A multi-objective Hinfinity design framewok for helicopter PID control tuning with handling qualities requirements (original) (raw)
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H 1 robust controller for autonomous helicopter hovering control
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Proceedings of the 44th IEEE Conference on Decision and Control, 2005
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International Journal of Applied Engineering Research, 2016
This paper aims to present the design procedure of control loading system (CLS) for military helicopters. The CLS is designed to meet the handling qualities specification known as Aeronautical Design Standard (ADS-33E-PRF). The CLS falls under the irreversible flight control system where the artificial feel system is designed by means of a second-order transfer function. The actuator system is made by means of state-space model which again uses a third-order transfer function. The step response, frequency response analysis and pole-zero map plot are made to verify the stability of the system. For validation purpose, we are comparing the software results with the hardware results. The software design is made by MATLAB/SIMULINK and the hardware CLS is purchased from Brunner’s Elektronik. Here we are concentrating only on the static control checks, longitudinal static stability and directional stability which use CLS to measure its performance. Finally we plot the graphs for force versus position for pitch, roll and yaw by meeting the requirements of ADS-33E-PRF level 1 handling qualities specifications in both hover and low speed.
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IEEE/ASME Transactions on Mechatronics, 2022
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Robust Control for Helicopters Performance Improvement: an LMI Approach
Journal of Aerospace Technology and Management, 2020
This paper presents an LMI (Linear Matrix Inequalities) application for the design of robust controllers for multivariate systems that have multiple points of operation. Some systems change their parameters along time, then, it is necessary to switch the control for different operational points. The purpose of this controller is to ensure the stability and performance requirements of the system for different operating points with the same controller. The method uses the following concepts of predefined structures controller, LMI region, and polytopic systems. To validate the controller a linearized model of a helicopter was used. These helicopters belong to a system class of MIMO (Multiple-Input Multiple Outputs) type and present a complex dynamic in their flight modes, therefore, due to these features, this type of helicopter is a good model to implement and test the efficiency of the described method in this work. The results were satisfactory. Some limitations in its implementati...