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A methodology for using nonlinear aerodynamics in aeroservoelastic analysis and design

机译:在气动弹性分析和设计中使用非线性空气动力学的方法

摘要

A methodology is presented for using the Volterra-Wiener theory of nonlinear systems in aeroservoelastic (ASE) analyses and design. The theory is applied to the development of nonlinear aerodynamic response models that can be defined in state-space form and are, therefore, appropriate for use in modern control theory. The theory relies on the identification of nonlinear kernels that can be used to predict the response of a nonlinear system due to an arbitrary input. A numerical kernel identification technique, based on unit impulse responses, is presented and applied to a simple bilinear, single-input single-output (SISO) system. The linear kernel (unit impulse response) and the nonlinear second-order kernel of the system are numerically-identified and compared with the exact, analytically-defined and linear and second-order kernels. This kernel identification technique is then applied to the CAP-TSD (Computational Aeroelasticity Program-Transonic Small Disturbance) code for identification of the linear and second-order kernels of a NACA64A010 rectangular wing undergoing pitch at M = 0.5, M = 8.5 (transonic), and M = 0.93 (transonic). Results presented demonstrate the feasibility of this approach for use with nonlinear, unsteady aerodynamic responses.
机译:提出了一种在航空弹塑性(ASE)分析和设计中使用非线性系统的Volterra-Wiener理论的方法。该理论适用于非线性气动响应模型的开发,该模型可以状态空间形式定义,因此适合在现代控制理论中使用。该理论依赖于对非线性核的识别,该核可用于预测由于任意输入而引起的非线性系统的响应。提出了一种基于单位脉冲响应的数字核识别技术,并将其应用于简单的双线性,单输入单输出(SISO)系统。对系统的线性核(单位脉冲响应)和非线性二阶核进行数值识别,并将其与精确的,解析定义的以及线性和二阶核进行比较。然后将该核识别技术应用于CAP-TSD(计算气动弹性程序-跨音速小扰动)代码,以识别NACA64A010矩形机翼在M = 0.5,M = 8.5(跨音速)时俯仰的线性和二阶核,M = 0.93(跨音速)。提出的结果证明了这种方法用于非线性,非稳态气动响应的可行性。

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  • 作者

    Silva Walter A.;

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  • 年度 1991
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