高超声速飞行器机翼颤振主动控制系统
Adaptive Control of a Shape Memory Spring Actuation for Twist Wing

飞行器飞行过程中由于气动弹性效应会引起机翼颤振，并且随着飞行马赫数（速度）的提高，颤振类型会发生改变，对飞机结构的破坏性增大，因此若不能有效抑制机翼颤振将对高超音速飞行器飞行造成严重后果。为此，提出了一种形状记忆弹簧扭转机翼自适应控制系统，该系统采用反馈控制，通过记忆弹簧驱动控制产生相应的变形以稳定结构抑制颤振。根据驱动结构设计、理论推导以及测试实验成功验证了该方案的可行性，采用参数自整定模糊PID控制算法，通过控制实验得到了SMA弹簧驱动器的偏转角度与电流强度的关系，在控制电流为8 A时，偏转角度在6s内可达到60°，响应速度10°/s。事实表明，采用文中设计的形状记忆弹簧扭转机翼自适应控制系统，可以对机翼翼面受力状态进行自适应监测与控制，使机翼结构吸取的能量等于消耗的能量，保持等幅振动而不发生颤振。
In the process of flight, airfoil flutter will be caused by the aero-elastic effect, and as the flight Mach number increases, the type of flutter will change, the destructive effect of the aircraft structure increases. Therefore, if the flutter of the hypersonic aircraft has not been effectively inhibited, it will cause serious consequences. Thus, an adaptive control system of shape memory spring torsion wing have been conducted to restrain the flutter of the wings. The purpose of the experimental test was to demonstrate the mechanism with the SMA Spring actuator has the ability to drive the wing to rotate around the central axis. A description of the system requirements associated with the SMA Spring actuator and its integration into the wing structure are provided and discussed. The relationship between the deflection angle and the current intensity of the SMA Spring actuator was obtained through the control of the fuzzy PID control algorithm. The deflection angle can reach 60° and the response speed is 10°/s in 6s when the control current is 8A. Test results showed that the SMA Spring actuator was able to successfully twist the wing according to the feedback control rule, the airfoil can be subjected to adaptive monitoring and controlling, so that the energy absorbed by the wing structure remain equal to the energy consumed, which achieve the purpose of suppressing the flutter