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根据垂尾载荷校准及建模需求,对飞机V型外倾双垂尾结构受载情况进行了分析和简化,确定了校准试验载荷,研制了垂尾载荷校准试验专用龙门梁架。采用液压协调加载技术,完成了外倾双垂尾载荷校准试验,建立了满足测载要求的载荷模型。此种方法充分利用了左右垂尾外倾、双垂尾之间空间较大的特点,对左右垂尾对称施加向外的单点、多点载荷,加载载荷侧向分量左右自平衡,垂向分量依靠飞机自身重量即可平衡,飞机不需要复杂的固定与约束。试验中采用先搭建龙门框架,再停放飞机的方法,降低了试验风险、加快了试验进度,取得了良好的试验结果,对其他此类结构的载荷校准具有一定的借鉴作用。
According to the requirements of vertical tail load calibration and modeling, the loading situation of V-shaped caper and double vertical tail structure of aircraft is analyzed and simplified, the calibration test load is determined, and the special gantry beam test for vertical tail load calibration test is developed. Using hydraulic coordinated loading technology, the camber double vertical tail load calibration test was completed, and the load model satisfying load measuring requirement was established. This method takes full advantage of left and right tail cape, large vertical space between the two tail features, applied to the left and right symmetrical outward single point, multi-point load, load side load left and right self-balancing, vertical Components rely on the weight of the aircraft to balance, the aircraft does not require complex fixation and constraints. In the experiment, the method of setting up the gantry frame and then parking the aircraft was adopted, which reduced the risk of test, accelerated the test progress and achieved good test results. It has some reference for the load calibration of other such structures.