DocumentCode :
861822
Title :
Nonlinear adaptive and sliding mode flight path control of F/A-18 model
Author :
Singh, Sahjendra N. ; Steinberg, Marc L. ; Page, Anthony B.
Author_Institution :
Dept. of Electr. & Comput. Eng., Nevada Univ., Las Vegas, NV, USA
Volume :
39
Issue :
4
fYear :
2003
Firstpage :
1250
Lastpage :
1262
Abstract :
The question of inertial trajectory control of aircraft in the three-dimensional space is discussed. It is assumed that the nonlinear aircraft model has uncertain aerodynamic derivatives. The control system is decomposed into a variable structure outer loop and an adaptive inner loop. The outer-loop feedback control system accomplishes (x,y,z) position trajectory and sideslip angle control using the derivative of thrust and three angular velocity components (p,q,r) as virtual control inputs. Then an adaptive inner feedback loop is designed, which produces the desired angular rotations of aircraft using aileron, elevator, and rudder control surfaces to complete the maneuver. Simplification in the inner-loop design is obtained based on a two-time scale (singular perturbation) design approach by ignoring the derivative of the virtual angular velocity vector, which is a function of slow variables. These results are applied to a simplified F/A-18 model. Simulation results are presented which show that in the closed-loop system asymptotic trajectory control is accomplished in spite of uncertainties in the model at different flight conditions.
Keywords :
adaptive control; aircraft control; nonlinear control systems; position control; singularly perturbed systems; variable structure systems; F/A-18 model; adaptive inner loop; angular rotation; asymptotic trajectory control; feedback loop; inertial trajectory control; nonlinear adaptive flight path control; nonlinear aircraft model; position trajectory; sideslip angle control; singular perturbation; sliding mode flight path control; variable structure outer loop; virtual angular velocity vector; Adaptive control; Aerodynamics; Aerospace control; Aircraft; Angular velocity; Angular velocity control; Control systems; Feedback control; Programmable control; Sliding mode control;
fLanguage :
English
Journal_Title :
Aerospace and Electronic Systems, IEEE Transactions on
Publisher :
ieee
ISSN :
0018-9251
Type :
jour
DOI :
10.1109/TAES.2003.1261125
Filename :
1261125
Link To Document :
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