无舵面飞机变弯度机翼承载/变形一体化设计

Integrated Design of Variable Camber Wing Structure and Mechanism for Aircraft without Rudder

为通过机翼弯度变化实现对无舵面飞机的控制、改善其气动性能,需要协调结构变形、力学承载和轻质设计三者之间的关系。针对传统机械驱动机构造价高、重量大和智能材料驱动机构承载能力弱的缺陷,通过承载/变形一体化设计方法,充分考虑机翼气动载荷的特点,协调配置机械驱动机构与智能材料驱动机构,结合拓扑优化设计,提出一种无舵面飞机变弯度机翼承载/变形一体化设计方案。结果表明,无舵面飞机可在不同飞行环境下改变机翼弯度以承受多种载荷条件,对提高飞机的飞行性能、飞行效率和适应飞行环境的能力具有积极意义。

In order to control an aircraft without rudder and improve its aerodynamic performance through variable camber wing,a lightweight structure that is capable of withstanding loads and changing shape should be designed coordinately.The cost and weight of traditional mechanism and the load-carrying ability of smart material must be fully considered.Thus,traditional mechanism and smart material should be configured according to the aerodynamic loads on the wing.Combined with topology optimization,a variable camber wing with load-carrying capability and deformability was realized by integrated design of structure and mechanism.The results show that the aircraft is able to change its shape in different flight environments and withstand various loading conditions.It is concluded that aircraft with variable camber wings by integrated design of structure and mechanism can adapt its aerodynamic shape to obtain better performances,such as flight efficiency and ability to adjust to flight environments.