基于边条优化外形的全机纵向响应与增升效果研究

用遗传基因算法优化设计了翼-身-尾全机模型机翼边条.通过求解全机纵向运动状态方程,分析了全机模型带与不带机翼边条时纵向动态响应问题.涉及的气动力、力距和纵向稳定导数等则由三维低阶板块法计算获得.通过优化设计,新的带有机翼边条的模型飞机,其升力线斜率可明显提高.当Ma=0.4-0.9时,斜率约提高13%-17%;当Ma=1.5时,约提高12%.数值计算结果表明:在装有机翼边条时,由于短周期频率和阻尼比的提高,飞机对在交战飞行时特别的偏转控制输入响应敏捷.最后,给出了部分基于板块法的气动力结果与Cy-20飞机飞行试验数据的比较.

AIRCRAFT LIFT AND LONGITUDINAL RESPONSE ENHANCEMENT BY OPTIMIZATION OF LEADING EDGE EXTENSION CONFIGURATION

An optimal design configuration of leading edge extensions (LEXs) is presented based on the standard genetic algorithms (Gas). Aircraft longitudinal dynamic response of the system with and without LEX is analyzed by solving the state equation of aircraft longitudinal motion. Aerodynamic force, moments, and longitudinal stability derivatives are estimated by three-dimensional low-order panel method. A novel aircraft model with LEX is optimized and its lift curve slope is increased by 13%-17% for Ma=0. 4-0. 9 and 12% for Ma=1.5. Numerical results show that because the frequency and damping ratio in a short period are improved, the aircraft rapidly responds to a specified deflection control input in the battle area when LEX is installed. Finally, compared the results from the panel method with those from the Cy-20 aircraft flight test data,aerodynamic characteristics are verified.