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Hypersonic Thermal-Structural Concept Trends
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English
Abstract
Improvement in airframe structural efficiency through the utilization of unique and minimum weight concepts is a primary applied engineering objective for the hypersonic environment. The essential elements for hypersonic structures criteria are temperature environment, low load intensities, room temperature load conditions, structural stability, minimum gage material requirements, material producibility, reusability, nonoptimum factors, and vehicle configuration compatibility. A comparison of thermal structural concepts indicates that the hot load-carrying structure is the leading candidate for a typical M8 hypersonic cruise vehicle wing and fuselage application.
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Authors
Citation
Plank, P., "Hypersonic Thermal-Structural Concept Trends," SAE Technical Paper 660678, 1966, https://doi.org/10.4271/660678.Also In
References
- Matthews C. O. “Final 1965 Report for Rye Canyon Laboratory on Materials and Structures for Hypersonic Vehicles.” Lockheed-California Co. Report LR 19431 January 1966
- Childers M. G. “Hypersonic and Reentry Structures and Materials.” Lockheed-California Co. Report LR 19511 January 1966
- Wilhelm K. A. “Methods for Fabricating Columbium and Cobalt Base Alloys for Reentry Vehicle Structures.” Lockheed-California Co. Report CMRI-1112 January 1966
- Plank P. P. MacMiller C. J. “Analytical Investigation of Candidate Thermal Structural Concepts Applicable to Wing, Fuselage and Inlet Structure of a Manned Hypersonic Vehicle.” AFFDL-TR-66-15 February 1966
- Emero D. H. Spunt L. “Optimization of Multirib and Multiweb Wing Box Structures Under and Moment Loads.” AIAA Sixth Structures and Materials Conference April 1965
- Crawford R. F. Burns A. B. “Strength, Efficiency and Design Data for Beryllium Structures,” ASD Tech. Report 61-692 1962