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Investigation on the use of optimization techniques for helicopter airframe vibrations design studiesResults of the investigation of formal nonlinear programming-based numerical optimization techniques of helicopter airframe vibration reduction are summarized. The objective and constraint function and the sensitivity expressions used in the formulation of airframe vibration optimization problems are presented and discussed. Implementation of a new computational procedure based on MSC/NASTRAN and CONMIN in a computer program system called DYNOPT for optimizing airframes subject to strength, frequency, dynamic response, and dynamic stress constraints is described. An optimization methodology is proposed which is thought to provide a new way of applying formal optimization techniques during the various phases of the airframe design process. Numerical results obtained from the application of the DYNOPT optimization code to a helicopter airframe are discussed.
Document ID
19940036051
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Sreekanta Murthy, T.
(Lockheed Engineering & Sciences Co. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: Control and dynamic systems. Vol. 54 - System performance improvement and optimization techniques and their applications in aerospace systems (A94-12701 02-01)
Publisher: Academic Press, Inc.
Subject Category
Aircraft Design, Testing And Performance
Accession Number
94A12706
Funding Number(s)
CONTRACT_GRANT: NAS1-19000
Distribution Limits
Public
Copyright
Other

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