Guidance and Control Development of the Multimode Airframe Technology (MAT) Missile

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Guidance and Control Development of the Multimode Airframe Technology (MAT) Missile

J. L. Walls

This paper overviews development of the guidance and control system design of the Multimode Airframe Technology (MAT) missile being developed at the Missile Research, Development, and Engineering Center, U.S. Army AMCOM. The teleoperated missile accomplishes high speed flyout, slowdown for target search using a variable wing/flap configuration, and provides high speed precision targeting at terminal attack. The control system's objective is to achieve these flight regimes and overall mission objectives. A high fidelity Six degree of freedom (6DOF) simulation of the missile system was likewise developed that serves as a development and testing environment. Simulation results are given to show the performance of the closed loop system. Confidence in the modeling efforts was obtained through testing of each subsystem and comparing with the six DOF simulation. The MAT missile simulation results show that the guidance and autopilot functions are achieved with respect to the mission requirements.