Robust control and limit protection in aircraft gas turbine engines
Robust control and limit protection in aircraft gas turbine engines
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DOI：
10.1109/cca.2012.6402640
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发表时间：
2012-10
期刊：
影响因子：
--
通讯作者：
I. Kolmanovsky;L. Jaw;W. Merrill;H. Van
中科院分区：
文献类型：
--
作者：
I. Kolmanovsky;L. Jaw;W. Merrill;H. Van
不确定性，特别是大的进气扭曲，会影响飞机燃气轮机的闭环系统稳定性和性能，并侵蚀喘振裕度。传统的鲁棒控制技术可以与鲁棒参考调节器相结合，以保持稳定性和跟踪性能，同时执行浪涌裕度限制。文中讨论了不确定性建模、进气失真对发动机性能的影响以及控制器结构的选择，并说明了鲁棒参考调节器和H_无穷控制器的组合应用。我们的结果表明，反馈回路的稳定性和跟踪性能可以通过鲁棒控制技术来保持，因此约束处理(极限保护)是处理入口失真影响的主要目标。
Uncertainties and, in particular, large inlet distortions, affect closed-loop stability, performance, and erode surge margins of aircraft gas turbine engines. Traditional robust control techniques can be combined with robust reference governors to preserve the stability and tracking performance, while enforcing the surge margin constraints. The paper examines uncertainty modeling, the effect of inlet distortions on engine performance, and on controller architecture selection; it also illustrates the combined application of robust reference governor and H-infinity controller. Our results suggest that stability and tracking performance of the feedback loop can be maintained with robust control techniques, hence constraint handling (limit protection) represents the primary goal in dealing with the effect of inlet distortions.