AbstractThis paper considers the application of compound control method to high-performance autopilot design for aerodynamically controlled agile missiles. The control objective in this paper is to track a reference angle of attack command signal in the presence of external disturbance and aerodynamic coefficient uncertainty with desired performance. The external disturbances and the aerodynamic uncertain terms are first lumped together as the lumped uncertainties, which can be estimated accurately by the introduced extended state observer (ESO). Combining the sliding mode control (SMC) and backstepping techniques, a robust nonsmooth (but continuous) compound control law is developed for angle of attack tracking. With the aid of Lyapunov stability criteria, it is proven that the angle of attack tracking error will converge into a small neighborhood around the origin in finite time. Theoretical analysis and simulation results demonstrate the robustness and effectiveness of the proposed composite method.
Compound Control Methodology for a Robust Missile Autopilot Design
Journal of aerospace engineering ; 28 , 6
2015
Article (Journal)
English
Robust Nonlinear Missile Autopilot Design
British Library Conference Proceedings | 1995
|Missile autopilot design using robust eigenvalue assignment
TIBKAT | 1992
|Robust autopilot design for future missile systems
AIAA | 1997
|Parametric Uncertainty Reduction in Robust Missile Autopilot Design
Online Contents | 1996
|