分布式电推进短距起降飞机的总体参数优化  

Optimization for overall parameters of STOL aircraft with distributed electric propulsion

作　　者：吕明浩 余雄庆[1] LYU Minghao;YU Xiongqing(College of Aeronautical Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空学院,南京210016

出　　处：《航空工程进展》2025年第1期18-25,共8页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金(12032011);湖南创新型省份建设专项经费资助(2022GK1070)。

摘　　要：基于分布式电动推进的短距起降飞机是一种新概念飞机,需要研究其总体参数的设计方法。以常规的涡桨飞机加装分布式电动螺旋桨的概念方案为示例,将这类飞机总体参数的设计问题提炼为一个优化设计问题;应用基于代理模型的优化方法,制定总体参数优化设计的流程。结果表明:该示例飞机总体参数优化后,能以最小的质量代价达到苛刻的短距起降要求(起飞滑跑距离小于100 m,着陆滑跑距离小于70 m);分布式螺旋桨安装在机翼下方且有一定的倾斜角,螺旋桨转速和直径适中;机翼面积有所增加,涡桨发动机的功率需求明显减小。The short takeoff and landing(STOL)aircraft using distributed electric propulsion is a novel concept,for which the design method of its overall parameters needs to be explored.Taking the conventional turboprop air⁃craft retrofitted with distributed electric propellers as an illustrative aircraft,the design problem of the aircraft over⁃all parameters is formulated as an optimization problem,and then the design optimization process for the overall air⁃craft parameters is presented using the optimization method with surrogate model.The results show that,after opti⁃mization for the overall parameters of the illustrative aircraft concept,the requirements for the ground roll distance during takeoff and landing can be met at the minimum weight penalty.The ground roll distance during takeoff is less than 100 m,the ground roll distance during landing is less than 70 m.The optimal results also indicate that the dis⁃tributed propellers are installed beneath the wing at a certain angle of inclination with moderate rotation speed and diameter,the wing area is increased slightly and required power for the turboprop engine is reduced significantly.

关 键 词：分布式推进 短距起降 飞机概念设计 多学科分析优化 

分 类 号：V272[航空宇航科学与技术—飞行器设计]