Flutter is an important topic to be considered during an aircraft development mainly due to its potentially catastrophic behavior. Typically a new aerial vehicle can require the addition of mass and limitations on its flight envelope to be flutter free. As an alternative, active control technologies can be used employing actuators and sources of power, and there are different techniques for computing the actuator’s force. In general, many approaches depend on describing the aeroelastic system through the state-space representation in the time domain. However, the state-space dynamic matrix typically contains nonphysical eigenvalues due to the unsteady aerodynamic forces approximations. In this context, this article introduces an algebraic arrangement for designing a modal controller to suppress the flutter phenomenon. The approach considers the modal state-space realization combined with the linear quadratic regulator to compute a control gain. The gain is converted from the new modal domain to the physical, and the control force introduces an effect of incremental damping for all flight envelope, although the controller is designed particularly for the flutter speed. To demonstrate the approach, numerical simulations are carried out considering the three-degree-of-freedom airfoil. The results show that this technique allows stabilizing the system.

颤振是飞机研发过程中要考虑的重要主题，主要是因为其潜在的灾难性行为。通常，新的飞行器可能需要增加质量并限制其飞行包线才能无抖动。替代地，可以使用采用致动器和动力源的主动控制技术，并且存在用于计算致动器力的不同技术。通常，许多方法都依赖于通过时域中的状态空间表示来描述气动弹性系统。但是，由于不稳定的空气动力近似，状态空间动态矩阵通常包含非物理特征值。在这种情况下，本文介绍了一种代数布置，用于设计模态控制器以抑制颤动现象。该方法考虑了与线性二次调节器相结合的模态状态空间实现，以计算控制增益。增益从新的模态域转换为物理域，并且控制力为所有飞行包线引入了增量阻尼的效果，尽管控制器是专为扑扑速度而设计的。为了演示该方法，考虑了三自由度翼型进行了数值模拟。结果表明，该技术可以稳定系统。尽管该控制器是专为扑动速度而设计的。为了演示该方法，考虑了三自由度翼型进行了数值模拟。结果表明，该技术可以稳定系统。尽管该控制器是专为扑动速度而设计的。为了演示该方法，考虑了三自由度翼型进行了数值模拟。结果表明，该技术可以稳定系统。