This paper examines the use of a nonlinear adaptive control law for multi-axis control of a high-performance aircraft with stabilator, aileron and rudder failures. The control law is based on a backstepping design approach with fixed parameter optimization done using a stochastic genetic algorithm. The control law is demonstrated on a six-degree-of-freedom simulation with nonlinear aerodynamic and engine models, actuator models with saturation, and turbulence. There are substantial differences between the control law design and simulation models, which are used to demonstrate some robustness aspects of this control law. To deal with actuator saturation, the Lyapunov function is modified so that the growth of integrated error and the rate of change of parameter growth are both reduced when the surface commands are growing at a rate that will likely saturate the actuators. Published in 1999 by John Wiley & Sons, Ltd. This article is a US Government work and is in the public domain in the United States.
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