基于TECS的舰载机轨迹角控制研究

Research on Flight Path Angle Control of Carrier-based Aircraft Based on TECS

舰载机进近着舰时多面临轨迹稳定性的问题。轨迹稳定性的下降和飞机进入第二平飞状态时阻力急剧增大有关,此时飞机的轨迹变化和操纵期望不匹配,突出表现为飞机总能量的急剧发散。对此基于总能量控制(TECS)的思路,设计了舰载机在轨迹不稳定性情况下的轨迹角控制器,经同常规动力补偿系统(APCS)的对比和蒙特卡洛拉偏仿真,表明基于TECS设计的轨迹角控制器,对于解决轨迹不稳定问题,有重要的工程意义。

Carrier-based aircraft's approach landing state often faces flight path stability problems. The decline of flight path stability is related to the dramatic increase of drag force when the aircraft enters the second level flight area, where mismatch between aircraft longitudinal control and actual trajectory changes appear, and mainly manifested by the sharp divergence of the total energy of the aircraft. Based on the idea of Total Energy Control System (TECS), a path angle controller for carrier-based aircraft under flight path instability is designed. Compared with conventional Automatic Power Compensation System (APCS) and Monte Carlo simulation, it shows that the path angle controller designed by TECS has good application value and has important engineering significance for solving the problem of flight path instability.