A flight controller using adaptive parameter approximation block backstepping is designed for a winged missile with unknown aerodynamic parameters. The assumptions for the controller design are analyzed. Moreover, some less stringent assumptions about commands and input matrixes are given. The unknown parameter matrixes, which are formed from the unknown aerodynamic parameters in the missile dynamic model, are estimated by an adaptive parameter approximation method. This method is less complex and easier to implement than neural network approximation. The filters are introduced into the process of controller design, which are used to overcome the "term explosion" problem caused by differentiations of the virtual control law and to reduce the restrictions of commands. The closed-loop system is proved to be stable and converge exponentially through the analysis of tracking errors dynamic and Lyapunov stability. Furthermore,a nonlinear six degree-of-freedom (DOF) flight is simulated on the winged missile model, and the results demonstrate good tracking performance and robustness of the designed flight controller.
CAO Lijia, ZHANG Shengxiu, LIU Yi'nan, LIU Ying, ZHANG Ying
. Flight Controller Design Using Adaptive Parameter Approximation Block Backstepping[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(12)
: 2259
-2267
.
DOI: CNKI:11-1929/V.20111018.1013.001
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