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首页> 外文期刊>Journal of aerospace engineering >Parameter Estimation of Unmanned Flight Vehicle Using Wind Tunnel Testing and Real Flight Data
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Parameter Estimation of Unmanned Flight Vehicle Using Wind Tunnel Testing and Real Flight Data

机译：基于风洞测试和真实飞行数据的无人飞行器参数估计

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The work presented in this paper addresses the longitudinal parameter estimation of an unmanned configuration using wind tunnel testing and flight data. For this purpose, an unmanned aerial vehicle has been designed with a cropped delta planform and rectangular crosssection. Exhaustive full-scale wind tunnel tests were carried out on the designed unmanned flight vehicle to capture the linear and nonlinear variation of aerodynamic force and moment coefficients. The measured wind tunnel test data, in the form of signals, have been processed to forces and moments about the desired reference point of the designed unmanned platform. A comprehensive discussion on the obtained results from wind tunnel testing has been presented. In order to enhance the confidence in the generated aerodynamic database from wind tunnel testing and also to estimate the dynamic derivatives, two sets of real flight data pertaining to longitudinal dynamics (acquired during the flight tests) have been used. The parameter estimation in the linear domain has been carried out using conventional maximum likelihood and least-square methods. The estimated longitudinal parameters from the flight data were used to corroborate the aerodynamic coefficients derived from the wind tunnel measurements. (C) 2016 American Society of Civil Engineers.
机译：本文介绍的工作使用风洞测试和飞行数据解决了无人配置的纵向参数估计问题。为此目的，已经设计了具有裁剪的三角形平面形状和矩形横截面的无人飞行器。在设计的无人飞行器上进行了详尽的风洞试验，以捕捉气动力和力矩系数的线性和非线性变化。以信号形式测得的风洞测试数据已处理为力和力矩，该力和力矩围绕设计的无人驾驶平台的所需参考点进行。已经对风洞测试获得的结果进行了全面的讨论。为了增强对风洞测试生成的空气动力学数据库的信心并估计动态导数，已使用了两组与纵向动力学有关的真实飞行数据（在飞行测试中获取）。线性域中的参数估计已使用常规的最大似然法和最小二乘法进行了。从飞行数据中估算出的纵向参数被用于证实从风洞测量中得出的空气动力学系数。 （C）2016年美国土木工程师学会。

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