Airworthiness compliance validating technical for civil aircraft low speed flutter model wind tunnel test
Liang Ji, Yang Fei,Yang Zhichun
Author information+
Stress Department, Shanghai Aircraft Design And Research Institute of COMAC, Shanghai, 200232, China
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History+
Received
Revised
Published
2012-05-07
2012-07-13
2013-06-25
Issue Date
2013-06-25
Abstract
Modern cilvil aircraft should be designed strictly according to the airworthiness requirements. Domestically, the aeroelastic design of the modern civil aircraft is mainly based on item CCAR25.629 “Aeroelastic stability requirement” and Advisory Circular AC25.629-1A “Aeroelastic Stability Substantiation of Transport Category Airplane”. Low speed flutter model wind tunnel test, which is a necessary technical means for aeroelastic design, is conducted to identify the subsonic flutter characteristics, the sensitive parameters as well as their impacts, and to validate the theoretical analysis results. Meanwhile, the low speed flutter model wind tunnel test is also a necessary means for civil aircraft design to show its airwothiness compliance. In this paper, airworthiness compliance technique of low speed flutter model wind tunnel test for civil aircraft was discussed based on on the work experiences of a certain aircraft type, and a effective program of airworthiness compliance designing and proving for low speed flutter model wind tunnel test was put forward.
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