带有舰尾流的舰载机进场动力补偿系统分析

Analysis of the Approach Power Compensator System With Carrier Air Wake

舰载机发生事故主要是在着舰过程中,其主要原因在于舰载机低速着舰时航迹控制不稳定。为克服这一不稳定问题,提高航迹控制精度,减轻飞行员在着舰阶段的工作负荷,飞机系统中需要引入进场动力补偿系统。采用F/A-18A舰载机参数、应用舰载机纵向运动小扰动线性化模型进行仿真分析,评价飞行品质,并引入飞机姿态控制系统来解决俯仰控制不稳定问题。完成进场动力补偿系统的设计,解决航迹角无法跟踪俯仰角这一航迹控制不稳定问题。引入舰尾流的垂直稳态分量验证了系统的抗扰动能力。

Most carrier-based aircraft disasters occur during landing,with the unstable flight path control at low speed being the major cause.Aiming at this problem,this paper introduces an approach power com pensator system to improve the precision of flight path control and reduce the burden of pilots’landing op eration.By taking the parameters of F/A-18A aircraft,a linear longitudinal motion model of the aircraft un der the condition of small perturbation is established,and the flight quality of the model is analyzed.It is seen that the instability of pitch control is reduced by the attitude control system,and a flight quality of lev el one is achieved.Also,by employing the presented approach power compensator,the problem of the track angle not being able to follow the pitch angle is solved.Finally,the vertical steady state component of the carrier air wake is examined to validate the disturbance resisting capability of the aircraft system.