Publications
236 results found
Clarke AB, Jones C, Greenhalgh ES, et al., 2001, Design and manufacture of a modular composite (CFRP) wingbox, ICCM13: 13th international conference on composite materials, Beijing, 25 - 29 June 2001
Greenhalgh E, Clarke A, Millson B, et al., 2000, Investigation of impact damage in a CFRP wingbox under load, Pages: 1344-1354, ISSN: 0273-4508
Carbon-fibre reinforced plastics are widely used in aircraft structures but are susceptible to impact damage. Previous studies on impact have been conducted on coupons and structural elements so the main objective of this work was to investigate the impact resistance of a more realistic structure; a CFRP wingbox. The effect of parameters such as impact energy, site with respect to substructure and proximity to the ends and sides on the impact resistance were investigated. In addition, a key aspect was to study the effect of the loading during impact on the structural response and damage extent. The wingbox was impacted at twenty-two sites, which led to a number of findings. Firstly, there was no interaction between the damages which implied good tolerance to multi-site impact. The location of the impact with respect to the substructure dominated the results, although loading during impact (particularly compressive) had a significant effect on the structural response and damage extent. The results of this study indicated that current design rules may be overly conservative but the use of dent depth as an indication of the severity of damage is not conservative and alternative indicators are required.
Greenhalgh ES, Singh S, Nilsson KF, 2000, Mechanisms and Modelling of Delamination Growth and Failure of Carbon-Fibre Reinforced Skin-Stringer Panels, Seattle, ASTM STP 1383 & ASTM D-30, 'Composite Structures: Theory & Practice, Publisher: ASTM
Greenhalgh E, Clarke A, Millson B, et al., 2000, Investigation of impact damage in a CFRP wingbox under load, AIAA/ASME/ASCE/AHS/ASC 41st Structures, Structural Dynamics, and Materials Conference, Publisher: AMER INST AERONAUTICS & ASTRONAUTICS, Pages: 1344-1354
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- Citations: 1
Greenhalgh E, Asp L, Singh S, 1999, Delamination Resistance, Failure Criteria and Fracture Morphology of 0?/0?, 0?/5? and 0?/90? Ply Interfaces in CFRP, London, 5th International Conference on Deformation and Fracture of Composites
Greenhalgh ES, Singh S, Hughes D, et al., 1999, Impact Damage Resistance and Tolerance of Stringer-Stiffened Composite Structures, Plastics, Rubber and Composites, Vol: 28, Pages: 228-251
Greenhalgh E, Singh S, 1999, Investigation of the Failure Mechanisms for Delamination Growth From Embedded Defects, Paris, France, 12th International Conference on Composite Materials (ICCM12), Paris, France
Hopgood P, Greenhalgh E, Singh S, 1999, Design and Analysis of Stiffened Composite Structures at DERA, London, IMechE Seminar S695, Designing High Performance Stiffened Structures, Publisher: IMechE
Singh S, Greenhalgh ES, 1998, Micromechanisms of Interlaminar Fracture in Carbon-Fibre Reinforced Plastics at Multidirectional Ply Interfaces Under Static and Cyclic Loading, Plastics, Rubber and Composites, Vol: 27, Pages: 220-226
Lord S, Greenhalgh E, 1998, Analysis and Prediction of Delamination Growth from Embedded Defects in Composite Materials, Naples, Italy, 8th European Conference on Composite Materials (ECCM8)
Singh S, Greenhalgh E, 1998, Delamination Growth in Epoxy-Matrix Composites under Cyclic Loading: Implications for Design and Certification, Naples, Italy, 8th European Conference on Composite Materials (ECCM8)
Greenhalgh ES, Bishop S, Bray D, et al., 1997, Characterisation of Impact Damage in Skin-Stringer Composite Structures, Composites Structures, Vol: 36, Pages: 187-207
Wiggenraad J, Greenhalgh ES, Maison S, et al., 1997, Damage Propagation in Composite Structural Elements - Structural Experiments and Analyses, Composites Structures, Vol: 36, Pages: 209-220
Singh S, Greenhalgh E, 1997, Micromechanisms of Interlaminar Fracture in Carbon-Epoxy Composites at Multidirectional Ply Interfaces, Manchester, 4th International Conference on Deformation and Fracture of Composites
Ireman T, Thesken J, Greenhalgh ES, et al., 1997, Damage Propagation in Composite Structural Elements - Coupon Experiments and Analyses, Composites Structures, Vol: 36, Pages: 173-186
