COMPOSITE MATERIAL SINGLE-SPAR STRUCTURAL DESIGN FOR TRANSONIC FLUTTER MODEL AND STIFFNESS CALCULATION METHOD THEREFOR

摘要

The present invention provides a composite material single-spar structure for a transonic flutter model consisting of a non-metallic core material and a single closed-cell thin-walled casing laid over the outer layer of the core material, characterized in that the casing has a rectangular chamfered closed cross-sectional shape, and is formed from the composite material laid alternately at ±α degrees and 0 degrees, wherein laying at 0 degrees represents laying the composite material along a direction perpendicular to the cross section. Using the single-spar structure of the present invention can effectively satisfy the requirements for strength and cross-sectionally varying stiffness of a transonic flutter model. The present invention also provides a corresponding calculation method for cross-sectional stiffness of the single-spar structure. Data relating to cross-sectional dimensions for realizing a target stiffness design can be quickly acquired by means of this calculation method.