Seven different nonlinear control laws for multiaxis control of a high-perf
ormance aircraft are compared in simulation. The control law approaches are
fuzzy logic control, backstepping adaptive control, neural network augment
ed control, variable structure control, and indirect adaptive versions of m
odel predictive control and dynamic inversion,In addition, a more conventio
nal scheduled dynamic inversion control la,v is used as a baseline. In some
of the cases, a stochastic genetic algorithm was used to optimize fixed pa
rameters during design. The control laws are demonstrated on a six-degree-o
f-freedom simulation with nonlinear aerodynamic and engine models, actuator
models with position and rate saturations, and turbulence. Simulation resu
lts include a variety of single- and multiple-axis maneuvers in normal oper
ation and with failures or damage, The specific failure and damage cases th
at are examined include single and multiple lost surfaces, actuator hardove
rs, and an oscillating stabilator case. There are also substantial differen
ces between the control law design and simulation models, which are used to
demonstrate some robustness aspects of the different control laws.