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A component view of a GLARE3-3/2 hybrid sheet. There are three layers of aluminum alternating with two layers of glass fiber. In a GLARE3 grade, each glass fiber layer has two plies: one oriented at zero degrees, and the other oriented at ninety degrees.

Glass laminate aluminum reinforced epoxy (GLARE) is a fiber metal laminate (FML) composed of several very thin layers of metal (usually aluminum) interspersed with layers of S-2 glass-fiber pre-preg, bonded together with a matrix such as epoxy. The uni-directional pre-preg layers may be aligned in different directions to suit predicted stress conditions.

Though GLARE is a composite material,[1] its material properties and fabrication are very similar to bulk aluminum metal sheets. It has far less in common with composite structures when it comes to design, manufacture, inspection, or maintenance. GLARE parts are constructed and repaired using mostly conventional metal working techniques.

Its major advantages over conventional aluminum are:[2]

  • Better "damage tolerance" behavior, especially in impact and metal fatigue. Since the elastic strain is larger than other metal materials, it can consume more impact energy. It is dented more easily but has a higher penetration resistance.
  • Better corrosion resistance.
  • Better fire resistance.
  • Lower specific weight.

Furthermore, the material can be tailored during design and manufacture so that the number, type and alignment of layers can suit the local stresses and shapes throughout the aircraft. This allows the production of double-curved sections, complex integrated panels, or very large sheets.

While a simple manufactured sheet of GLARE is three to ten times more expensive than an equivalent sheet of aluminum,[3] considerable production savings can be made using the aforementioned optimization. A structure built with GLARE is lighter and less complex than an equivalent metal structure, requires less inspection and maintenance, and has a longer lifetime-till failure. These characteristics can make GLARE cheaper, lighter, and safer to use in the long run.


GLARE is a relatively successful FML, patented by the Dutch company Akzo Nobel in 1987.[4][5] It entered major application in 2007, when the Airbus A380 airliner began commercial service. Much of the research and development was done in the 1970s and 1980s at the Faculty of Aerospace Engineering, Delft University of Technology, where professors and researchers advanced the knowledge of FML and earned several patents, such as a splicing technique to build wider and longer panels without requiring external joints.[6]

The development of FML reflects a long history of research that started in 1945 at Fokker, where earlier bonding experience at de Havilland inspired investigation into the improved properties of bonded aluminum laminates compared to monolithic aluminum. Later, the United States National Aeronautics and Space Administration (NASA) became interested in reinforcing metal parts with composite materials in the Space Shuttle program, which led to the introduction of fibers to the bond layers. Thus, the concept of FMLs was born.

Further research and co-operation of Fokker with Delft University,[7] the Dutch aerospace laboratory NLR, 3M, Alcoa, and various other companies and institutions led to the first FML: the Aramid Reinforced ALuminum Laminates (ARALL), which combined aluminum with aramid fibers and was patented in 1981.[8][9][10] This material had some cost, manufacturing, and application problems; while it had very high tensile strength, the material proved suboptimal in compressive strength, off-axis loading, and cyclic loading. These issues led to an improved version with glass fiber instead of aramid fibers.

Over the course of the development of the material, which took more than 30 years from start to the major application on the Airbus A380, many other production and development partners have been involved, including Boeing, McDonnell Douglas, Bombardier, and the US Air Force.[11] Over the course of time, companies withdrew from this involvement, sometimes to come back after a couple of years. For example, Alcoa departed in 1995, returned in 2004, and withdrew again in 2010. It is alleged that disagreements between some of these partners caused Boeing to remove GLARE from the cargo floor of the Boeing 777 in 1993[12] (before the aircraft's service entry in 1995) and blocked Bombardier's plans to use GLARE in its CSeries aircraft in 2005.[13][11] These strategic decisions show the dynamic nature of innovation processes.[13]


Areas of the Airbus 380 aircraft fuselage where the glass laminated aluminum reinforced epoxy (GLARE) structural material is applied.

