舰载机偏心情况下弹射起飞研究

Research on carrier-based aircraft catapult launching in the case of different eccentricity

在研究舰载机弹射过程中,考虑弹射杆形变、轮胎的滚动摩擦力和侧向滑动摩擦力对弹射起飞的影响,通过建立完整的蒸汽弹射器模型和舰载机六自由度动力学模型,并分析舰载机与弹射装置之间的衔接情况,分析不同偏心距情况下舰载机运动姿态、弹射杆和弹射器的受力。舰载机在偏心情况下会发生滚转运动与偏航运动,进而使弹射杆受到垂直于舰载机运动方向的侧偏力。仿真结果表明:侧偏力的产生原因主要是滚转运动和偏航运动,偏心距越大,弹射杆所受的侧偏力越大,而俯仰角几乎不变;汽缸有杆腔压力随着初始偏心距增大而有小幅下降,但变化不明显,因而舰载机的速度也有小幅下降。

During the process of aircraft catapult research,considering the influence on catapult takeoff caused by the deformation of catapulting bar and the rolling and side-sliding friction of tire,by establishing complete steam catapult model and carrier aircraft six degrees of freedom dynamic model and analyzing the convergence situation between aircraft carrier and catapult device,the aircraft carrier motion and the force on the catapulting bar at different eccentricity are analyzed. In the case of eccentricity,the aircraft will present rolling and yawing movement,resulting in the force in the vertical movement of aircraft.The simulation results show that the main cause of bending movement and torque is rolling and yawing movement,and the greater the eccentricity is,the larger the force on the catapulting bar is. But the pitch angle is almost unchanged. The pressure of the cylinder with piston presents a slight decrease as the increase of initial eccentricity,so the speed of aircraft has a slight decrease.