Case Study: Development of a Baseline Controller for Automatic Landing of an F-16 Aircraft Using Linear Matrix Inequalities (LMIs)
Case Study: Development of a Baseline Controller for Automatic Landing of an F-16 Aircraft Using Linear Matrix Inequalities (LMIs)
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案例研究：使用线性矩阵不等式 (LMI) 开发用于 F-16 飞机自动着陆的基线控制器
DOI：
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发表时间：
2000
期刊：
影响因子：
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通讯作者：
T. Marz
中科院分区：
文献类型：
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作者：
D. Seto;E. Ferreira;T. Marz
摘要：在这份报告中，我们提出了初步的结果设计的基线控制器的F-16飞机自动着陆系统使用线性矩阵不等式（LMI）为基础的方法。我们从飞机控制和动力学的一般研究开始，以获得飞机动力学模型及其内环控制系统的结构知识。然后，我们确定了一个线性模型沿着下滑路径的内环控制系统在模拟器中。利用这个线性模型，控制目标是解决一个稳定问题--利用线性状态反馈控制使飞机沿沿着轨迹稳定。将稳定性判据和约束条件用线性矩阵不等式表示，将镇定问题转化为一个优化问题。利用Wu和Boyd开发的SDPSOL软件包，我们解决了控制增益和稳定域的优化问题，完成了控制器的设计。
Abstract : In this report, we present preliminary results on the design of the baseline controller for an F-16 aircraft automatic landing system using linear matrix inequalities (LMI)-based approaches. We start with a general study of aircraft control and dynamics to gain knowledge of the structure of an aircraft dynamic model and its inner loop control system. We then identify a linear model along the glide path for the inner loop control system in the simulator. With this linear model, the control objective is to solve a stabilization problem-stabilizing the aircraft along the glide path using linear state feedback controls. Expressing the stability criterion and the constraints in LMIs, we cast the stabilization problem as an optimization problem. Using the SDPSOL software package developed by Wu and Boyd, we solve this optimization problem for the control gain and stability region, which completes the controller design.