The design study of a lightweight, effective, reuseable seal for use along the elevon cove of shuttle-type reentry and hypersonic cruise vehicles is presented. The study deals primarily with membrane seals, both metallic and non-metallic. This type of seal spans the cove gap between the wing and elevon, and does not depend on spring tension to maintain contact along a flexing wing span. Technical requirements and criteria were generally derived from the space shuttle and utilized for seal design.
Design and fabrication of elevon cove thermal protection systems for aerospace vehicles
1979-05-01
Report
No indication
English
Shuttle elevon cove aerodynamic heating by internal flow
AIAA | 1977
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