Multivariable flight control synthesis and literal robustness analysis for an aeroelastic vehicleAn integrated flight/aeroelastic control law is developed analytically for a hypothetical large supersonic transport aircraft in which the first aeroelastic mode frequency of the fuselage (6 rad/sec) is near the short-period mode (2 rad/sec). The approach employed is based on a linear-quadratic-regulator (LQR) formulation (yielding model-following state-feedback gains), followed by asymptotic loop-transfer recovery of LQR robustness (to produce an output-feedback control law). The derivation is outlined, and numerical results comparing the performance and multivariate stability robustness of the present controller with those of a classical controller are presented in graphs. The two controllers are shown to have similar characteristics, even with respect to the sources of limitations on robustness.
Document ID
19900060644
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schmidt, David K. (Arizona State Univ. Tempe, AZ, United States)
Newman, Brett (Arizona State University Tempe, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Cybernetics
Report/Patent Number
AIAA PAPER 90-3446
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference