An 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.
Multivariable flight control synthesis and literal robustness analysis for an aeroelastic vehicle
AIAA Guidance, Navigation and Control Conference ; 1990 ; Portland, OR, United States
1990-01-01
Conference paper
No indication
English
Aeroelastic Vehicle Multivariable Control Synthesis with Analytical Robustness Evaluation
Online Contents | 1994
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