舰载机前起落架突伸性能优化

Optimization on fast-extension performance of nose landing gear of carrier-based aircraft

为提高舰载机的起飞性能,通过对双腔油气缓冲器阻尼油孔截面积随行程变化的控制,实现某舰载机前起落架突伸性能优化.该方法选取二质量弹簧—阻尼器系统作为前起落架突伸运动的力学模型,将阻尼油孔面积随行程变化的函数代入突伸运动微分方程,建立以突伸时间为优化目标的数学模型.采用黄金分割优化方法,得到优化后突伸运动位移和速度曲线.经与3组不同直径常截面油孔在同样结构参数和初始填充参数下曲线的对比分析,证明采用变截面油孔缓冲器优化前起落架突伸性能的合理性.

To improve the take-off performance of carrier-based aircrafts, the fast-extension performance of the nose landing gear of a carrier-based aircraft is optimized by controlling the process that the crosssection area of damping oil-hole of oleo-pneumatic buffer with two-stage shock absorber changes with the stroke. A mechanical model is built for the fast-extension motion of nose landing gear using the two-massspring-damping system, the function on the changes of the cross-section area of damping oleo-hole with the stroke is substituted into the fast-extension motion differential equation, and the mathematical model is established to optimize the fast-extension time. The displacement curves and velocity curves of the optimized fast-extension motion are obtained by the golden section optimization method. The curves are compared which are obtained from three sets of damping oleo-hole with different constant section area under the same structure parameters and initial filling parameters. The result shows that it is rational to use the damping oil-hole with variable cross-section area to optimize the fast-extension performance of the nose landing gear of cartier-based aircraft.