基于A320飞机横航向控制律架构的LQ设计

前缘缝翼、襟翼活动面及其支承结构的疲劳试验是民用飞机取证前要开展的一项重要工作。在试验中采用主动驱动和随动加载方法加载，不仅能缩小试验规模，同时可提高试验精度。国内某型机采用此技术成功进行了前缘缝翼、襟翼及其悬挂结构的疲劳试验。从试验件及其支承设计、系统构成和载荷与运行三方面，介绍了一种适用于大中型固定翼飞机前缘缝翼和襟翼的疲劳试验技术。

Linear Quadratic Design Based on A320 Lateral and Directional Control Law Architecture

The fatigue tests on slat, flap and their supporting structures are very important work to be launched for a new airplane before technology certification (TC) being granted. The loading which adopts active driving and servo loading not only reduces the test scale but also enhances the test accuracy. This technology has been applied to make the fatigue test on some civil aircraft successfully. This paper presents the new fatigue test technology in three aspects: test article with its suspension, test system, load and implementation respectively.