasserin aut Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 2020transfer abstract 13 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. Electric solar wind sail Elsevier ESTCube-2 Elsevier Space debris Elsevier Coulomb drag propulsion Elsevier Deorbiting Elsevier FORESAIL-1 Elsevier Plasma brake Elsevier Space sustainability Elsevier Janhunen, Pekka oth Praks, Jaan oth Allik, Viljo oth Bussov, Kadri oth Clayhills, Bruce oth Dalbins, Janis oth Eenmäe, Tõnis oth Ehrpais, Hendrik oth Envall, Jouni oth Haslam, Sean oth Ilbis, Erik oth Jovanovic, Nemanja oth Kilpua, Emilia oth Kivastik, Joosep oth Laks, Jürgen oth Laufer, Philipp oth Merisalu, Maido oth Meskanen, Matias oth Märk, Robert oth Nath, Ankit oth Niemelä, Petri oth Noorma, Mart oth Mughal, Muhammad Rizwan oth Nyman, Samuli oth Pajusalu, Mihkel oth Palmroth, Minna oth Paul, Aditya Savio oth Peltola, Tatu oth Plans, Mathias oth Polkko, Jouni oth Islam, Quazi Saimoon oth Reinart, Anu oth Riwanto, Bagus oth Sammelselg, Väino oth Sate, Janis oth Sünter, Indrek oth Tajmar, Martin oth Tanskanen, Eija oth Teras, Hans oth Toivanen, Petri oth Vainio, Rami oth Väänänen, Mika oth Slavinskis, Andris oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:177 year:2020 pages:771-783 extent:13 https://doi.org/10.1016/j.actaastro.2019.11.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 177 2020 771-783 13 |
| spelling |
10.1016/j.actaastro.2019.11.030 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001230.pica (DE-627)ELV05239817X (ELSEVIER)S0094-5765(19)31425-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Iakubivskyi, Iaroslav verfasserin aut Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 2020transfer abstract 13 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. Electric solar wind sail Elsevier ESTCube-2 Elsevier Space debris Elsevier Coulomb drag propulsion Elsevier Deorbiting Elsevier FORESAIL-1 Elsevier Plasma brake Elsevier Space sustainability Elsevier Janhunen, Pekka oth Praks, Jaan oth Allik, Viljo oth Bussov, Kadri oth Clayhills, Bruce oth Dalbins, Janis oth Eenmäe, Tõnis oth Ehrpais, Hendrik oth Envall, Jouni oth Haslam, Sean oth Ilbis, Erik oth Jovanovic, Nemanja oth Kilpua, Emilia oth Kivastik, Joosep oth Laks, Jürgen oth Laufer, Philipp oth Merisalu, Maido oth Meskanen, Matias oth Märk, Robert oth Nath, Ankit oth Niemelä, Petri oth Noorma, Mart oth Mughal, Muhammad Rizwan oth Nyman, Samuli oth Pajusalu, Mihkel oth Palmroth, Minna oth Paul, Aditya Savio oth Peltola, Tatu oth Plans, Mathias oth Polkko, Jouni oth Islam, Quazi Saimoon oth Reinart, Anu oth Riwanto, Bagus oth Sammelselg, Väino oth Sate, Janis oth Sünter, Indrek oth Tajmar, Martin oth Tanskanen, Eija oth Teras, Hans oth Toivanen, Petri oth Vainio, Rami oth Väänänen, Mika oth Slavinskis, Andris oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:177 year:2020 pages:771-783 extent:13 https://doi.org/10.1016/j.actaastro.2019.11.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 177 2020 771-783 13 |
| allfields_unstemmed |
10.1016/j.actaastro.2019.11.030 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001230.pica (DE-627)ELV05239817X (ELSEVIER)S0094-5765(19)31425-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Iakubivskyi, Iaroslav verfasserin aut Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 2020transfer abstract 13 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. Electric solar wind sail Elsevier ESTCube-2 Elsevier Space debris Elsevier Coulomb drag propulsion Elsevier Deorbiting Elsevier FORESAIL-1 Elsevier Plasma brake Elsevier Space sustainability Elsevier Janhunen, Pekka oth Praks, Jaan oth Allik, Viljo oth Bussov, Kadri oth Clayhills, Bruce oth Dalbins, Janis oth Eenmäe, Tõnis oth Ehrpais, Hendrik oth Envall, Jouni oth Haslam, Sean oth Ilbis, Erik oth Jovanovic, Nemanja oth Kilpua, Emilia oth Kivastik, Joosep oth Laks, Jürgen oth Laufer, Philipp oth Merisalu, Maido oth Meskanen, Matias oth Märk, Robert oth Nath, Ankit oth Niemelä, Petri oth Noorma, Mart oth Mughal, Muhammad Rizwan oth Nyman, Samuli oth Pajusalu, Mihkel oth Palmroth, Minna oth Paul, Aditya Savio oth Peltola, Tatu oth Plans, Mathias oth Polkko, Jouni oth Islam, Quazi Saimoon oth Reinart, Anu oth Riwanto, Bagus oth Sammelselg, Väino oth Sate, Janis oth Sünter, Indrek oth Tajmar, Martin oth Tanskanen, Eija oth Teras, Hans oth Toivanen, Petri oth Vainio, Rami oth Väänänen, Mika oth Slavinskis, Andris oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:177 year:2020 pages:771-783 extent:13 https://doi.org/10.1016/j.actaastro.2019.11.