Design of a Smart Morphing Wing Using Integrated and Distributed Trailing Edge Camber Morphing

Abstract

In this study, the design and development of an autonomous morphing wing concept were investigated. This morphing wing was developed in the scope of, the Smart-X project, aiming to demonstrate in-flight performance optimisation. This study proposed a novel distributed morphing concept, with six Translation Induced Camber (TRIC) morphing trailing edge modules, inter-connected triangular skin segments joined by an elastomer material to allow seamless variation of local lift distribution along the wingspan. An FSI structural optimisation tool was developed, to achieve this optimised design, and to produce an optimal laminate design of fibre Glass weave material, capable of reaching target shapes and minimise actuation loads. Analysis of the kinematic model of the embedded actuator was performed, and a conventional actuator design was selected to continuously operate at the required load and fulfil both static and dynamic requirements in terms of bandwidth, actuation force and stroke. Preparations were made in this study for the next stage of the Smart-X design, to refine the morphing mechanism design and build a functional demonstrator for wind tunnel testing.

Design and Development of a Seamless Smart Morphing Wing Using Distributed Trailing Edge Camber Morphing for Active Control

“…The design of the morphing wing was obtained using an FSI framework, which couples a Finite Element Model (FEM) and an inviscid low-cost aerodynamic model of the morphing system [16].…”

“…The design approach can be summarized in the following steps/elements [16]: 1) Development of an FSI tool and an optimisation routine incorporating the FSI loop, allowing laminate design optimisation by varying the ply thickness to ensure target shapes at minimal input force. 2) Development of easy to manufacture laminate meeting the actuator loads and actuator travel range 3) Selection of the actuator and actuator mechanism.…”

“…Suitable convergence bounds were determined for the deformation error, actuation load and the lift coe cient increment, by performing a convergence study. Convergence of these variables typically reached in three-four iterations [16]. The inviscid aerodynamic model allowed analysis of angle of attack between -12 and 5 degrees for the given NACA 6510 baseline airfoil shape.…”

Adaptive State Estimation and Real-Time tracking of Aeroelastic Wings with Augmented Kalman filter and Kernelized Correlation Filter

“…Fig. 12a shows the full range of frequencies (1)(2)(3)(4)(5). This shift in response type appears to happen between the 3Hz (yellow) and 4 Hz (red) lines.…”

“…In particular, fuselage-mounted camera systems can provide significant advantages for flexible aircraft systems, save costs associated with installation, certification, and have the potential of being non-invasive and universally applicable. This type of smart sensing system is also of particular importance for over-actuated and over-sensored morphing designs such as the SmartX [5]. Furthermore, image data is a rich source of information; collected over a period of time, it unlocks the opportunity to approach the state estimation from a new perspective using machine learning methods.…”