Greenhalgh E, Singh S, Roberts D, 1997, Impact Damage Growth and Failure of Carbon-Fibre Reinforced Skin-Stringer Panels, Brisbane, 11th International Conference on Composite Materials (ICCM11), Gold Coast, Australia
Wiggenraad JFM, Aoki R, Gadke M, et al., 1996, Damage propagation in composite structural elements - Analysis and experiments on structures, COMPOSITE STRUCTURES, Vol: 36, Pages: 173-186, ISSN: 0263-8223
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- Citations: 17
Greenhalgh ES, Matthews F, 1996, Characterisation of Mixed-Mode Fracture in Unidirectional Laminates, London, 7th European Conference on Composite Materials (ECCM7)
Greenhalgh E, Bishop S, Jelley J, 1996, Environmental Sequence Effects in Fatigue of Carbon Fibre Composites, London, 7th European Conference on Composite Materials (ECCM7)
Bogdanovich AE, Pastore CM, Greenhalgh ES, et al., 1994, Analytical and experimental results for a quasi-unbalanced composite double box beam spar, Pages: 851-862
The benefits of bend-twist coupling are known in the aircraft industry, but practical manufacturing schemes have not been previously developed. In this paper, a double box beam spar manufactured with conventional textile processes is presented which demonstrates twist-bend coupling without extension-shear coupling. This type of material system is termed 'quasi-unbalanced.' Methods for predicting the response of such a 'smart spar' are presented and compared with experimental results. The analytical method incorporates the technique of 'meso-volumes' to represent the material inhomogeneities associated with the manufacturing method. Several meso-volume representations of the spar cross section are used in the analysis, and the convergence of numerical data when using finer meso-volume meshes is demonstrated. Experimental results are obtained by bending the spar with uncoupled bending load and measuring the resulting displacements with laser ranging techniques. The twist/bend couple is determined from this experimental method for a series of spars with the fiber orientations 0, 17, 30, 45, and 65°. The experimental data are in a good agreement with the analytical results obtained from the 3-D solutions based on two distinct meso-volume models.
Greenhalgh ES, 1993, Delamination Growth in Carbon/Fibre Composite Structures, Composite Structures, Vol: 23, Pages: 165-175
GREENHALGH ES, PASTORE CM, GARFINKLE M, 1993, A CONTINUOUS-FIBER COMPOSITE WING BOX-BEAM EXHIBITING TWIST-BEND COUPLING, COMPOSITES ENGINEERING, Vol: 3, Pages: 691-697, ISSN: 0961-9526
Greenhalgh ES, Cox PC, 1991, A Method to Determine Propagation Direction of Compression Fracture in Carbon/Fibre Composites, Composite Structures, Vol: 21, Pages: 1-7
Greenhalgh ES, McGrath G, 1991, Failure Analysis of Thermoplastic Welds, Manchester, 1st International Conference on Deformation & Fracture of Composites, Publisher: PRI
Greenhalgh E, Millson B, Thompson R, et al., 1990, Testing and Failure Analysis of a CFRP Wingbox Containing a 150J Impact, Paris, France, 12th International Conference on Composite Materials (ICCM12), Paris, France
Bregazzi M, Greenhalgh E, Sutherland JW, et al., 1965, Some observations on the reaction of polymer carbons with carbon dioxide, Carbon, Vol: 3, ISSN: 0008-6223
The reaction of carbon dioxide with pyrolysed polymer carbons having different structures has been studied in the temperature range 750-850°C and in the pressure range 1-12 cm Hg. The kinetics have been followed gravimetrically using a sensitive microbalance. A static system was used throughout. The carbons have been characterised by electron microscopy, electron diffraction, X-ray diffraction, chemical analysis and physical adsorption techniques. The two polymer materials chosen (polyvinyl chloride, and polyvinylidene chloride) produce two carbons having extreme structures (graphitisable and non-graphitisable respectively). The samples used were heat-treated to 2500°C. Two distinct activation energies were found and these were identical for both materials. The high value (85 kcal mole-1) was always found with well outgassed samples, and the low value (69 kcal mole-1) with those which were poorly outgassed or highly oxidised. A new reaction scheme is postulated which fits all the facts. The two activation energies are explained in terms of the intercalation of oxygen, water vapour and possibly carbon dioxide. © 1965.
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