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Application of advanced composites to helicopter airframe structuresThe present work outlines a study whose objective was to assess the possible use of advanced composite materials to helicopter fuselage structure. The study used the CH-53D as a baseline design for comparison of composite with current conventional construction. Boron/epoxy and graphite/epoxy appeared to be the prime candidate materials for the major portion of the primary structure, while Kevlar-49/epoxy was the prime candidate material for secondary structure. A single-laminate shear-carrying skin combined with stringers and frames in an all-molded construction was considered the most promising concept for the airframe shell construction; foam-stabilized graphite/epoxy stringer was considered the prime concept for stringer construction. Shell construction and assembly concepts are discussed, and comparison of weight and material between current CH-53D airframe and the composite airframe shows that the latter may represent an 18% weight saving. Based on a fleet requirement of 600 vehicles, the operating cost for a fleet of helicopters constructed with the composite material airframe flying 500 hours a year per aircraft over a ten-year service life was calculated, indicating a $337,000 saving per helicopter.
Document ID
19740053860
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rich, M. J.
Ridgley, G. F.
Lowry, D. W.
(United Aircraft Corp. Sikorsky Aircraft Div., Stratford, Conn., United States)
Date Acquired
August 7, 2013
Publication Date
May 1, 1974
Subject Category
Aircraft
Report/Patent Number
AHS PREPRINT 880
Meeting Information
Meeting: Annual National V/STOL Forum
Location: Washington, DC
Start Date: May 7, 1974
End Date: May 9, 1974
Sponsors: American Helicopter Society
Accession Number
74A36610
Funding Number(s)
CONTRACT_GRANT: NAS1-11688
Distribution Limits
Public
Copyright
Other

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