基于线性矩阵不等式的改进阻尼F-16飞机动力学模型鲁棒控制

World Academy of Science, Engineering and Technology, International Journal of Computer and Information Engineering Pub Date : 2017-01-02 DOI:10.5281/ZENODO.1128926

J. P. P. Andrade, V. A. F. Campos

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引用次数: 5

摘要

本文介绍了线性矩阵不等式(LMI)在F-16飞机鲁棒控制中的应用，通过一种保证闭环系统阻尼系数的算法。结果表明，零点和增益设置足以确保相对于各种工作点的鲁棒性能和稳定性。所使用的技术是极点放置，其目的是将系统置于复杂平面的特定区域的闭环极点中。介绍并讨论了F-16飞机动力学模型的试验结果。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Robust Control of a Dynamic Model of an F-16 Aircraft with Improved Damping through Linear Matrix Inequalities

This work presents an application of Linear Matrix Inequalities (LMI) for the robust control of an F-16 aircraft through an algorithm ensuring the damping factor to the closed loop system. The results show that the zero and gain settings are sufficient to ensure robust performance and stability with respect to various operating points. The technique used is the pole placement, which aims to put the system in closed loop poles in a specific region of the complex plane. Test results using a dynamic model of the F-16 aircraft are presented and discussed.

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World Academy of Science, Engineering and Technology, International Journal of Computer and Information Engineering

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