Design and implementation of FPGA-based integrated missile actuation system and control synthesis

The missile's overall accuracy and autonomy are potentially affected by its actuation system and controller design. The current paper presents an integrated missile's actuation system design process in the presence of different mechanical and electrical constraints, a reliable electric actuation system (EAS) and its related control system are developed based on missile mechanical and electrical requirements. A real-time motion simulation is performed using solid work software to guarantee compatibility with the actual size, weight, and load constraints. The actuation system model is performed using a system identification technique based on real-time input-output data extraction utilising a predesigned test and control setup. A real-time floating-point PID controller based on the genetic algorithm optimisation approach is designed using MATLAB, simulated using hardware simulation utilising Modalism software, and then implemented by an embedded FPGA-based board. The novelty of this paper is the design, control, and implementation of a real-time embedded aerodynamic missile actuation system based on aerodynamic fin loading exerted in missile control surfaces. Hardware in the loop simulation is carried out with a simulated missile trajectory which presents the proposed actuation system performance, robustness, and reliability achieved through highly professional design and implementation steps and results.