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提出一种在较强的工程约束条件下,开展机翼优化设计的高效率多目标方法。综合升力线理论和RANS的流场计算方法以及数学近似的响应面方法,研究在多种工程约束条件下,巡航设计点中升阻比和翼根弯矩的多目标优化问题。采用分步嵌套优化的方法,首先,固定平面形状,优化展向的扭转角分布;然后优化固定形式下的平面形状参数,对于每一个平面外形,展向扭转角分布的优化为平面形状优化的内迭代;最后通过响应面的结果得到双目标的近似Pareto锋面。该方法对完成特定约束条件下的气动设计具有参考价值。
A highly efficient multi-objective method for wing optimization design is proposed under strong engineering constraints. Based on the theory of lift line, flow field calculation of RANS and the response surface method of mathematical approximation, the multi-objective optimization problem of the ratio of drag to drag and the bending moment of cruise root under cruise design is studied under various engineering constraints. Firstly, the plane shape is fixed to optimize the distribution of torsional angle. Then the plane shape parameters in fixed form are optimized. For each plane shape, the optimization of the twist angle distribution is optimized for the planar shape Finally, we obtain the approximate Pareto front of the bi-objective through the result of the response surface. The method is of reference value for the aerodynamic design under certain constraints.