Development of metallic thermal protection systems for the reusable launch vehicle

Journal Article · Wed Jan 01 04:00:00 EST 1997 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.51930· OSTI ID:627621

Blosser, M L ^[1]

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1. NASA-Langley Research Center Mail Stop 396 Hampton, Virginia23681-0001 (United States)

A reusable Thermal Protection System (TPS) that is not only lightweight, but durable, operable and cost effective is one of the technologies required by the Reusable Launch Vehicle (RLV) to achieve the goal of drastically reducing the cost of delivering payload to orbit. Metallic TPS is one of the systems being developed to meet this challenge. Current efforts involve improving the superalloy honeycomb TPS concept, which consists of a foil-gage metallic box encapsulating a low density fibrous insulation, and evaluating it for RLV requirements. The superalloy honeycomb TPS concept is mechanically attached to the vehicle structure. Improvements include more efficient internal insulation, a simpler, lighter weight configuration, and a quick-release fastener system for easier installation and removal. Evaluation includes thermal and structural analysis, fabrication and testing of both coupons and TPS panels under conditions simulating RLV environments. Coupons of metallic honeycomb sandwich, representative of the outer TPS surface, were subjected to low speed impact, hypervelocity impact, and rain erosion testing as well as subsequent arcjet exposure. Arrays of TPS panels have been subjected to radiant heating in a thermal/vacuum facility, aerodynamic heating in an arcjet facility and acoustic loading. {copyright} {ital 1997 American Institute of Physics.}

• Sponsoring Organization: USDOE
• OSTI ID: 627621
• Report Number(s): CONF-970115--
• Journal Information: AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 387; ISSN APCPCS; ISSN 0094-243X
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
ACOUSTIC TESTING
AERODYNAMIC HEATING
DESIGN
FINITE DIFFERENCE METHOD
HEAT RESISTING ALLOYS
SPACE VEHICLES
TEMPERATURE RANGE 1000-4000 K