Use this URL to cite or link to this record in EThOS: http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.690034
Title: Development, integration and testing of a 0-v honeycomb structure for aircraft morphing
Author: Dove-Jay, Ashley
Awarding Body: University of Bristol
Current Institution: University of Bristol
Date of Award: 2015
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Abstract:
This thesis lays out the development, analysis, integration and testing of a camber morphing concept for control surfaces dealing with fluidic dynamics, with specific focus on replacing the outboard aileron of fixed-wing aircraft in an effort to increase associated fuel efficiency. Core to the development of the morphing concept was a zero Poisson's ratio (O-v) honeycomb. The state-of-the-art was studied, modified for compatibility with the application intended, was subjected to topological optimization to improve relevant performance charactelistics, and was validated through experimental studies. Mass was reduced by 20% and energy for morphing by 42-55% without affecting load-carrying capability; but fatigue life was reduced by 18%. A near-term performance study was conducted. The outboard aileron of a state-of-the-art A320 wing was replaced with the morphing equivalent, demonstrating higher efficiency and increasing aircraft range by 0.8-0.9% depending on weather conditions in a medium fidelity flight simulation (Heathrow to Amsterdam). A first-iteration long-term study, unrestricted by current design constraints, indicated a significant increase in aerodynamic efficiency; towards 50% for high control surface deflections. Coupled to a pre-stressed hyper-elastic surface skin and an an-ay of micro-linear actuators for morphing, the O-u honeycomb was integrated into a 1.05m span wing for wind-tunnel testing. The generated morphed shapes successfully met the overarching geometric objectives; significant reduction in chordwise and spanwise geometric discontinuities and pressure gradients. Comparison between FE and hammer-testing showed modal frequencies agreed with an average en-or of 8%. Comparison between CFD and wind-tunnel studies showed CL agreement with an average error of 0.07 CL. A methodology for whole wing conformal shape optimisation, based on modified Class Shape Transformations and Bemstein Polynomials, enabled by integration of the O-u honeycomb structure generated coupled to cellular micro-linear actuators, was developed and proposed as a logical step forward to explore the full potential of the morphing system proposed.
Supervisor: Not available Sponsor: Not available
Qualification Name: Thesis (Ph.D.) Qualification Level: Doctoral
EThOS ID: uk.bl.ethos.690034  DOI: Not available
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