舰载机偏中心定位弹射起飞弹射杆载荷分析

 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。

Launch Bar Load Analysis of Carrier-based Aircraft During Off-center Catapult Launch

A six-degree-of-freedom dynamics model of catapult launch of a carrier-based aircraft is established taking into consideration its off-center position. The launch bar load during the off-center catapult launch is calculated. The effect of initial off-center distance and take-off weight on the launch bar load is analyzed, and the kinetic cause of this phenomenon is also discussed in detail. From the catapult launch calculation, three important conclusions are obtained: the roll movement of the aircraft is the primarily source of the bending moment and the torsion which act on the launch bar; the bending moment and the torsion increase sharply with the increase of initial off-center distance, while the axle load is only slightly affected; in the prophase of catapult launch, the launch bar loads, including its axle load, bending moment and torsion, all increase with the decrease of the take-off weight, but in the anaphase of catapult launch, these loads decrease with the decrease of the take-off weight.