In order to obtain better aerodynamic efficiency and take-off/landing capacity, it will be an excellent configuration for distributed electric propulsion (DEP) aircraft to install the blown flap in the propulsion wake. For this configuration, the coupling motion between the blown flap and the duct is hard to be achieved by the transmission mechanism of traditional distributed electric propulsion aircraft. This article describes the design and optimization of a transmission mechanism of a high lift device which composed of the distributed electric propulsion system and the blown flap. Firstly, the theoretical design rationale which is mainly based on the analytic hierarchy process and ant colony algorithm is introduced. Then, the kinematic simulation is conducted in details using closed loop vector equation. To further demonstrate the feasibility and reliability of the design approach, the functional test of a full-size transmission mechanism model is carried out. Kinematic simulation and ground test results show that the proposed mechanism can meet the requirements of the coupling motion between the duct and the blown flap, and the corresponding design scheme can be used to solve the design problem of such DEP aircraft transmission mechanism with the blown flap.

为获得更好的气动效率和起降能力，将是分布式电力推进的绝佳配置(DEP) 飞机在推进尾流中安装吹动襟翼。对于这种配置，传统的分布式电力推进飞行器的传动机构难以实现吹动襟翼与导管之间的耦合运动。本文介绍了由分布式电力推进系统和风门襟翼组成的高升力装置传动机构的设计与优化。首先介绍了主要基于层次分析法和蚁群算法的理论设计原理。然后，使用闭环矢量方程详细进行运动学模拟。为了进一步论证该设计方法的可行性和可靠性，进行了全尺寸传动机构模型的功能测试。