Ceramic Nose Cap and Leading Edges for High Performance Weapon Systems.
Interim technical rept. 15 Jun 70-15 Dec 71,
MARTIN MARIETTA AEROSPACE DENVER CO
Pagination or Media Count:
Activities pursued in the Design, Analysis and Subscale Test Phase of the program entailed the development of the technology necessary to apply Diboride VIII 56 ZrB2, 14 SiC, 30 C, by volume nose tip and leading edge components to the first 46 in. of the Air Force FDL-5A Lifting Body configuration. Design criteria for diboride ceramic components and metal attachment structures were defined and an aerodynamic analysis was performed to provide heating rate and flight pressure data for the FDL-5A. Property data for Diboride VIII composites were obtained through a literature survey and stress concentration effects and high temperature stress-strain behavior were determined experimentally for two Diboride VIII materials. Plasma arc tests were conducted to ascertain the thermal stability, heat transfer characteristics, and thermal stress resistance of diboride ceramics. Diboride design allowables were developed, based on Weibulls theory of brittle fracture. Full-scale diboride nose, skirt, and leading edge components were designed to replace existing water-cooled copper units on the Hypersonic Aerospace Test Structure HATS.
- Ceramics, Refractories and Glass
- Unmanned Spacecraft