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Flutter of Maneuvering Aircraft

机译：机动飞机颤振

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The objective of this paper is to investigate how the aeroelastic stability, particularly flutter, is affected by aircraft maneuvers. The authors' investigation is based on a comprehensive mathematical model of aircraft, which is achieved by seamlessly integrating all the disciplines pertinent to flight of aircraft. The aircraft is treated as an unstrained, flexible multibody system subject to unsteady aerodynamics. The bodies are fuselage, wing, and horizontal and vertical stabilizers, whose structures are modeled as beams in bending and torsion. The equations of motion are derived using Lagrange's equations in quasi-coordinates. The resulting equations are a set of nonlinear ordinary differential equations of relatively high order. The final model is used to determine flutter speeds of aircraft at steady level turn and steady climb at various altitudes. These maneuvers are especially chosen to keep the equations time invariant. The numerical results are given for a generic transport model (GTM). The stability of a GTM is affected by turn radius, climb angle, and altitude. The results for climbing flight can be extended to address stability of gliding flight. (C) 2014 American Society of Civil Engineers.
机译：本文的目的是研究飞机操纵如何影响气动弹性稳定性，特别是颤振。作者的研究基于飞机的综合数学模型，该模型是通过无缝集成与飞机飞行有关的所有学科而实现的。该飞机被视为不受稳定的空气动力学约束的不变形，灵活的多体系统。车身为机身，机翼以及水平和垂直稳定器，其结构建模为弯曲和扭转梁。运动方程是使用准坐标中的拉格朗日方程导出的。所得方程是一组相对较高阶的非线性常微分方程。最终模型用于确定飞机在各种高度下稳定转弯和稳定爬升时的扑动速度。特别选择这些操作以使方程保持时间不变。给出了通用运输模型（GTM）的数值结果。 GTM的稳定性受转弯半径，爬升角度和高度的影响。爬升飞行的结果可以扩展以解决滑行飞行的稳定性。 （C）2014年美国土木工程师学会。

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