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 177 2020 771-783 13 |
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10.1016/j.actaastro.2019.11.030 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001230.pica (DE-627)ELV05239817X (ELSEVIER)S0094-5765(19)31425-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Iakubivskyi, Iaroslav verfasserin aut Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 2020transfer abstract 13 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. Electric solar wind sail Elsevier ESTCube-2 Elsevier Space debris Elsevier Coulomb drag propulsion Elsevier Deorbiting Elsevier FORESAIL-1 Elsevier Plasma brake Elsevier Space sustainability Elsevier Janhunen, Pekka oth Praks, Jaan oth Allik, Viljo oth Bussov, Kadri oth Clayhills, Bruce oth Dalbins, Janis oth Eenmäe, Tõnis oth Ehrpais, Hendrik oth Envall, Jouni oth Haslam, Sean oth Ilbis, Erik oth Jovanovic, Nemanja oth Kilpua, Emilia oth Kivastik, Joosep oth Laks, Jürgen oth Laufer, Philipp oth Merisalu, Maido oth Meskanen, Matias oth Märk, Robert oth Nath, Ankit oth Niemelä, Petri oth Noorma, Mart oth Mughal, Muhammad Rizwan oth Nyman, Samuli oth Pajusalu, Mihkel oth Palmroth, Minna oth Paul, Aditya Savio oth Peltola, Tatu oth Plans, Mathias oth Polkko, Jouni oth Islam, Quazi Saimoon oth Reinart, Anu oth Riwanto, Bagus oth Sammelselg, Väino oth Sate, Janis oth Sünter, Indrek oth Tajmar, Martin oth Tanskanen, Eija oth Teras, Hans oth Toivanen, Petri oth Vainio, Rami oth Väänänen, Mika oth Slavinskis, Andris oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:177 year:2020 pages:771-783 extent:13 https://doi.org/10.1016/j.actaastro.2019.11.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 177 2020 771-783 13 |
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10.1016/j.actaastro.2019.11.030 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001230.pica (DE-627)ELV05239817X (ELSEVIER)S0094-5765(19)31425-0 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Iakubivskyi, Iaroslav verfasserin aut Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 2020transfer abstract 13 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. Electric solar wind sail Elsevier ESTCube-2 Elsevier Space debris Elsevier Coulomb drag propulsion Elsevier Deorbiting Elsevier FORESAIL-1 Elsevier Plasma brake Elsevier Space sustainability Elsevier Janhunen, Pekka oth Praks, Jaan oth Allik, Viljo oth Bussov, Kadri oth Clayhills, Bruce oth Dalbins, Janis oth Eenmäe, Tõnis oth Ehrpais, Hendrik oth Envall, Jouni oth Haslam, Sean oth Ilbis, Erik oth Jovanovic, Nemanja oth Kilpua, Emilia oth Kivastik, Joosep oth Laks, Jürgen oth Laufer, Philipp oth Merisalu, Maido oth Meskanen, Matias oth Märk, Robert oth Nath, Ankit oth Niemelä, Petri oth Noorma, Mart oth Mughal, Muhammad Rizwan oth Nyman, Samuli oth Pajusalu, Mihkel oth Palmroth, Minna oth Paul, Aditya Savio oth Peltola, Tatu oth Plans, Mathias oth Polkko, Jouni oth Islam, Quazi Saimoon oth Reinart, Anu oth Riwanto, Bagus oth Sammelselg, Väino oth Sate, Janis oth Sünter, Indrek oth Tajmar, Martin oth Tanskanen, Eija oth Teras, Hans oth Toivanen, Petri oth Vainio, Rami oth Väänänen, Mika oth Slavinskis, Andris oth Enthalten in Elsevier Science Al-Hamid, Hussein ELSEVIER Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? 2016 journal of the International Academy of Astronautics Amsterdam [u.a.] (DE-627)ELV014615371 volume:177 year:2020 pages:771-783 extent:13 https://doi.org/10.1016/j.actaastro.2019.11.030 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 GBV_ILN_105 GBV_ILN_2021 51.00 Werkstoffkunde: Allgemeines VZ AR 177 2020 771-783 13 |
