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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 optimization formulation is described 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 dynamic optimization for vibration reduction, rotor structural optimization for minimum weight, and integrated aerodynamic load/dynamics optimization for minimum vibration and weight.
Document ID
19900001573
Document Type
Conference Paper
Authors
Adelman, Howard M.
(NASA Langley Research Center Hampton, VA, United States)
Mantay, Wayne R.
(Army Aviation Systems Command Hampton, VA., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1989
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:101642
NASA-TM-101642
AD-A233514
AVSCOM-TM-89-B-008
Meeting Information
Meeting: AIAA/AHS/ASEE 1989 Aircraft Design and Operations Meeting
Location: Seattle, WA
Country: United States
Start Date: July 31, 1989
End Date: August 2, 1989
Accession Number
90N10889
Funding Number(s)
PROJECT: RTOP 505-63-51-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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