Structured robust control-loop design with input saturations for tandem ducted fan vehicle

2015 ◽  
Author(s):  
Changle Xiang ◽  
Yang Wang ◽  
Yue Ma ◽  
Bin Xu
Keyword(s):  
Robust Control ◽  
Control Loop ◽  
Loop Design ◽  
Ducted Fan

Variable DC-Link Control Loop Design for an Integrated Two-Stage AC/DC Converter

2018 ◽  
Vol 4 (1) ◽  
pp. 99-107 ◽  
Author(s):  
Jiangheng Lu ◽  
Ayan Mallik ◽  
Shenli Zou ◽  
Alireza Khaligh
Keyword(s):  
Control Loop ◽  
Two Stage ◽  
Loop Design

Feedback control loop design for workload change detection in self-tuning NoSQL wide column stores

2020 ◽  
Vol 142 ◽  
pp. 112973 ◽  
Author(s):  
Maryam Mozaffari ◽  
Eslam Nazemi ◽  
Amir Masoud Eftekhari-Moghadam
Keyword(s):  
Feedback Control ◽  
Change Detection ◽  
Control Loop ◽  
Loop Design ◽  
Self Tuning ◽  
Column Stores

scholarly journals Level control loop design for a test-rig flotation column

2019 ◽  
Vol 1219 ◽  
pp. 012014
Author(s):  
J Piñeres ◽  
M. Mendoza ◽  
M Tellez ◽  
F Jiménez
Keyword(s):  
Control Loop ◽  
Level Control ◽  
Test Rig ◽  
Flotation Column ◽  
Loop Design

Full Flight Envelope Transient Main Control Loop Design Based on LMI Optimization

2020 ◽  
Author(s):  
Keqiang Miao ◽  
Xi Wang ◽  
Meiyin Zhu
Keyword(s):  
Robust Stability ◽  
Design Method ◽  
Settling Time ◽  
Pole Placement ◽  
Linear Matrix ◽  
Control Loop ◽  
Turbofan Engine ◽  
Loop Design ◽  
Gain Schedule ◽  
Flight Envelope

Abstract To solve the problem of full flight envelope transient main control loop design of turbofan engine, a design method based on linear matrix inequality (LMI) is proposed. Robust stability of the closed-loop turbofan engine system in all conditions is proved by using Lyapunov inequalities. The robust performance is ensured by gain-schedule and pole-placement. Reduced order multivariable gain-schedule and minimum trace optimization algorithm are presented to guarantee the feasibility of the design method. Full flight envelope simulations based on a nonlinear turbofan engine model were done. The results show that the maximum settling time of N1cor is 4.3s and the maximum overshoot is 1.7%. The maximum settling time of N2cor is 4.5s and the maximum overshoot is 0.1%. The robust stability and consistent performance in full flight envelope are also shown in the results.

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