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Impact of active controls technology on structural integrityThis paper summarizes the findings of The Technical Cooperation Program to assess the impact of active controls technology on the structural integrity of aeronautical vehicles and to evaluate the present state-of-the-art for predicting the loads caused by a flight-control system modification and the resulting change in the fatigue life of the flight vehicle. The potential for active controls to adversely affect structural integrity is described, and load predictions obtained using two state-of-the-art analytical methods are given.
Document ID
19910047396
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Noll, Thomas
(NASA Langley Research Center Hampton, VA, United States)
Austin, Edward
(U.S. Army, Aviation Research and Technology Activity, Fort Eustis VA, United States)
Donley, Shawn
(U.S. Navy, Naval Air Development Center Warminster, PA, United States)
Graham, George
(DND Ottawa, Canada)
Harris, Terry
(USAF, Wright Research and Development Center Wright-Patterson AFB, OH, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 91-0988
Meeting Information
Meeting: AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
Location: Baltimore, MD
Country: United States
Start Date: April 8, 1991
End Date: April 10, 1991
Accession Number
91A32019
Distribution Limits
Public
Copyright
Other

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