首页> 外文期刊>The Aeronautical Journal >A hybrid fuzzy logic proportional- integral-derivative and conventional on-off controller for morphing wing actuation using shape memory alloy Part 1: Morphing system mechanisms and controller architecture design
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A hybrid fuzzy logic proportional- integral-derivative and conventional on-off controller for morphing wing actuation using shape memory alloy Part 1: Morphing system mechanisms and controller architecture design

机译:使用形状记忆合金对机翼致动进行变形的混合模糊逻辑比例积分微分和常规开关控制器第1部分:变形系统机制和控制器架构设计

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The present paper describes the design of a hybrid actuation control concept, a fuzzy logic proportional-integral-derivative plus a conventional on-off controller, for a new morphing mechanism using smart materials as actuators, which were made from shape memory alloys (SMA). The research work described here was developed for the open loop phase of a morphing wing system, whose primary goal was to reduce the wing drag by delaying the transition (from laminar to fully turbulent flows) position toward the wing trailing edge. The designed controller drives the actuation system equipped with SMA actuators to modify the flexible upper wing skin surface. The designed controller was also included, as an internal loop, in the closed loop architecture of the morphing wing system, based on the pressure information received from the flexible skin mounted pressure sensors and on the estimation of the transition location. The controller's purposes were established following a comprehensive presentation of the morphing wing system architecture and requirements. The strong nonlinearities of the SMA actuators' characteristics and the system requirements led to the choice of a hybrid controller architecture as a combination of a bi-positional on-off controller and a fuzzy logic controller (FLC). In the chosen architecture, the controller would behave as a switch between the SMA cooling and heating phases, situations where the output current is OA or is controlled by the FLC. In the design phase, a proportional-integral-derivative scheme was chosen for the FLC. The input-output mapping of the fuzzy model was designed, taking account of the system's error and its change in error, and a final architecture for the hybrid controller was obtained. The shapes chosen for the inputs' membership functions were s-function, π-function, and z-function, and product fuzzy inference and the center average defuzzifier were applied (Sugeno).
机译:本文描述了一种混合驱动控制概念的设计,模糊逻辑比例积分微分加常规开关控制器的设计,该结构适用于使用形状记忆合金(SMA)制成的,以智能材料为执行器的新型变形机制。 。此处描述的研究工作是针对变形机翼系统的开环阶段开发的,其主要目标是通过延迟向机翼后缘的过渡(从层流到完全湍流)位置来减少机翼阻力。设计的控制器驱动配备有SMA执行器的执行系统,以修改柔性上翼蒙皮表面。基于从柔性蒙皮安装的压力传感器接收的压力信息和过渡位置的估计,设计的控制器也作为内部回路包含在变形机翼系统的闭环体系结构中。在全面介绍了变形机翼系统的体系结构和要求之后,确定了管制员的目的。 SMA执行器特性和系统要求具有很强的非线性特性,因此选择了混合控制器架构,将双向开关控制器和模糊逻辑控制器(FLC)结合在一起使用。在所选架构中,控制器将充当SMA冷却阶段和加热阶段之间的切换,此时输出电流为OA或由FLC控制。在设计阶段,为FLC选择了比例积分微分方案。设计了模糊模型的输入输出映射,并考虑了系统的误差及其误差变化,得到了混合控制器的最终架构。为输入的隶属度函数选择的形状是s函数,π函数和z函数,并且应用了乘积模糊推理和中心平均去模糊器(Sugeno)。

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