Rotorcraft Modeling Renovation for Improved Fidelity
Rotorcraft Modeling Renovation for Improved Fidelity
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DOI：
10.4050/f-0075-2019-14637
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发表时间：
2019-05
期刊：
影响因子：
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通讯作者：
N. Cameron;Linghai Lu;A. Gubbels;M. White;G. Padfield;Dheeraj Agarwal
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作者：
N. Cameron;Linghai Lu;A. Gubbels;M. White;G. Padfield;Dheeraj Agarwal
本文报告的研究既检查了建立和新的系统识别技术的旋翼机飞行模型更新。基于传统飞机的飞行行为模型通常是新设计的起点，并且当在新原型的早期飞行测试中收集数据时，可以验证保真度或模型准确性。随着数据的流入，飞行模型可以在保真度上得到改进，最终支持认证，前提是体现了正确的物理学。系统识别已成为一种既定的方法，用于提高逼真度，并提出飞行和飞行模型不匹配和丢失的物理之间的因果关系。我们研究的目标包括扩展当前的系统识别方法来处理非线性模型结构，并建立适当的近似复杂的旋翼机空气动力学所需的提高保真度，包括机动尾流畸变效应。这项研究的重点是使用利物浦的FLIGHTLAB贝尔412模拟模型的基础上收集的数据对国家研究理事会的先进系统研究飞机的改造。我们建立在早期的工作使用频域方法，非常适合线性模型结构和飞行条件足够稳定，允许控制扫描数据被收集。对于悬停和低速飞行，强烈的非线性所造成的转子尾流的影响和显着偏差的配平条件，需要一个不同的方法和文件显示了如何一个新的时域方法，使模型结构和参数被识别增量。
The research reported in this paper examines both established and new system identification techniques for rotorcraft flight-model renovation. Flight behavior models based on legacy aircraft are often the starting point for a new design and the fidelity, or model accuracy, can be validated when data are gathered in early flight testing of the new prototype. As data flow in, so flight models can be improved in fidelity, eventually supporting certification, provided the correct physics are embodied. System identification has become an established method for enhancing fidelity and suggesting causal relationships between flight and flight-model mismatches and missing physics. The objectives of our investigation include extending current system identification methods to address nonlinear model structures, and establishing appropriate approximations to the complex rotorcraft aeromechanics required to enhance fidelity, including maneuver wake distortion effects. The research is focused on renovation using Liverpool's FLIGHTLAB Bell 412 simulation model based on data gathered on the National Research Council's Advanced Systems Research Aircraft. We build on earlier work using frequency-domain methods, ideally suited to linear model structures and flight conditions sufficiently stable to allow control sweep data to be gathered. For hover and low-speed flight, strong nonlinearities caused by rotor-wake effects and significant deviations from the trim conditions, require a different approach and the paper shows how a new time-domain approach enables model structures and the parameters to be identified incrementally.