Nonlinear fuzzy H/sub ∞/ guidance law with saturation of actuators against maneuvering targets

Abstract

A nonlinear guidance law based on a fuzzy model is proposed for tactical missiles pursuing maneuvering targets in three-dimensional (3-D) space. In the proposed guidance scheme, the relative motion equations between the missile and target are first interpolated piecewise by Takagi-Sugeno linear fuzzy models. Then, a nonlinear fuzzy guidance law is designed to eliminate the effects of approximation error and external disturbances to achieve the desired goal. The linear matrix inequality (LMI) technique is then employed to treat this optimal guidance design in consideration of control constraints. Finally, the problem is further transformed into a standard eigenvalue problem so that it can be efficiently solved via a convex optimization algorithm, which is available from a numerical computation software.

Comparative Account of Robust H∞ Techniques for Missile Autopilot Design

“…Chen et. al in the year 2002 exploited the linear matrix inequality (LMI) technique to implement the H∞ guidance design considering control constraints [14] . Lim et.al in the year 2003 applied the gain scheduled autopilot for missile applications [15] .…”

Backstepping‐based zero‐sum differential games for missile‐target interception systems with input and output constraints

“…Since the differential game is a mathematical tool for dealing with the problems of continuous dynamic conflict, competition or cooperation with two or more control actions, differential game guidance methods have been paying much attention by researchers [5][6][7][8][9]. In [6], the missile-aircraft differential game was studied, in which a family of local solutions rather than a unique solution was found by introducing the concept of energy manoeuvrability.…”

Design of a robust guidance law via active disturbance rejection control

“…Guidance laws have been extended to the three-dimensional engagement case for highly maneuverable targets [2] and have been applied to missile systems considering the induced drag and the internal dynamics of the control loop [3]. New guidance laws using nonlinear control theories such as the Lyapunov function method [4], the optimal control theory [5], the nonlinear H ∞ control theory [6][7], and the adaptive sliding-mode control theory [8][9][10][11] have also been developed. As to the robustness in missile guidance law design, the guidance law proposed in [12] and [13] took into account the lag of the autopilot.…”