大型飞机主起落架连接区静力试验误差控制技术

主起落架作为飞机的重要部件,其基于全机的连接区静强度试验是飞机地面静强度试验必须的试验项目.试验中主起落架载荷大、变形大,该部位载荷施加的准确性会直接影响试验考核是否满足要求.为了提高该部位载荷施加准确性,提出基于全机约束点反馈的试验误差控制技术,通过分析全机约束点载荷误差的影响因素,筛选确定影响试验考核部位的载荷施加准确性的主要因素,并对主要因素进行优化处理.以某型飞机主起落架连接区为研究对象开展静力试验.结果表明,大型飞机主起落架连接区的试验误差控制技术可保证试验约束点反馈趋势与预期一致,试验误差控制达到了更高的水平且可靠性更高.飞机姿态主动控制及起落架随动加载等技术有效实现试验误差控制,提升了试验加载精度,可为同类试验提供参考.

Error control technology of static test for the connection area of main landing gear based on large aircraft

The main landing gear is an important part of the aircraft, and the static strength test for the connection area of it based on the full-scale aircraft is necessary. Due to the large load and large deformation of the main landing gear during the test, the accuracy of the loading will determine whether the test satisfy meets the requirements directly. In order to improve the accuracy of the loading in the target area, an error control technology based on the feedback of constraint point based on full-scale aircraft was proposed. Firstly, the influencing factors of the error of the constraint point based on the whole aircraft were analyzed, and then the main factors which affect the accuracy of the loading were selected, and the main factors will be optimized to achieve the accurate loading of the main landing gear. Finally, the static test for the connection area of the main landing based on one type of aircraft was taken as an example, and the test results show that error control technology of static test for the connection area of main landing gear based on large aircraft can ensure the feedback trend of constraint point is consistent with expectations and the error control is more reliable. The conclusion shows that the active control of aircraft attitude and self-adaptable loading technique for undercarriage can achieve error control effectively and improve test accuracy, which can be used as a reference for other similar static test.