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首页> 外文期刊>ScientificWorldJournal >Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications
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Modeling and Simulation of Control Actuation System with Fuzzy-PID Logic Controlled Brushless Motor Drives for Missiles Glider Applications

机译：用于导弹滑翔机应用的模糊PID逻辑控制无刷电动机控制驱动系统的建模与仿真

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A control actuation system has been used extensively in automotive, aerospace, and defense applications. The major challenges in modeling control actuation system are rise time, maximum peak to peak overshoot, and response to nonlinear system with percentage error. This paper addresses the challenges in modeling and real time implementation of control actuation system for missiles glider applications. As an alternative fuzzy-PID controller is proposed in BLDC motor drive followed by linkage mechanism to actuate fins in missiles and gliders. The proposed system will realize better rise time and less overshoot while operating in extreme nonlinear dynamic system conditions. A mathematical model of BLDC motor is derived in state space form. The complete control actuation system is modeled in MATLAB/Simulink environment and verified by performing simulation studies. A real time prototype of the control actuation is developed with dSPACE-1104 hardware controller and a detailed analysis is carried out to confirm the viability of the proposed system.
机译：控制致动系统已广泛用于汽车，航空航天和防御应用。建模控制驱动系统中的主要挑战是上升时间，最大峰值峰值过冲，以及响应非线性系统的误差。本文涉及导弹滑翔机应用控制驱动系统的建模和实时实施的挑战。作为在BLDC电动机驱动中提出的替代模糊PID控制器，然后用连杆机构在导弹和滑翔机中致动翅片。在以极端非线性动态系统条件下运行，所提出的系统将实现更好的上升时间和更少的过冲。 BLDC电动机的数学模型以状态空间形式导出。完整的控制驱动系统在Matlab / Simulink环境中建模，并通过执行模拟研究来验证。控制致动的实时原型与DSPace-1104硬件控制器开发，并进行了详细的分析以确认所提出的系统的可行性。

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