知识与财富的链接
飞机在起飞降落阶段前轮偏度过大会发生侧翻,应根据滑跑速度合理限制前轮的偏度。基于侧翻现象发生的原理,通过分析起飞降落阶段前轮偏转时飞机相对侧翻轴的合力矩,得到前轮极限滚动方向偏度;建立前轮滚动方向偏度和偏转角度的关系,计算起飞降落状态下各速度的前轮限偏角度以及考虑飞机螺旋桨不对称滑流的前轮中立位,得到前轮的偏转范围。结果表明：计算得到的前轮限偏范围符合前轮限偏的一般特性,能够防止侧翻的同时最大保留前轮纠偏能力。
In order to prevent the aircraft from rollover due to excessive deflection of the nosewheel during takeoff and landing, the nosewheel deflection should be reasonably limited according to the taxiing speed. Based on the principle of the rollover phenomenon, we analyzed resultant moments of the aircraft relative to the rollover axis while the nosewheel deflecting, determined nosewheel rolling direction limitation, studied on the relationship between the rolling direction of the nosewheel and the deflection, calculated the deflection angle of the nosewheel at different speeds and the neutral position of the nosewheel while considering the asymmetric slip flow of the propeller, then got the deflection range of the nosewheel during takeoff and landing phase. The limited range of the nosewheel deflection obtained by the calculation results show that the limited range accords with the general characteristics of deflection limitation, which can prevent rollover while retaining the correcting capability of the nosewheel.
