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Integrated multidisciplinary design optimization of rotorcraftThe NASA/Army research plan for developing the logic elements for helicopter rotor design optimization by integrating appropriate disciplines and accounting for important interactions among the disciplines is discussed. The paper describes the optimization formulation in terms of the objective function, design variables, and constraints. The analysis aspects are discussed, and an initial effort at defining the interdisciplinary coupling is summarized. Results are presented on the achievements made in the rotor aerodynamic performance optimization for minimum hover horsepower, rotor dynamic optimization for vibration reduction, rotor structural optimization for minimum weight, and integrated aerodynamic load/dynamics optimization for minimum vibration and weight.
Document ID
19890062107
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Adelman, Howard M.
(NASA Langley Research Center Hampton, VA, United States)
Mantay, Wayne R.
(NASA Langley Research Center; U.S. Army, Aerostructures Directorate, Hampton VA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 89-2132
Accession Number
89A49478
Distribution Limits
Public
Copyright
Other

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