Ascent Heating Thermal Analysis on the Spacecraft Adaptor (SA) Fairings and the Interface with the Crew Launch Vehicle (CLV)
Ascent Heating Thermal Analysis on the Spacecraft Adaptor (SA) Fairings and the Interface with the Crew Launch Vehicle (CLV)
- Neue Suche nach: Wang, Xiao-Yen
- Neue Suche nach: Yuko, James
- Neue Suche nach: Motil, Brian
- Neue Suche nach: Wang, Xiao-Yen
- Neue Suche nach: Yuko, James
- Neue Suche nach: Motil, Brian
When the crew exploration vehicle (CEV) is launched, the spacecraft adaptor (SA) fairings that cover the CEV service module (SM) are exposed to aero heating. Thermal analysis is performed to compute the fairing temperatures and to investigate whether the temperatures are within the material limits for nominal ascent aero heating case. Heating rates from Thermal Environment (TE) 3 aero heating analysis computed by engineers at Marshall Space Flight Center (MSFC) are used in the thermal analysis. Both MSC Patran 2007r1b/Pthermal and C&R Thermal Desktop 5.1/Sinda models are built to validate each other. The numerical results are also compared with those reported by Lockheed Martin (LM) and show a reasonably good agreement.
Dokumentinformationen
Ascent Heating Thermal Analysis on the Spacecraft Adaptor (SA) Fairings and the Interface with the Crew Launch Vehicle (CLV)
2008 Thermal and Fluids Analysis Workshop ; 2008 ; San Jose, CA, United States
2009-01-01
Report
Keine Angabe
Englisch