基于飞机总能量控制系统(TECS)的飞行航迹/速度解耦控制方法研究

对飞机航速／速度解耦控制系统进行了分析与研究。将偏差控制与基于飞机总能量控制的解耦理论结合在一起，实现了对飞行速度和飞行高度的无稳差控制。对某型飞机在低动压情况下6组典型飞行状态进行解耦控制律设计和仿真，结果显示该方法在所有6组状态下均达到飞机解耦控制标准。由于所选6组飞行状态包含飞机参数不确定信息(有油、无油状态)和干扰不确定信息(地面效应)，从而使得所设计控制律对飞机解耦控制具有一定的鲁棒稳定性。

An Improved Decoupling Method for Airspeed and Flight Path Based on Total Energy Control System

Total energy control is a new decoupling control concept for vertical flight path and speed control through coordinating thrust and elevator effects. In order to eliminate the stable error of airspeed and altitude which is inherently generated by the existing core algorithm of total energy control system (TECS) in eqs.(11) and (12), an improved TECS core algorithm was given in eqs.(17) and (18), which adopted proportional-derivative control method. Based on this new core algorithm, the structure of aircraft longitude TECS control mode was built (as shown in fig.2). The TECS core flight path angle and speed control algorithm provides about 80% of what is needed for an advanced fly-by-wire manual control mode. Finally, digital simulations of this new control system are conducted for an aircraft in six typical situations. The results, as given in Figs.3 and 4, show that with our improved decoupling method the stable error of airspeed and altitude are eliminated. Since these six typical situations include the information of structure change (oil state change) and disturbance (turbulence), our decoupling control law possesses good robust performance.