Please use this identifier to cite or link to this item: https://doi.org/10.1109/CDC.2007.4434065
Title: Design of H∞ command and control loops for unmanned aerial vehicles using static output-feedback
Authors: Gadewadikar, J.
Lewis, F.
Subbarao, K.
Chen, B.M. 
Issue Date: 2007
Source: Gadewadikar, J.,Lewis, F.,Subbarao, K.,Chen, B.M. (2007). Design of H∞ command and control loops for unmanned aerial vehicles using static output-feedback. Proceedings of the IEEE Conference on Decision and Control : 5395-5400. ScholarBank@NUS Repository. https://doi.org/10.1109/CDC.2007.4434065
Abstract: The aim of this paper is to design a helicopter position control system with guaranteed performance that allows tracking control of Unmanned Aerial Vehicle positions -X, Y, Z, and yaw while preserving a structure that is generally accepted in the helicopter control community. The paper presents an approach for designing compensators for shaping the closed-loop inertial positions and yaw step response using H∞ output-feedback design techniques. Simplified conditions are used which only require the solution of two coupled matrix design equations. H∞ framework is utilized to pose the problem of stabilization as an outer position command loop and an inner control loop. Inner loop controls attitude rates along with roll and pitch and provides robustness and structure. This paper thereby presents a design for hover and station-keeping control of UAV helicopters. It is shown that the rotorcraft model can be first loop shaped to achieve desired characteristics about the hover operating condition. A numerically efficient solution algorithm to solve the H∞ coupled design equations for both inner and outer loops is used. A major contribution is that an initial stabilizing gain is not needed. The efficacy of the control law and the disturbance accommodation properties are shown on a rotorcraft design example. © 2007 IEEE.
Source Title: Proceedings of the IEEE Conference on Decision and Control
URI: http://scholarbank.nus.edu.sg/handle/10635/83613
ISBN: 1424414989
ISSN: 01912216
DOI: 10.1109/CDC.2007.4434065
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