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Safety aspects of CMC materials and hot structures

Hald, H. and Weihs, H. (2002) Safety aspects of CMC materials and hot structures. Joint ESA/NASA space flight safety conference, Noordwijk, The Netherlands, 11-14 Juni 2002.

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Abstract

There is a growing demand for reusability of future space re-entry vehicles and an associated tendency towards further increase of the maximum operational temperatures of hot structures and thermal protection system elements. This is mainly driven by advanced aerodynamic vehicle shaping, higher weight and mission profiles as is shown typically ba NASA's X-38. As there is no alternative material available other than ceramic matrix composites like C/SiC and C/C for such kinds of hot primary structures the question is obvious where the operational limits of the materials and the related structures are and how safe operation of the hot structural elements can be guaranteed. This paper deals with the special material dependent problems and the general design approach of fibre ceramic components to enhance the system safety already during the initial lay out.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2003,
Title:Safety aspects of CMC materials and hot structures
Authors:
AuthorsInstitution or Email of Authors
Hald, H.UNSPECIFIED
Weihs, H.UNSPECIFIED
Date:2002
Status:Published
Keywords:ceramic matrix composites, CMC, hot primary structures, qualification, tests, re-entry
Event Title:Joint ESA/NASA space flight safety conference, Noordwijk, The Netherlands, 11-14 Juni 2002
Organizer:ESA/NASA
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):UNSPECIFIED
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design
Deposited By: elib DLR-Beauftragter
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 22:32

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