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Sonic fatigue testing of an advanced composite aileronThe sonic fatigue test program to verify the design of the composite inboard aileron for the L-1011 airplane is described. The composite aileron is fabricated from graphite/epoxy minisandwich covers which are attached to graphite/epoxy front spar and ribs, and to an aluminum rear spar with fasteners. The program covers the development of random fatigue data by means of coupon testing and modal studies on a representative section of the composite aileron, culminating in the accelerated sonic fatigue proof test. The composite aileron sustained nonlinear panel vibration during the proof test without failure. Viscous damping coefficients as low as 0.4% were measured on the panels. The effects of moisture conditioning and elevated temperature on the random fatigue life of both undamaged and impact damaged coupons were investigated. The combination of impact damage, moisture, and a 180 F temperature could reduce the random fatigue life by 50%.
Document ID
19820043032
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Soovere, J.
(Lockheed-California Co. Burbank, CA, United States)
Date Acquired
August 10, 2013
Publication Date
April 1, 1982
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 81-0634
Accession Number
82A26567
Funding Number(s)
CONTRACT_GRANT: NAS1-15069
Distribution Limits
Public
Copyright
Other

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