摘要
翼面结冰是运输类飞机适航标准气动弹性稳定性要求条款(CCAR25.629)规定的必须考虑的失效、故障与不利条件之一,必须通过风洞试验和理论分析相结合的方法来表明飞机对该适航条款的符合性。针对某型民用飞机,进行了模拟翼面不同结冰状态的颤振模型风洞试验,采用希利普法外推得到颤振速度;同时对不同结冰状态进行了理论分析。试验与分析结果表明,该型飞机翼面结冰状态下颤振形式为机翼弯扭耦合;翼面结冰对该型飞机颤振速度无不利影响;该型飞机翼面结冰状态满足颤振包线要求。
The aeroelastic stability requirements of airworthiness standard for transport category airplanes （ CCAR25. 629） prescribe that icing on wing surfaces is one of failures, malfunctions, and adverse conditions which must be considered. The compliance with the airworthiness standard must be shown with wind tunnel test and theoretical analysis. For a civil airplane, wind tunnel test was carried out to simulate different ice accumulation expected on wing surfaces. Schlipp＇s Method was used to extrapolate the flutter speed. And study was done to analyze different icing conditions. The results of test and analysis showed that the flutter form under icing condition is eoupled with wing＇s bending and torsion; ice accumulation on wing surfaces has no adverse influence on aeroplane＇s flutter speed; and this type of aeroplane can satisty the requests of a flutter envelope.
出处
《振动与冲击》
EI
CSCD
北大核心
2011年第1期171-174,共4页
Journal of Vibration and Shock
关键词
翼面结冰
颤振特性
风洞试验
icing on wing surface
flutter
wind tunnel test
