机翼跨音速颤振模型设计中大梁截面有渐变扭转角问题探讨
摘要：大多数飞机跨音速区的颤振边界都会出现很强的压缩性现象，即“凹坑”，其压缩性程度随机型的不同而不同。目前，国内还没有可靠的适用于工程计算的跨音速颤振计算软件，因此，要得到正确的跨音速区颤振边界，需要进行跨音速颤振模型试验。本文对某型飞机机翼跨音速颤振模型的初期设计中由于大梁的几何横截面超出了机翼模型几何外形而使大梁截面有渐变扭转角问题进行探讨。结论表明大梁带有渐变扭转转角机翼跨音速颤振模型面内模态与弯曲模态存在耦合现象，因此机翼跨音速颤振模型设计中大梁应避免带有渐变扭转角。
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The flutter boundary of majority aircraft transonic speed region all have very strong compressibility phenomena, namely “dent”,the compressibility degree is different of different type aircrafts. At present, domestic graduate school don't have transonic speed flutter analysis software which is the same with engineering analysis. So in order to obtain correct transonic speed region flutter boundary, we must carry through transonic speed flutter model test. The paper discusses gradual change torsion angle crossbeam problem of transonic speed flutter model design. The conclusion indicates that the crossbeam's chordwise bending model and spanwise bending model are coupling, so the crossbeam of transonic speed flutter model design can't have gradual change torsion angle.
关键字：跨音速；颤振模型设计；风洞试验
: transonic speed; flutter model design; test in wind tunnel
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