Search

To achieve the tactics mission of cooperative attack at the fixed impact time, for multiple route planning anti-ship missiles, a dynamic route planning algorithm with impact time control is proposed. First, a recursive route planning algorithm is designed to choose navigation points and come to a reference route. Then, in order to control the impact time, the reference route is re-planned on line according to the error time between the fixed impact time and the estimated time to go. If the error time is positive, the reference route from the current navigation point to the next one is extended by maneuvering fly; if the error time is negative, the reference route is shorten by adjusting the location of navigation point. The realization of controlling the impact time is transferred to dynamically increase or decrease distance of the reference route. The simulation results show the validity and effectiveness of the proposed algorithm.

In order to achieve the tactical mission of cooperative attack for multi-missiles, in a predetermined direction at a predetermined time, this paper studies the design of guidance law with impact angle and impact time constraints. Firstly, using the optimal control theory, the optimal guidance law is designed to control the impact angle, based the relative motion between missile and target. Then the state feedback guidance law is designed to control the arrival impact time, with the application of feedback linearization control theory. Finally, reference the design idea of two-stage guidance system, the anti-ship missile use two different guidance laws in the process of attacking the target. During the first stage, the state feedback guidance law is used to accurately control the impact time and coarsely control the impact angle. During the second stage, the optimal guidance law is used to accurately control the impact angle. And the correctness and effectiveness of the design method is verified by simulation.

Adaptive fuzzy sliding mode control strategy for the overload control of anti-ship missiles using Lyapunov's stability theory is proposed. The internal dynamics of the system is stabilized based on the output-redefinition technique firstly, then an adaptive controller is adopted to attenuate the unknown parameters and uncertainties; and a sliding mode controller is applied to guarantee the robustness of the system. Because the switching term in the sliding mode control can cause the chattering phenomenon, a fuzzy controller is adopted to adjust it. The three controllers compose the integrated controller for the uncertain missile system. The simulation shows validity of the proposed method.

In order to achieve the tactical mission of attacking the target on the appointed direction, the characteristics of maneuver target was analyzed, and a variable structure guidance law with constraints on impact angle, based on the 3-D relative motion model of missile and target, was presented in the point of view of engineering application. The guidance law is simple and can be implemented conveniently with little target information. In the guidance law, the distance between missile and target, and their relative velocity, which is difficult to measure, were substituted by estimation values. The estimation errors, the target's velocity, and the target's maneuver acceleration are all treated as bounded disturbance. And all these disturbances can be successfully restrained by choosing the appropriate parameters of guidance law. The performance of the guidance system was analyzed theoretically, and the numerical simulation result shows the validity and effectiveness of the proposed guidance law.