Ablative thermal management structural material on the hypersonic vehicles
- Rockwell International Corporation, Seal Beach, CA (United States)
A hypersonic vehicle is designed to fly at high Mach number in the earth`s atmosphere that will result in higher aerodynamic heating loads on specific areas of the vehicle. A thermal protection system is required for these areas that may exceed the operating temperature limit of structural materials. This paper delineates the application of ablative material as the passive type of thermal protection system for the nose or wing leading edges. A simplified quasi-steady-state one-dimensional computer model was developed to evaluate the performance and thermal design of a leading edge. The detailed description of the governing mathematical equations and results are presented. This model provides a quantitative information to support the design estimate, performance optimization, and assess preliminary feasibility of using ablation as a design approach.
- OSTI ID:
- 104468
- Report Number(s):
- AIAA-Paper-95-6133; CONF-9504202-; TRN: 9590452
- Resource Relation:
- Conference: 6. American Institute of Aeronautics and Astronautics (AIAA) aerospace planes and hypersonics technologies conference, Chattanooga, TN (United States), 3-7 Apr 1995; Other Information: PBD: 1995
- Country of Publication:
- United States
- Language:
- English
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