现代民用飞机须严格按照适航规章要求进行设计，国内现代民用飞机的气动弹性设计参照的适航条款主要为CCAR25.629条款“气动弹性稳定性要求”和咨询通报AC25.629-1A“Aeroelastic Stability Substantiation of Transport Category Airplane”。低速颤振模型风洞试验是飞机气动弹性设计中的一种有效技术手段，用以摸清飞机的亚音速颤振特性、影响颤振特性的敏感参数及其影响规律，并验证理论分析结果；低速颤振模型风洞试验同时也是民用飞机适航符合性的一种验证方法，用以表明飞机气动弹性设计的适航符合性。本文结合某型号飞机研制经验对民用飞机低速颤振模型风洞试验的适航符合性验证技术进行探讨研究，提出了切实可行的民用飞机低速颤振模型风洞试验适航符合性设计和验证方案。
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.
2013, Vol. 32 
