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EASA.2009.OP.24 LIBCOS – Significance of Load upon Impact Behaviour of Composite Structure

Toso, Nathalie and Johnson, Alastair (2011) EASA.2009.OP.24 LIBCOS – Significance of Load upon Impact Behaviour of Composite Structure. Project Report. DLR-IB 435-2011/88, 150 S. EASA (European Aviation Safety Agency).

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Official URL: http://easa.europa.eu/safety-and-research/research-projects/large-aeroplanes.php

Abstract

A critical safety issue for the design of primary aircraft structures is vulnerability and damage tolerance due to foreign object impact from bird strike, hail, tyre rubber and metal fragments. The damage tolerance strategy for the aircraft industry is based on defining critical damage states for composites which are linked to damage visibility and hence damage detection during service. Currently impact tests on aircraft structures are carried out on test specimens supported in a test fixture in a stress-free condition. However aircraft fuselage and wing structures in flight are subjected to quasi-static loads up to design limit load, hence foreign object impacts usually occur on preloaded structures which may influence damage tolerance. This study commissioned by EASA under the project name LIBCOS focuses on a comprehensive test programme investigating the influence of pre-loads on the residual strength of composite generic panels after impact, representative of fuselage bay panels. To that aim, a total of 78 tests have been conducted: 57 on composite plates and 21 on aluminium plates for comparison. The test programme used representative composite fuselage bay panels situated between frames and stringers. Material selected is an aerospace UD carbon epoxy prepreg Cycom 977-2-35-12KHTS-134-300 from Cytec. Plates with impact area 500 mm x 170 mm are loaded in axial tension or compression in a new hydraulic pre-stressing frame designed to fit in the DLR gas gun target chamber and are then tested under impact. Impact tests are carried out with a 60 mm diameter gas gun at velocities in the range 64 – 136 m/s, and impact energies 36 – 125 J. Two main impact scenarios are considered: notch damage from a 12 mm steel cube projectile, representative of impact from engine fragments or metal objects, and blunt impact damage from glass balls (Ø24-25 mm), which could represent hail or runway stone debris. Impact damage is detected by visual inspection and quantified with lock-in thermography, especially for delamination. Depending on the preload regime, corresponding residual strength tests are carried out on each plate.

Document Type:Monograph (Project Report)
Title:EASA.2009.OP.24 LIBCOS – Significance of Load upon Impact Behaviour of Composite Structure
Authors:
AuthorsInstitution or Email of Authors
Toso, NathalieUNSPECIFIED
Johnson, AlastairUNSPECIFIED
Date:November 2011
Number of Pages:150
Publisher:EASA (European Aviation Safety Agency)
Status:Published
Keywords:high velocity impact, damage tolerance, residual strength tests, composite panels
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Structures & Materials
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Nathalie Toso
Deposited On:12 Jan 2012 10:04
Last Modified:12 Jan 2012 10:04

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