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首页> 外文期刊>The Aeronautical Journal >A linear guide-based actuation concept for a novel morphing aileron
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A linear guide-based actuation concept for a novel morphing aileron

机译：新型变形副翼的基于线性导向的致动概念

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This paper deals with the actuation system design of a full-scale morphing aileron for regional aircraft. The aileron is allowed to smoothly change its geometrical configuration and perform the in-flight transition from a baseline shape to a set of optimal morphed ones pre-defined on the basis of aerodynamic requirements. The design of such innovative aileron is aimed not only at substituting the conventional aileron installed on a real aircraft but also to provide additional functionality. The aileron is free to rotate around its main hinge axis and it is also allowed to smoothly modify camber with two independent actuation systems. In such manner it can be used also during cruise with a symmetric deflection between the two half wings in order to reduce drag in off design condition. To accomplish variable aileron shape, a rigid-body mechanism was designed. The proposed aileron architecture is characterised by segmented adaptive ribs rigidly linked each other with spanwise reinforcements such as spars and stringers in a multi-box arrangement. Each rib is split into two movable plates connected by means of rotational hinges in a finger-like mechanism. The mechanism is driven by a load-bearing actuator by means of a kinematic chain opportunely tied based on the structural requirements in terms of shape to be matched and load to be withstood. The proposed device is an innovative arrangement of the quick-return mechanism composed of a beam leverage, commercial linear guides and a crank. The actuator shaft is directly inserted in the crank, which transmits the rotation to the linear guide that slide along a rail moving upward or downward the beam thus resulting in a camber variation. The entire aileron is moved by three leverages internally contained and distributed along the first two bays while the most external ribs are considered passive and their movement slaved. Two actuation layouts are analytically and numerically studied, the analytical theory is presented and validated by means of a multi-body simulation. Moreover, a linear static analysis was carried out under the hypothesis of glued contact between linear guides components simulating a jamming condition. This assumption has been formulated because it represents the most severe condition that envelop all the operative loads to which the actuation system is subjected. The analyses conducted are preliminarily aimed to verify that no failure occur under the imposed loads. In this first design loop, the vertical static force acting on the linear carriage exceeded allowable value and then a new configuration with double-sided linear guides was then investigated.
机译：本文研究了支线飞机全尺寸变形副翼的致动系统设计。允许副翼平稳地改变其几何形状，并在飞行中从基线形状过渡到根据空气动力学要求预先定义的一组最佳变形飞机。这种创新的副翼的设计不仅旨在代替安装在真实飞机上的常规副翼，而且还提供其他功能。副翼可以绕其主铰链轴自由旋转，并且还可以通过两个独立的致动系统平稳地改变外倾角。以这种方式，它也可以在巡航期间以两个半翼之间的对称偏斜使用，以减少偏离设计状态的阻力。为了实现副翼的可变形状，设计了一种刚体机构。所提出的副翼结构的特征在于，在多箱布置中，分段的自适应肋与翼展方向的加强件（例如，翼梁和纵梁）彼此刚性连接。每个肋条被分成两个活动板，活动板通过指状机构中的旋转铰链连接。该机构由一个负载致动器通过一条运动链条来驱动，该运动链条根据结构要求在要匹配的形状和要承受的载荷方面根据结构要求进行了适当的系紧。拟议中的设备是一种快速返回机构的创新装置，该机构由光束杠杆，商用线性导轨和曲柄组成。致动器轴直接插入曲柄中，该曲柄将旋转传递到线性导轨，线性导轨沿着使光束向上或向下移动的导轨滑动，从而导致外倾角变化。整个副翼沿前两个舱室通过内部控制和分布的三个杠杆运动，而最外部的肋被认为是被动的，其运动是从动的。对两种致动布局进行了分析和数值研究，并通过多体仿真对解析理论进行了介绍和验证。此外，在线性导轨组件之间模拟接触条件的粘接接触的假设下进行了线性静态分析。之所以制定这一假设，是因为它代表了最严酷的条件，包围了致动系统所承受的所有操作负载。进行的分析旨在初步验证在施加的载荷下是否不会发生故障。在第一个设计循环中，作用在线性滑架上的垂直静力超过了允许值，然后研究了带有双面线性导轨的新配置。

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