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为研究鸭式布局飞行器摇滚特性,设计了一种包括鸭翼、脊型前体、边条翼、主翼和垂尾的模型,进行了自由滚转、扰动滚转、静动态测力和烟线流场显示多种技术手段相结合的风洞试验。通过自由滚转和扰动滚转试验得到了该模型翼体摇滚的时间历程,静态测力和动导数测定验证了非极限环运动形式摇滚的发生。结果表明该鸭式布局模型摇滚不仅同侧存在多个摇滚平衡点,而且在临界俯仰角,摇滚过程中可能出现从一摇滚平衡点跳动至同侧另一摇滚平衡点的突变。通过流场显示技术得到该鸭式布局模型复杂流场的基本形态分布,并对滚转角为0°时的全机涡系干扰和摇滚形成机理进行了简要分析。
In order to study the rocking characteristics of a duck-typed layout vehicle, a model of duck-wing, ridge-shaped precursors, wingtips, main wings and vertical tail was designed. Free rolling, turbulent rolling, The flow field shows a combination of wind tunnel tests with various technical means. The time histories of the wing of the model body were obtained by free rolling and disturbing roll tests. The static force measurement and the dynamic derivative test validated the occurrence of rock in the form of non-limit cycle. The results show that there are multiple rock balance points on the same side of the rock model, and there may be sudden jumps from one rock balance point to the other rock balance point at the critical pitch angle and rock. The basic morphological distribution of the complex flow field of the canard layout model is obtained by the flow field display technology. The whole-turbine vortex disturbance and rock formation mechanism are analyzed when the roll angle is 0 °.