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 Stability analysis for a deformable aircraft is one of the important subjects in the context of modern flight dynamics. This paper studies longitudinal stability of the deformable aircraft with and without flight control system, involving interaction between rigid motion modes and elastic vibration shapes of the deformable aircraft and between flight control system and airframe dynamics. From a numerical example it is shown that the effect of the structural distortion of the aircraft with flight control... Stability analysis for a deformable aircraft is one of the important subjects in the context of modern flight dynamics. This paper studies longitudinal stability of the deformable aircraft with and without flight control system, involving interaction between rigid motion modes and elastic vibration shapes of the deformable aircraft and between flight control system and airframe dynamics. From a numerical example it is shown that the effect of the structural distortion of the aircraft with flight control system on its longitudinal stability is quite considerable, and hence can't be neglected, although it belongs in a type of little plane. This influence would not only degrades flying qualities of the aircraft but also, sometimes, causes a new type of instability, that is unacceptable, referred to as coupling instability between flight control system and elastic structural dynamics. Thus, in stability analysis for an aircraft and designing its flight con rol system we have to consider the aircraft as deformable body, not rigid body, and use highorder smalldisturbance equations, involving elastic degrees of freedom of the aircraft.  本文讨论弹性飞机的纵向稳定性问题。包括带与不带飞行控制系统两种情况。文中通过算例,分析讨论弹性飞机的总体运动模态和弹性运动振型之间的藕合以及弹性飞机本身和飞行控制系统之间的耦合。分析与计算表明,带有飞行的控制系统的飞机,其结构弹性变形运动对纵向稳定性的影响,即使对于算例中的“小”飞机,也是不可忽视的。飞机的弹性影响,不但会降低飞机的飞行品质,有时还会引起飞机与系统之间的耦合不稳定。  The flight mechanism of birds and big insects was probed valuably, and airframe dynamics and airfoil aerodynamics of Flapping Wing Micro Aerial Vehicle (FWMAV) were researched. The conclusion is that aerodynamic force, gravity, and impetus from airfoil act normal to airframe, for airfoil moment composed of two degrees of freedom for flapping and rotation, the impetus of FWMAV are its instantaneous forces which are represented as the sum of the instantaneous translational force and rotational force.... The flight mechanism of birds and big insects was probed valuably, and airframe dynamics and airfoil aerodynamics of Flapping Wing Micro Aerial Vehicle (FWMAV) were researched. The conclusion is that aerodynamic force, gravity, and impetus from airfoil act normal to airframe, for airfoil moment composed of two degrees of freedom for flapping and rotation, the impetus of FWMAV are its instantaneous forces which are represented as the sum of the instantaneous translational force and rotational force. So the relevant parameter equations were acquired and the dynamic model was established. Simulations on the proposed model demonstrate that the flight process can be simulated preferably if the relevant parameters are tuned reasonably.  对鸟和昆虫的飞行机理进行了有价值的探讨,并对扑翼式微型飞行器机体动力学和机翼空气动力学进行了详细的分析。由此分析得出结论:机体所受外力为空气动力、自身重力和机翼作用于机体的驱动力,而采用扑动与扭转两个自由度飞行的机翼所产生的机体驱动力就是由瞬时平移力和旋转循环力合成的瞬时空气动力,从而得出了相应的参数方程以及整机动力学模型。对所建模型的仿真结果表明,只要合理选择参数,各种飞行过程能得到很好的模拟。  
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