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全机缩比模型跨声速颤振试验是飞行器气弹设计验证工作的重要环节,借助该试验可研究跨声速区空气压缩性效应,并有效获得飞行器的跨声速颤振边界。通过总结、梳理多次部件级跨声速颤振试验研究经验,并基于某型翼身模态高度耦合的静不安定飞机全模试验研究,较全面地阐述了目前全模跨声速颤振模型设计、地面试验及风洞试验技术,可供工程应用借鉴。
The transonic flutter test of the full scale model is an important part of the verification of the aeroelastic design of the aircraft. With this test, the air compressibility effect of the transonic zone can be studied and the transonic flutter boundary of the aircraft can be effectively obtained. Through summarizing and combing the experience of many component-level transonic flutter tests, and based on the full-scale experimental study of some type of wing-body coupled hypersound aircraft, the current full-mode transonic flutter model design , Ground test and wind tunnel test technology, which can be used for engineering application.