【作者】 蔡佳昆； 李健；

【Author】 Cai Jiakun Li Jian (Beijing Aeronautical Technology Research Center)

【机构】 北京航空工程技术研究中心第十研究室；

【摘要】 以某型飞机主起落架疲劳试验为例,介绍起落架在装机状态下以全机作为支持平台进行疲劳试验遇到的飞机作为载体既要支持又要约束的问题、起落架主动加载与机体平衡问题、多通道加载的协调控制问题、试验状态的多变量监控问题、试验件关键部位受空间和结构限制导致可达性差不易检查等技术难点,重点阐述在飞机支持与约束方案、试验载荷的施加与平衡方案、试验的加载控制方案、试验状态监控与试验件探伤检查等方面给出的合理有效的解决方法。该疲劳试验系统安装连接良好,各加载点稳定、协调,试验状态良好,加载精度达到:峰值误差≤2%满量程,动态误差≤5%满量程;加载频率达到:平均7次/分钟。在预期部位发现了关键的疲劳裂纹,并进行了耐久性修理,试验获得圆满成功。更多还原

【Abstract】 In this paper, the main landing gear fatigue test of an aircraft is taken for example,it focuses on the technical difficulties and problems of the landing gear fatigue test in the installed state and under the balance of support through the whole aircraft. Then reasonable and effective solutions are given from several aspects including support and constraints from the whole aircraft, active load on the landing gear set, loading under the balancing of whole aircraft, control of multi-channel load coordination, test condition monitoring, testing and detection of test parts,etc. The test was established smoothly and run well. Test status is also perfect. The error at peak-valley is less than 2% full scale, and dynamic error is less than 5% full scale. Loading frequency is about 7 cycle per minute on average. The fatigue events was find and repaired on the predict positions. The test is completed successfully.更多还原