Partial Integrated Guidance and Control for Missiles with Three-Dimensional Impact Angle Constraints

摘要

A partial integrated guidance and control design for an interception with terminal impact angle constraints in three-dimensional space is presented in this paper. A three-dimensional nonlinear engagement dynamic is considered here and full nonlinear six-degrees-of-freedom model of the interceptor with aerodynamic uncertainties has been accounted for. The partial integrated guidance and control design contains a two-loop controller structure. The outer loop, which generates directly the commanded body rates, is constructed, and then the inner loop is designed to track the outer loop commands. The main feature of the partial integrated guidance and control design is that it accurately satisfies terminal impact angle constraints in both azimuth and elevation, in addition to being capable of hitting the target with high accuracy. Moreover, the aerodynamic uncertainties and the target acceleration, which are assumed to be bounded, are considered by virtue of the proposed adaptive multiple input multiple output sliding mode control method. The performance of the proposed scheme is investigated using nonlinear simulation studies. A comparison among the proposed partial integrated guidance and control method, the conventional method where the guidance and control loops are designed separately, and the integrated guidance and control method executed in a single loop is presented to show the effectiveness of the proposed partial integrated guidance and control scheme. Finally, a Monte Carlo study is conducted to test the robustness to aerodynamic uncertainties.