有起落架布置的双三角翼载荷测试技术研究

针对起落架布置在机翼上从而很难实现对机翼根部切面载荷测试的问题,结合某型飞机全机载荷测试项目,分析研究了该型机翼的结构特点,并设计机翼根部弯矩、剪力、扭矩测试应变电桥。考虑到外场无承力结构可作为约束载荷点的试验条件,提出全机自平衡多点协调加载标定模型,得到了较准确的载荷标定数据。同时对标定试验数据进行多元回归分析,建立了载荷标定方程,并通过校验工况对载荷标定方程进行了误差分析,大载荷下的误差均不超过5%,可满足一般的工程要求。最后经飞行实测验证,得到了该类机翼根部切面准确的载荷-时间历程。该技术可以运用到有起落架布置的机翼载荷外场测试上,对起落架以内的切面载荷测试可作为通用方法使用。

Load Testing Technology of Double Delta Wing Mounting Undercarriage

The root of a wing-mounted undercarriage load was investigated in light of how difficult it currently is to test, combined with a certain type of aircraft load test project. A wing root strain-gage bridge was designed that included moment, shear and torque. Considering the condition that there was no load-carrying structure as a constraint point in the outfield, a self-balanced model of the whole structure with multiple-point coordinated loading was established. Using these methods, reliable calibration data was obtained and analyzed with multiple regression, and the load calibration equation was established. In the check condition, the error of the load calibration equation was obtained to be less than 5% in the case of large load and the engineering utilization requirements have been met. The aircraft ran test flights, so the measured load of the wing was derived using the calibration equation. This method can be applied generally to the root of wing-mounted undercarriage load tests in the outfield.