This paper presents the design constraints, flight environments, conceptual design iterations and analytical methods used in the design and flight certification of the Reinforced Carbon-Carbon (RCC) chin panel for the Space Shuttle Orbiter. A discussion of the thermal/structural response of the chin panel to the imposed environments is presented. As with all critical airframe components, it was desirable to conduct a structural test to verify design adequacy. However, with the chin panel, a meaningful test to simulate the critical thermal stresses was not considered feasible.
Thermal structural analysis of the RCC chin panel
1990-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Online Contents | 2006
|DataCite | 1893
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