某歼击机前起落架着陆瞬间有关参数的试验研究

Parameters Study at Touchdown Instant of the Nose Undercarriage of Fighter Airplane

以某歼击飞机前起落架为例,用落震试验的方法,通过分析起落架有关参数随机轮转速变化的情况,来研究飞机着陆瞬间起落架的状况。研究结果表明,在飞机着陆过程中,当起转水平载荷达到最大值时,起落架逆航向的弹性变形还未结束;当起落架逆航向的弹性变形达到最大值时,机轮从滑动转为滚动。

The status of an undercarriage of fighter airplane at the touchdown instant is studied by analyzing the undercarriage parameters which change with the wheel rotational speed in the drop test. The result indicates that when the spin-up horizontal load is the maximum during the landing, the opposite course residual elasticity deformation of the undercarriage is not finished, and when the opposite course residual elasticity deformation of the undercarriage is the maximum, the wheel movement is changed from slide to roll.