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基于能量方法推导了弹性飞机静气弹配平方程,提出了用定常涡格法结合Trefftz平面理论与阻力计算经验公式来求解弹性飞机定直平飞配平状态诱导阻力与配平阻力的分析思路,建立了通过机翼几何扭转角优化配置减小全机诱导阻力的分析方法.以某双尾撑无人机为例进行研究,分析发现尾撑纵向弯曲刚度对该布局飞机的全机诱导阻力、升降舵配平舵偏型阻及全机阻力等参数有重要影响.优化分析结果表明:通过机翼扭转角的合理优化,可使全机展向升力分布形式更接近于椭圆分布,进而有效减小全机诱导阻力,且对其他阻力分量也有一定的减缓效果.
Based on the energy method, the static equation of static bomb for elastic aircraft is deduced, and the analytical method of steady induced equilibrium and induced resistance of elastic aircraft is put forward by using the steady vortex grid theory combined with Trefftz plane theory and resistance calculation empirical formula. In order to reduce the total induced resistance of the whole aircraft, an analysis method of optimizing the configuration of wing geometry torsional angle to reduce the total induced resistance of the aircraft is presented. Taking a two-tail UAV as an example, the longitudinal bending stiffness of the tail- The results of optimization analysis show that reasonable optimization of wing torsion angle can make the form of lift distribution close to the elliptical distribution in the whole aircraft and thus reduce the size of the whole machine effectively Induce resistance, and have some mitigation effect on other resistance components.