Robustness in linear quadratic feedback design with application to an aircraft control problemSome new results concerning robustness and asymptotic properties of error bounds of a linear quadratic feedback design are applied to an aircraft control problem. An autopilot for the flare control of the Augmentor Wing Jet STOL Research Aircraft (AWJSRA) is designed based on Linear Quadratic (LQ) theory and the results developed in this paper. The variation of the error bounds to changes in the weighting matrices in the LQ design is studied by computer simulations, and appropriate weighting matrices are chosen to obtain a reasonable error bound for variations in the system matrix and at the same time meet the practical constraints for the flare maneuver of the AWJSRA. Results from the computer simulation of a satisfactory autopilot design for the flare control of the AWJSRA are presented.
Document ID
19780034150
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Patel, R. V. (NASA Ames Research Center Moffett Field, CA, United States)
Sridhar, B. (NASA Ames Research Center Moffett Field, CA, United States)
Toda, M. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Aircraft Stability And Control
Meeting Information
Meeting: Annual Asilomar Conference on Circuits, Systems, and Computers