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首页> 外文期刊>Journal of guidance, control, and dynamics >Longitudinal Flight Dynamics of Bioinspired Ornithopter Considering Fluid-Structure Interaction
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Longitudinal Flight Dynamics of Bioinspired Ornithopter Considering Fluid-Structure Interaction

机译：考虑流体-结构相互作用的生物启发旋翼机的纵向飞行动力学

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This paper addresses the flapping frequency-dependent trim flight characteristics of a bioinspired ornithopter. An integrative ornithopter flight simulator including a modal-based flexible multibody dynamics solver, a semiempirical reduced-order flapping-wing aerodynamic model, and their loosely coupled fluid-structure interaction are used to numerically simulate the ornithopter flight characteristics. The effect of the fluid-structure interaction of the main wing is quantitatively examined by comparing the wing deformations in both spanwise and chordwise directions, with and without aerodynamic loadings, and it shows that the fluid-structure interaction created a particular phase delay between the imposed wing motion and the aeroelastic response of the main wing and tail wing. The trimmed level flight conditions of the ornithopter model are found to satisfy the weak convergence criteria, which signifies that the longitudinal flight state variables of ornithopters need to be bounded and that the mean value of the variables are converged to the finite values. Unlike conventional fixed-wing aerial vehicles, the longitudinal flight state variables, such as forward flight speed, body pitch attitude, and tail-wing angle of attack in trimmed level flight, showed stable limit-cycle oscillatory behaviors with the flapping frequency as the dominant oscillating frequency. The mean body pitch attitude and tail-wing angle, and the root-mean-square value of the body pitch attitude, decreased as the flapping frequency increased. In addition, the mean forward flight speed is found to almost linearly increase with the flapping frequency.
机译：本文探讨了生物启发性鸟类直升机的随拍动频率而定的微调飞行特性。包括基于模式的柔性多体动力学求解器，半经验降阶扑翼空气动力学模型以及它们的松散耦合的流固耦合在内的一体式飞行器飞行模拟器用于数值模拟飞行器的飞行特性。通过比较翼展在翼展方向和弦向和翼弦方向（在有和没有空气动力学载荷的情况下）的变形，定量地检查了主翼流固耦合的影响，结果表明，流固耦合在所施加的力之间产生了特定的相位延迟。机翼的运动以及主翼和尾翼的气动弹性响应。发现该飞行器模型的水平飞行条件满足弱收敛准则，这表明需要限制飞行器的纵向飞行状态变量，并且变量的平均值收敛到有限值。与常规固定翼飞行器不同，纵向飞行状态变量（如微调水平飞行中的前向飞行速度，身体俯仰姿态和尾翼迎角）显示出稳定的极限周期振荡行为，其中拍击频率为主导振荡频率。随着拍打频率的增加，平均身体俯仰姿态和尾翼角度以及身体俯仰姿态的均方根值均减小。此外，发现平均向前飞行速度几乎随拍动频率线性增加。

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