The Terminal Guidance And Control Of Anti-TBM Missile

The high frequently use of tactical ballistic missile (TBM) makes the research of anti-TBM missile very urgently. This paper mainly studies the terminal guidance scheme and control of anti-TBM missile in atmosphere such as PAC-3.Most TBM use maneuver as the primary means to break through defence in atmosphere. This paper designed a spiral maneuvering reentry trajectory as the target of anti-TBM missile, which changes the magnitude and direction of the maneuver periodically. The simulation shows that the penetration capacity of the spiral maneuvering reentry target is better than that of inertia reentry target. Intercepting highly maneuverable TBM put forward new problems in the design of guidance law, especially as the terminal guidance scheme influence the shoot precision of the missile crucially. This paper put forward a variable structure terminal guidance that can be used in engineering and has a good performance in intercepting highly maneuverable target.To improve the efficiency of the implement of control and guide dictate, this paper designs a switching curve laws for steering control engines. It can restrict the turn rate of sight line in the process of approaching the target in a small range, and the breadth of the turn rate of sight line decreases as the distance diminishes.Based on the deploy of steering control engines of the anti-TBM missile such as PAC-3, at the end of flight trajectory when approaching the target, the missile studied in this paper uses the combination of thrust vector to provide large fast respond lateral force, and adjusts the engine thrust to provide precise terminal revise. The Simulation shows that while the missile rotates slowly, the combination of thrust vector will improve the lateral maneuverability greatly, the adjusting thrust works in revising maneuver, the turn rate of sight line is limited in a small range, and the miss distance of interception is diminished.