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考虑舰载机偏中心定位,建立了六自由度弹射起飞动力学模型,对偏中心弹射过程中弹射杆受载情况进行了分析计算,讨论了初始偏心距离和起飞重量对弹射杆载荷的影响,并详细论述了其动力学成因。研究结果表明:飞机的滚转运动是导致弹射杆承受较大弯矩和扭矩的主要原因;弹射杆弯矩和扭矩随初始偏心距离的增大而迅速增大,但其轴向拉力受初始偏心距离影响较小;在弹射滑跑初始阶段,弹射杆的轴向拉力、弯矩以及扭矩随起飞重量的减小而增大,而在弹射滑跑后期,弹射杆所受载荷则随起飞重量的减小而减小。
Considering the off-center positioning of the carrier-based aircraft, a six-DOF ejection dynamic model was established and the loading conditions of the ejector rod during the center-ejection process were analyzed. The influence of the initial eccentric distance and take-off weight on the ejector load was discussed. The dynamics of formation is discussed in detail. The results show that the rolling motion of the aircraft is the main reason that the ejector rod is subjected to large bending moment and torque. The bending moment and torque of the ejector rod increase rapidly with the increase of the initial eccentricity. However, the axial tensile force is affected by the initial eccentricity The distance between the ejector and the take-off weight in the initial stage of ejector sliding, the axial tension, bending moment and torque of the ejector rod increased with the decrease of take-off weight, Reduce and decrease.