A novel nonlinear control law for the purpose of lateral control of a missile is presented in this paper. This approach can be applied to generate lateral control commands for a missile operating in flight regimes where the effectiveness of conventional aerodynamic surfaces is reduced (i.e. high angle of attack). The design objective is to specify one control law that satisfies the H2 performance for the nonlinear attitude tracking design of missiles. In general, it is hard to obtain the closed-form solutions from this nonlinear attitude tracking problem. Fortunately, because of the adequate choice of state variable transformation, the nonlinear H2 attitude tracking problem of the missile can be reduced to solving one nonlinear time varying Riccati-like equation. Furthermore, one closed-form solution to this equation can be obtained in a very simple form for the preceding control design.
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering