阻拦索断裂对螺旋桨舰载机着舰安全影响数值分析

喷气动力舰载机着舰拦阻滑跑，如阻拦索断裂，其逃逸复飞的概率极小。螺旋桨动力舰载机零升阻力大，推重比小，其安全复飞的能力值得研究。本文基于建立的螺旋桨舰载机逃逸复飞仿真模型（含阻拦索工作模型、发动机动力响应模型、升降舵操纵模型与气动力的动力影响修正模型），数值模拟了E-2C舰载预警机着舰阻拦索断裂情况下，其逃逸复飞的过程。仿真计算显示对象飞机在不同气动力、离舰速度与舵面操纵逻辑状态下，其纵向动力学方程中敏感参数与航迹下沉量的动态变化，结合视频数据分析其复飞成功的原因。研究表明：动力对螺旋桨舰载机俯仰力矩与升力特性的影响是其逃逸复飞成功的关键。动力影响使对象飞机的俯仰力矩曲线上移0.15，8°迎角下纵向静稳定性减小85%，升力线斜率增大29.7%、最大升力系数增大39%。这显著改善了螺旋桨飞机逃逸复飞状态下俯仰操纵的敏捷性，升降舵操纵效率与失速特性。动力影响使螺旋桨舰载机可在较小的加速度、离舰速度与有限的留空时间情况下，迅速改变其航迹角，减小航迹下沉量，保证逃逸复飞安全。

Numerical analysis of the effect of block cable crack on landing safety of propeller carrier-based aircraft

If the arresting cable is broken during the arrest sliding of the jet-powered carrier aircraft, the probability of escape and re-flight of the carrier will be extremely small. As the aircraft has a large zero-liter resistance and a small push-weight ratio, its ability to safely re-flight is worth studying. A simulation model for the escape and return flight of the propeller carrier aircraft is built, including a working sub-model for the blocking cable, a sub-model for the engine dynamic response, a sub-model for elevator steering, and a sub-model for correction of the aerodynamic influence. The process of escape and re-flight of the E-2C shipborne early warning aircraft under the condition of vessel blocking cable fracture is numerically simulated. The dynamic changes of the amount of track sinking and the main motion parameters in the longitudinal dynamics equation for the carrier under different aerodynamic forces at different departure speed and with different steering surface control logic are obtained. The simulation results, together with the video data, are analyzed to get the reasons for successful re-flight of the carrier aircraft. The study shows that the influence of power on the pitch torque and lift of the propeller carrier aircraft is the key to its success of escape and re-flight. The power effect causes the plane's pitch moment curve to shift upward 0.15. The longitudinal static stability at the 8° angle of attack decreases by 85%, the slope of the lift line increases by 29.7%, and the maximum lift coefficient increases by 39%, demonstrating significant improvement of the agility of pitch control, efficiency of elevator control, and stall characteristics of the propeller aircraft during escape and re-flight. The power influence enables the propeller carrier aircraft to quickly change its track angle, reduce the sinking amount of the track, and ensure the safety of escape and re-flight.