Numerical Analyses of Discrete Gust Response for an Aircraft
Numerical Analyses of Discrete Gust Response for an Aircraft
复制标题
DOI：
10.2514/1.2531
复制
发表时间：
2004-11
影响因子：
2.2
通讯作者：
Guowei Yang;S. Obayashi
中科院分区：
文献类型：
--
作者：
Guowei Yang;S. Obayashi
基于Navier-Stokes方程和结构和飞行动力学运动方程，研究了超音速输运模型在垂直离散阵风气流扰动下的动力响应。通过气动力方程和动力学运动方程之间的次迭代，发展了一种紧耦合方法。首先，在垂直俯冲运动为刚体和单自由度的假设下，比较了直接耦合法和准定常模型法的计算结果。在此基础上，分析了考虑和不考虑结构变形的飞机外形在俯冲和俯仰两个运动自由度下一负余弦阵风剖面的阵风响应。
Based on Navier-Stokes equations and structural and flight dynamic equations of motion, dynamic responses in vertical discrete gust flow perturbation are investigated for a supersonic transport model. A tightly coupled method was developed by subiterations between aerodynamic equations and dynamic equations of motion. First, under the assumption of rigid-body and single freedom of motion in the vertical plunging, the results of a direct-coupling method are compared with the results of quasi-steady model method. Then, gust responses for the one-minus-cosine gust profile arc analyzed with two freedoms of motion in plunging and pitching for the airplane configurations with and without the consideration of structural deformation.