Zobrazeno 1 - 10
of 25
pro vyhledávání: '"AVCOAT"'
Publikováno v:
Journal of Thermal Analysis and Calorimetry. 147:5057-5066
Ablative thermal protection systems are used for high temperature applications. Ablative response models use thermo-gravimetric analysis datasets of composite materials in order to extrapolate insulation degradation behavior at very high heating rate
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::93ee9eeae1b57cc1504da913ff8357de
https://doi.org/10.1007/s10973-021-10892-2
https://doi.org/10.1007/s10973-021-10892-2
Autor:
Ali D. Omidy, Marco Panesi, Haoyue Weng, Alexandre Martin, Przemyslaw Rostkowski, Simone Venturi
Publikováno v:
Journal of Thermophysics and Heat Transfer. 33:356-369
The current design of NASA’s Multi-Purpose Crew vehicle uses the latest iteration of AVCOAT, an ablating thermal protection material. However, restrictions placed on the export of experimental data...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a6f1d30c1fb54396436a53a317afc991
https://doi.org/10.2514/1.t5396
https://doi.org/10.2514/1.t5396
Akademický článek
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Publikováno v:
2019 IEEE Aerospace Conference.
This paper describes how the Orion program is incorporating improvements in the heat shield design and manufacturing processes reducing programmatic risk and ensuring crew safety in support of NASA's Exploration Missions. The Orion program successful
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::784cc84ca082f3b9b81e102c7fbbb489
https://doi.org/10.1109/aero.2019.8742249
https://doi.org/10.1109/aero.2019.8742249
Publikováno v:
Procedia Engineering. 103:398-404
Monolithic, porous, thermal protection systems were used heavily on the Apollo command module, and they are currently being used on the next generation of US manned spacecraft, Orion. These systems insulate reentry critical components of a spacecraft
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::ba6d557c96d722ad1d044b87df80c88e
https://doi.org/10.1016/j.proeng.2015.04.038
https://doi.org/10.1016/j.proeng.2015.04.038
Publikováno v:
2018 AIAA SPACE and Astronautics Forum and Exposition.
This paper describes how the Orion program is utilizing the Thermal Protection System (TPS) experience from the Apollo and Space Shuttle programs to reduce program risk and improve affordability to meet NASA's future manned exploration missions. The
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8a54374556f9f9cb0e563f8bf59951c3
https://doi.org/10.2514/6.2018-5134
https://doi.org/10.2514/6.2018-5134
Publikováno v:
2018 AIAA Aerospace Sciences Meeting.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::ffa78b0ed5c3d65244c8ee78876bdffb
https://doi.org/10.2514/6.2018-0495.c1
https://doi.org/10.2514/6.2018-0495.c1
Publikováno v:
2018 AIAA Aerospace Sciences Meeting.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::ea11f73e4dbbb8955c418ef675e39507
https://doi.org/10.2514/6.2018-0495
https://doi.org/10.2514/6.2018-0495
Publikováno v:
2018 AIAA Aerospace Sciences Meeting.
Ablative materials are often used for spacecraft heatshields to protect underlying structures from the extreme environments associated with atmospheric reentry. NASA's Orion EM-1 capsule has been designed to use a molded Avcoat material system. In or
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6f561caa41dc1a7744560475bb8b6745
https://doi.org/10.2514/6.2018-0499
https://doi.org/10.2514/6.2018-0499
Publikováno v:
International Journal of Heat and Mass Transfer. 84:245-252
In-depth thermal responses and surface recession of charring materials are two main performances of the thermal protection system in reentry vehicles subjected to aerodynamic heating. To explore the thermal behavior of the charring ablator, we develo
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::00d77d8e31a48392becd5e21c64b5ce8
https://doi.org/10.1016/j.ijheatmasstransfer.2015.01.004
https://doi.org/10.1016/j.ijheatmasstransfer.2015.01.004