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Systems integration and demonstration of advanced reusable structure for ALSThe objective was to investigate the potential of advanced material to achieve life cycle cost (LCC) benefits for reusable structure on the advanced launch system. Three structural elements were investigated - all components of an Advanced Launch System reusable propulsion/avionics module. Leading aeroshell configurations included sandwich structure using titanium, graphite/polyimide (Gr/PI), or high-temperature aluminum (HTA) face sheets. Thrust structure truss concepts used titanium, graphite/epoxy, or silicon carbide/aluminum struts. Leading aft bulkhead concepts employed graphite epoxy and aluminum. The technical effort focused on the aeroshell because the greatest benefits were expected there. Thermal analyses show the structural temperature profiles during operation. Finite element analyses show stresses during splash-down. Weight statements and manufacturing cost estimates were prepared for calculation of LCC for each design. The Gr/PI aeroshell showed the lowest potential LCC, but the HTA aeroshell was judged to be lower risk. A technology development plan was prepared to validate the applicable structural technology.
Document ID
19910017865
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Gibbins, Martin N. (Boeing Co. Seattle, WA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
NAS 1.26:187509
NASA-CR-187509
Accession Number
91N27179
Funding Number(s)
PROJECT: RTOP 505-63-01-22
CONTRACT_GRANT: NAS1-18560
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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