摘要
基于分布式混合电推进飞行器先进气动布局设计技术研究背景,针对分布式动力翼推进/气动耦合问题,提出了一种面向工程约束的方形涵道风扇单元松耦合设计思路和方法。通过耦合涵道壁面影响的转子叶片设计优化和基于给定转子叶片动量源模型的涵道壁面设计优化这2个模块的耦合迭代,有效降低了设计问题复杂程度,实现兼顾方形涵道风扇单元这种多参数复杂对象的悬停特性和前飞特性的多目标设计优化。最终通过风洞测力和测压试验验证了松耦合设计思路和方法的有效性和可行性。
Based on the research background of advanced aerodynamic design technology of distributed hybrid electric propulsion aircraft,a loose coupling design method of rectangle ducted fan unit under engineering constraints is proposed for the propulsive/aerodynamic coupling problem of distributed propulsion wing.Through the coupling iteration of the rotor blade design optimization module influenced by the duct wall and the duct wall design optimization module based on a given rotor blade momentum source model,the complexity of the design problem is effectively reduced,and the multi-objective design optimization considering both hovering and forward flight characteristics of the rectangle ducted fan unit is achieved for this complex,multi-parameter object.Finally,the effectiveness and feasibility of the present loose coupling design method are verified through wind tunnel tests including force and pressure measurements.
作者
王科雷
周洲
李明浩
WANG Kelei;ZHOU Zhou;LI Minghao(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Aircraft Configuration Design,Xi’an 710072,China)
出处
《航空学报》
北大核心
2025年第9期212-229,共18页
Acta Aeronautica et Astronautica Sinica
基金
装备预研项目(50911040803)
航空科学基金(2024Z006053001)。
关键词
分布式混合电推进飞行器
分布式动力翼
方形涵道风扇单元
推进/气动耦合
松耦合设计
风洞试验
distributed hybrid electric propulsion aircraft
distributed propulsion wing
rectangle ducted fan unit
propulsive/aerodynamic coupling
loose coupling design
wind tunnel test
