Saft Solutions For Full Geo Electric Propulsion
Today, the full electric propulsion is becoming more commonly used on board geostationary satellites for the launch up to the Electrical Orbit Raising (EOR) and all on-orbit manoeuvres. This electrical propulsion induces additional cycles for the battery that may result in higher ageing. The Electri...
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
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EDP Sciences
2017-01-01
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| Series: | E3S Web of Conferences |
| Subjects: | |
| Online Access: | https://doi.org/10.1051/e3sconf/20171617005 |
| _version_ | 1818846569398534144 |
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| author | Prevot D. Borthomieu Y. Malet F. Rebuffel C. Carre A. Cenac-Morthe C. |
| author_facet | Prevot D. Borthomieu Y. Malet F. Rebuffel C. Carre A. Cenac-Morthe C. |
| author_sort | Prevot D. |
| collection | DOAJ |
| description | Today, the full electric propulsion is becoming more commonly used on board geostationary satellites for the launch up to the Electrical Orbit Raising (EOR) and all on-orbit manoeuvres.
This electrical propulsion induces additional cycles for the battery that may result in higher ageing.
The Electrical Orbit Raising (EOR) is currently simulated by two additional GEO seasons up to 80%DoD while the Plasmic Propulsion System (PPS) cycles are carried out, at least 162 cycles up to 24%DoD or 198 cycles up to 20%DoD per solstice season and at least 52 cycles up to 15%DoD or 64 cycles up to 10%DoD per eclipse season for 15 years.
The need for an appropriate demonstration by life-test was anticipated and addressed in collaboration with the primes and the agencies, in the frame of ARTES 3–4 contract with ESA for the VES180SA cell & CNES contract for the VES16 cell.
The article will present the whole cycling results available, and will provide afterwards the correlation status of Saft Li-ion Model (SLIM) with the experimental data acquired. |
| first_indexed | 2024-12-19T05:47:38Z |
| format | Article |
| id | doaj.art-bdd0247d179142d7ae0671d245edb37c |
| institution | Directory Open Access Journal |
| issn | 2267-1242 |
| language | English |
| last_indexed | 2024-12-19T05:47:38Z |
| publishDate | 2017-01-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | E3S Web of Conferences |
| spelling | doaj.art-bdd0247d179142d7ae0671d245edb37c2022-12-21T20:33:46ZengEDP SciencesE3S Web of Conferences2267-12422017-01-01161700510.1051/e3sconf/20171617005e3sconf_espc2017_17005Saft Solutions For Full Geo Electric PropulsionPrevot D.0Borthomieu Y.1Malet F.2Rebuffel C.3Carre A.4Cenac-Morthe C.5Saft Space and Defence DivisionSaft Space and Defence DivisionAIRBUS D&SThales Alenia SpaceEuropean Space Agency – European Space Research and Technology Centre (ESTEC)CNESToday, the full electric propulsion is becoming more commonly used on board geostationary satellites for the launch up to the Electrical Orbit Raising (EOR) and all on-orbit manoeuvres. This electrical propulsion induces additional cycles for the battery that may result in higher ageing. The Electrical Orbit Raising (EOR) is currently simulated by two additional GEO seasons up to 80%DoD while the Plasmic Propulsion System (PPS) cycles are carried out, at least 162 cycles up to 24%DoD or 198 cycles up to 20%DoD per solstice season and at least 52 cycles up to 15%DoD or 64 cycles up to 10%DoD per eclipse season for 15 years. The need for an appropriate demonstration by life-test was anticipated and addressed in collaboration with the primes and the agencies, in the frame of ARTES 3–4 contract with ESA for the VES180SA cell & CNES contract for the VES16 cell. The article will present the whole cycling results available, and will provide afterwards the correlation status of Saft Li-ion Model (SLIM) with the experimental data acquired.https://doi.org/10.1051/e3sconf/20171617005DOD: Depth of DischargeOCV: Open Circuit VoltageEOCV: End Of Charge VoltageEODV: End Of Discharge VoltageEOR: Electrical Orbit RaisingGEO: Geosynchronous OrbitIR: Internal ResistancePPS: Plasmic Propulsion SystemSG: Strain GaugeSLIM: Saft Li-Ion ModelSoC: State of Charge. |
| spellingShingle | Prevot D. Borthomieu Y. Malet F. Rebuffel C. Carre A. Cenac-Morthe C. Saft Solutions For Full Geo Electric Propulsion E3S Web of Conferences DOD: Depth of Discharge OCV: Open Circuit Voltage EOCV: End Of Charge Voltage EODV: End Of Discharge Voltage EOR: Electrical Orbit Raising GEO: Geosynchronous Orbit IR: Internal Resistance PPS: Plasmic Propulsion System SG: Strain Gauge SLIM: Saft Li-Ion Model SoC: State of Charge. |
| title | Saft Solutions For Full Geo Electric Propulsion |
| title_full | Saft Solutions For Full Geo Electric Propulsion |
| title_fullStr | Saft Solutions For Full Geo Electric Propulsion |
| title_full_unstemmed | Saft Solutions For Full Geo Electric Propulsion |
| title_short | Saft Solutions For Full Geo Electric Propulsion |
| title_sort | saft solutions for full geo electric propulsion |
| topic | DOD: Depth of Discharge OCV: Open Circuit Voltage EOCV: End Of Charge Voltage EODV: End Of Discharge Voltage EOR: Electrical Orbit Raising GEO: Geosynchronous Orbit IR: Internal Resistance PPS: Plasmic Propulsion System SG: Strain Gauge SLIM: Saft Li-Ion Model SoC: State of Charge. |
| url | https://doi.org/10.1051/e3sconf/20171617005 |
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