Optimization of Thermal Protection Systems Utilizing Sandwich Structures with Low Coefficient of Thermal Expansion Lattice Hot Faces

• Published in: Journal of the American Ceramic Society Vol. 94; no. s1; pp. s55 - s61
• Main Authors: Steeves, Craig A., Evans, Anthony G.
• Format: Journal Article
• Language: English
• Published: Malden, USA Blackwell Publishing Inc 01.06.2011; Wiley Subscription Services, Inc
• Subjects: Aircraft; Atmospherics; Ceramics; Crystal lattices; Design optimization; Heating; Hypersonic flight; Hypersonic vehicles; Lattices; Mechanical properties; Optimization; Temperature; Thermal expansion; Thermal protection; Thermal stresses
• ISSN: 0002-7820; 1551-2916
• DOI: 10.1111/j.1551-2916.2011.04447.x

Atmospheric cruise hypersonic vehicles are subject to high viscous heating over large surface areas. Acreage thermal protection systems (TPSs) must be stiff, strong, and light while withstanding large thermal gradients and protecting the cool interior of the vehicle. It is a challenge to design thermal protection to minimize the thermal stresses caused by thermal expansion mismatch. This paper uses a recent concept for low‐thermal‐expansion periodic lattices to propose a sandwich configuration for acreage TPSs. A key aspect of these concepts is that they can be attached to coll structures without inducing thermal stresses during heating. Sandwich TPSs are analyzed and optimized for minimum mass for required performance characteristics, and compared with an optimized baseline system. For performance requirements relevant to atmospheric hypersonic flight, the sandwich TPSs using low‐thermal‐expansion periodic lattices are superior to the baseline system for a large range of operating conditions.