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Modelling Continuously Morphing Aircraft for Flight Control

机译:为飞行控制连续变形飞机建模

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The goal of the present work is to develop a small-scale flying wing with active winglets from a discrete surfaces concept, actuated via single torque actuators, to a seamless continuous concept actuated via a distribution of actuators. A conceptual approach will allow the tailoring of the main parameters influencing the flexibility of the structures, via an efficient optimisation routine based on a certain actuation power requirement. The efficiency is guaranteed by the implementation of equivalent continuum models for the structure rather than a discrete finite element approach, while the aerodynamic loads are provided by the implementation of a vortex lattice code. The actuation can be provided either by piezo or thermo strain actuators. The paper describes the tools based on a static aeroelastic code which predicts the interaction of the actuated morphing wing and the flow field, and shows results from preliminary analysis.
机译:本发明的目的是将具有主动小翼的小型飞行机翼从通过单个扭矩致动器致动的离散表面概念发展到通过致动器分布致动的无缝连续概念。一种概念性的方法将允许通过基于某个驱动功率需求的高效优化例程来定制影响结构灵活性的主要参数。效率是通过为结构实现等效的连续模型而不是离散的有限元方法来保证的,而空气动力学载荷是由涡流格子代码的实现提供的。可以通过压电或热应变致动器来提供致动。本文介绍了基于静态气动弹性代码的工具,这些代码可预测变形机翼与流场的相互作用,并显示初步分析的结果。

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