静不安定飞机缩比模型跨声速颤振试验技术

Review of Transonic Flutter Test Techniques for Statically Unstable Aircraft Scaled Model

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 wind tunnel test of whole aircraft scaled model plays an important role in engineering certification of AC aeroelastic design, by which the aero compressibility and flutter boundary in transonic region can be investigated. The design experiences of transonic flutter tests for several components are summarized first in this paper, and the test techniques for whole aircraft scaled model are introduced in detail subsequently, which are composed of flutter scaled model design technique, ground tests technique and wind tunnel test technique. This paper is also abstracted based on the engineering project of scaled model design for a statically unstable aircraft, which has massive coupling modes between fuselage and other components. The contents introduced in this paper are supposed to be valuable for engineering application.