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English |
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Enthalten in Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? Amsterdam [u.a.] volume:177 year:2020 pages:771-783 extent:13 |
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Enthalten in Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? Amsterdam [u.a.] volume:177 year:2020 pages:771-783 extent:13 |
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Electric solar wind sail ESTCube-2 Space debris Coulomb drag propulsion Deorbiting FORESAIL-1 Plasma brake Space sustainability |
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Sa1204 Does Intravenous Toradol Lower the Risk for Post- Endoscopic Retrograde Cholangiopancreatography Pancreatitis? |
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Iakubivskyi, Iaroslav @@aut@@ Janhunen, Pekka @@oth@@ Praks, Jaan @@oth@@ Allik, Viljo @@oth@@ Bussov, Kadri @@oth@@ Clayhills, Bruce @@oth@@ Dalbins, Janis @@oth@@ Eenmäe, Tõnis @@oth@@ Ehrpais, Hendrik @@oth@@ Envall, Jouni @@oth@@ Haslam, Sean @@oth@@ Ilbis, Erik @@oth@@ Jovanovic, Nemanja @@oth@@ Kilpua, Emilia @@oth@@ Kivastik, Joosep @@oth@@ Laks, Jürgen @@oth@@ Laufer, Philipp @@oth@@ Merisalu, Maido @@oth@@ Meskanen, Matias @@oth@@ Märk, Robert @@oth@@ Nath, Ankit @@oth@@ Niemelä, Petri @@oth@@ Noorma, Mart @@oth@@ Mughal, Muhammad Rizwan @@oth@@ Nyman, Samuli @@oth@@ Pajusalu, Mihkel @@oth@@ Palmroth, Minna @@oth@@ Paul, Aditya Savio @@oth@@ Peltola, Tatu @@oth@@ Plans, Mathias @@oth@@ Polkko, Jouni @@oth@@ Islam, Quazi Saimoon @@oth@@ Reinart, Anu @@oth@@ Riwanto, Bagus @@oth@@ Sammelselg, Väino @@oth@@ Sate, Janis @@oth@@ Sünter, Indrek @@oth@@ Tajmar, Martin @@oth@@ Tanskanen, Eija @@oth@@ Teras, Hans @@oth@@ Toivanen, Petri @@oth@@ Vainio, Rami @@oth@@ Väänänen, Mika @@oth@@ Slavinskis, Andris @@oth@@ |
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Coulomb drag propulsion experiments of ESTCube-2 and FORESAIL-1 |
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This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. |
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This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. |
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This paper presents two technology experiments – the plasma brake for deorbiting and the electric solar wind sail for interplanetary propulsion – on board the ESTCube-2 and FORESAIL-1 satellites. Since both technologies employ the Coulomb interaction between a charged tether and a plasma flow, they are commonly referred to as Coulomb drag propulsion. The plasma brake operates in the ionosphere, where a negatively charged tether deorbits a satellite. The electric sail operates in the solar wind, where a positively charged tether propels a spacecraft, while an electron emitter removes trapped electrons. Both satellites will be launched in low Earth orbit carrying nearly identical Coulomb drag propulsion experiments, with the main difference being that ESTCube-2 has an electron emitter and it can operate in the positive mode. While solar-wind sailing is not possible in low Earth orbit, ESTCube-2 will space-qualify the components necessary for future electric sail experiments in its authentic environment. The plasma brake can be used on a range of satellite mass classes and orbits. On nanosatellites, the plasma brake is an enabler of deorbiting – a 300-m-long tether fits within half a cubesat unit, and, when charged with - 1 kV, can deorbit a 4.5-kg satellite from between a 700- and 500-km altitude in approximately 9–13 months. This paper provides the design and detailed analysis of low-Earth-orbit experiments, as well as the overall mission design of ESTCube-2 and FORESAIL-1. |
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