Equations of motion of a quasisteady flight vehicle utilizing restrained static aeroelastic characteristics
Equations of motion of a quasisteady flight vehicle utilizing restrained static aeroelastic characteristics
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利用约束静态气动弹性特性的准稳态飞行器的运动方程
DOI：
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发表时间：
1985
期刊：
影响因子：
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通讯作者：
J. Love
中科院分区：
文献类型：
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作者：
W. Rodden;J. Love
在挠性飞行器的操纵和动态响应分析中，平均轴提供了通常的参考。由于结构的柔度特性仅针对受约束的结构确定，因此也使用了附着轴或结构轴。如果采用结构轴，则需要结构轴相对于平均轴的取向的关系，因为运动方程确定平均轴的取向。如果不考虑这种关系，正如许多出版物中所没有的那样，结构轴运动方程的解就不会随着计算结构柔度影响系数时所用的支承构型的选择而保持不变，因此是不正确的。本文给出了这种关系式和结构轴的正确运动方程，并在前掠翼飞机常速度纵向机动研究中用数值方法证明了公式的正确性。虽然本文在基本的发展中假设空速恒定，但最后讨论了气动弹性速度导数和气动弹性对阻力的影响。本文假定结构在荷载作用下处于准稳态平衡。
Mean axes provide the usual reference in maneuvering and dynamic response analyses of flexible vehicles. Attached or structural axes have also been used because the flexibility characteristics of the structure are only determined for a restrained structure. If the structural axes are employed, a relationship is required for the orientations of the structural axes relative to the mean axes, since the equations of motion determine the orientations of the mean axes. If this relationship is not considered, as it has not been in a number of publications, the solution to the equations of motion of the structural axes is not invariant with the choice of support configuration used in the calculation of the structural flexibility influence coefficients and is, therefore, incorrect. This relationship and the correct equations of motion for the structural axes are presented, and the correctness of the formulation is demonstrated numerically in studies of longitudinal maneuvering of an example forward-swept-wing airplane at constant forward velocity. Although the paper assumes constant airspeed in the basic developments, it concludes with discussions of aeroelastic speed derivatives and aeroelastic effects on drag. The paper assumes quasisteady equilibrium of the structure with its applied loads throughout.