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非对称因素会导致舰载机在弹射后出现横航向偏离,并影响其纵向起飞航迹。针对定位偏心、弹射道偏角、甲板横摇等三类扰动因素,开展了这些不对称因素对飞机弹射起飞特性影响规律的理论分析与仿真计算,掌握了飞机在甲板滑跑段的偏航运动特性以及离舰上升段的横航向偏离特性。基于弹射起飞后飞机航迹下沉量与滚转角二项安全性要求,通过仿真计算建立了安全甲板风包线,结果表明:安全甲板风包线的下边界由最大航迹下沉量约束,左右边界由最大滚转角限制确定,上边界由最大海面风速决定;定位偏心、甲板横摇等非对称因素将显著缩小安全甲板风包线的风速和风向角范围。
Asymmetric factors can cause cross-heading deviations of the carrier aircraft after they have been ejected and affect their longitudinal takeoff trajectory. According to three kinds of perturbation factors, such as positioning eccentricity, declination angle of deflection projectile and deck rolling, the theoretical analysis and simulation calculation of the influence law of these asymmetric factors on the launching characteristics of the aircraft are carried out. The yaw motion of the aircraft during the slip section of the deck Characteristics as well as the lateral deviation characteristics of the ascent-rising section of the ship. Based on two safety requirements of aircraft track sinking and roll angle after take-off, the safe envelope air line was established through simulation calculation. The results show that the lower boundary of safe envelope wind envelope is restrained by the maximum track sinking amount, The left and right boundaries are determined by the maximum roll angle limit. The upper boundary is determined by the maximum sea surface wind speed. Asymmetric factors such as positioning eccentricity and deck rolling will significantly reduce the wind speed and the wind direction angle of the safety envelope wind envelope.