DEVELOPMENT OF AN AUTOMATED ULTRASONIC INSPECTION SYSTEM FOR COMPOSITE STRUCTURE ON IN-SERVICE AIRCRAFT

Authors
  1. Sturrock, W.R.
  2. Ramsbottom, R.W.
  3. Miller, W.J.
Corporate Authors
Defence Research Establishment Pacific, Victoria BC (CAN);Galatea Research, Brentwood Bay BC (CAN);Director Aerospace Support Engineering, Ottawa ONT (CAN)
Abstract
Composite honeycomb (carbon/epoxy facesheets bonded to aluminum honeycomb) control surfaces for the CF-18 are inspected at the time of manufacture using (among other methods) ultrasonic through-transmission, but there is no automated ultrasonic inspection system to verify structural integrity of the honeycomb on in-service aircraft. Manual methods of ultrasonic contact scanning or even local through-transmission can be performed over small areas, but it is impossible to reliably inspect a complete control surface, such as a trailing edge flap on the wing or a horizontal stabilator, with hand-held transducers. A description is given of the development and characteristics of an automated scanner and ultrasonic system to perform through-transmission inspections of honeycomb structure on the CF-18 without removal of the part from the aircraft. TRUNCATED
Report Number
AGARD-CP-462-PAP-13 — @Paper presented at the 69th Meeting of the Structures and Materials Panel, Brussels, Belgium, 1-6 October 1989; CONTAINED IN 90-04601
Date of publication
15 May 1990
Number of Pages
13
DSTKIM No
90-04590
CANDIS No
66822
Format(s):
Originator's fiche received by DSIS

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