利用几何遗传方法优化前缘翼根延伸的外形以增强飞行器升力系数和机动性

为了提高所选定飞行器模型的机动性,采用了一种标准遗传算法设计前缘翼根延伸(LEX).同时使用一种由三维低阶板方法结合DATCOM方法半经验公式的改进方法预测复杂外形飞行器(机身 机翼 尾翼)的空气动力载荷和最大升力系数.结果表明,在前缘翼根存在的情况下,升力系数在马赫数为0.4～0.8时提升了20.5%～15.3%,在马赫数为1.2时提升了6.8%,在马赫数为0.2～0.95之间升力系数最大值提升了9.5%～15%.在1～5 km的高度亚音速飞行时,其回转率得到了6.6%～8.0%的提升.

AIRCRAFT LIFT AND MANEUVERABILITY ENHANCEMENT BY GENETIC GEOMETRY OPTIMIZATION OF LEX CONFIGURATION

To enhance the maneuverability of the selected aircraft model, a standard genetic algorithm (GA) is used as an optimization method for the preliminary design of the leading-edge extension (LEX) layout. The aerodynamic loads and the maximum lift coefficient of the complete aircraft configuration (fuselage wing tail) are computed by using the modified three-dimensional low-order panel method in conjunction with the semi-empirical formulas of DATCOM. Results show that the lift coefficient increases approximately 20.5 %-15.3 % for Mach number 0.4-0.8 and 6.8 % for Mach number 1.2, and its maximum value approximately 9.5 %-15.0 % for Mach number 0.2-0.95 when LEX is installed. A 6.6 %-8.0 % gain at altitudes of 1-5 km on the turn rate maneuverability and the corner speed have been achieved in the subsonic regime.