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Optimization of helicopter airframe structures for vibration reduction considerations, formulations and applicationsSeveral key issues involved in the application of formal optimization technique to helicopter airframe structures for vibration reduction are addressed. Considerations which are important in the optimization of real airframe structures are discussed. Considerations necessary to establish relevant set of design variables, constraints and objectives which are appropriate to conceptual, preliminary, detailed design, ground and flight test phases of airframe design are discussed. A methodology is suggested for optimization of airframes in various phases of design. Optimization formulations that are unique to helicopter airframes are described and expressions for vibration related functions are derived. Using a recently developed computer code, the optimization of a Bell AH-1G helicopter airframe is demonstrated.
Document ID
19880064715
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Murthy, T. Sreekanta
(NASA Langley Research Center; PRC Kentron, Inc. Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
September 1, 1988
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 88-4422
Accession Number
88A51942
Distribution Limits
Public
Copyright
Other

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