GLARE has been most often applied in the aviation field. It forms part of the Airbus A380 fuselage and the leading edge of the tail surfaces. In 1995, an aircraft freight container made out of GLARE became the first container certified by the Federal Aviation Administration (FAA) for blast resistance; the container can absorb and neutralize the explosion and fire from a bomb such as the one used in the Pan Am Flight 103 disaster over Lockerbie, Scotland in 1988.[14][15] GLARE has also been used in the front radome bulkhead of the Bombardier Learjet 45 business jet,[16] which was first delivered in 1998,[17] as a cargo liner solution for regional jets,[18] and in straps for the highest loaded frames in the Airbus A400M military transport aircraft.[19]

Varieties and nomenclature[edit]

There are six standard GLARE grades (GLARE1 through GLARE6) with typical densities ranging from 2.38 to 2.52 grams per cubic centimetre (0.086 to 0.091 lb/cu in),[20] which is similar to the 2.46 to 2.49 g/cm3 (0.089 to 0.090 lb/cu in) density of S-2 glass fiber.[21] These densities are smaller than the 2.78 g/cm3 (0.100 lb/cu in) density of 2024-T3 aluminum alloy,[22] a common aluminum alloy in aircraft structures that is also incorporated into all but one of these GLARE grades. (GLARE1 uses the 7475-T761 alloy instead.) As the strength of the composite varies with fiber direction, the GLARE grades differ by the number and complexity of pre-preg plies and orientations within a composite layer.[20] Each GLARE grade has A and B variants that have the same number of plies but with alternate fiber orientations.[23] The standard GLARE grades are cured in an autoclave at 120 °C (248 °F) for 3.5 hours under 11-bar pressure (11 atm; 160 psi; 1,100 kPa), and they use the FM94 epoxy pre-preg.[24]

Standard GLARE grades, ply orientations, and benefits[25]
Grade (ply orientations, in degrees) Advantages
1 (0°/0°) Fatigue, strength, yield stress
2A (0°/0°) Fatigue, strength
2B (90°/90°) Fatigue, strength
3A (0°/90°) Fatigue, impact
3B (90°/0°) Fatigue, impact
4A (0°/90°/0°) Fatigue, strength in 0° direction
4B (90°/0°/90°) Fatigue, strength in 90° direction
5A (0°/90°/90°/0°) Impact
5B (90°/0°/0°/90°) Impact
6A (+45°/-45°) Shear, off-axis properties
6B (-45°/+45°) Shear, off-axis properties

A single sheet of GLARE may be referred to using the naming convention GLARE grade - Aluminum layers / Glass fiber layers - Aluminum layer thickness. The number of aluminum layers is always one more than the number of glass fiber layers, and the aluminum layer thickness is in millimeters, which can range from 0.2 to 0.5 mm (0.0079 to 0.0197 in; 7.9 to 19.7 mils). (GLARE1 can only consist of aluminum layers of 0.3 to 0.4 mm (0.012 to 0.016 in; 12 to 16 mils) thickness, though.) For example, GLARE4B-4/3-0.4 is a GLARE sheet with a GLARE4 grade (using the B variant) where there are four aluminum layers and three glass fiber layers, and the thickness of each aluminum layer is 0.4 mm (0.016 in; 16 mils).[25] (In contrast, a typical sheet of photocopy paper is 0.097 mm (0.004 in; 4 mils) thick, while a typical business card is 0.234 mm (0.009 in; 9 mils) thick.)[26]

The thickness of a GLARE grade does not need to be separately specified, because each pre-preg ply has a nominal thickness of 0.125 mm (0.0049 in; 4.9 mils), and the number of plies is already defined for a GLARE grade number. GLARE grades 1, 2, 3, and 6 have just two plies of glass fibers, so the thickness of an individual glass fiber layer is 0.25 mm (0.0098 in; 9.8 mils). GLARE4 has three plies, so its glass fiber layers are each 0.375 mm (0.0148 in; 14.8 mils) thick. GLARE5 has four plies, with individual glass fiber layers of 0.5 mm (0.020 in; 20 mils) thickness.[20] GLARE sheets have typical overall thicknesses between 0.85 and 1.95 mm (0.033 and 0.077 in; 33 and 77 mils).[22]

Other, less common grades and designations of aluminum/glass fiber hybrids also exist. A newer class of GLARE, called High Static Strength GLARE (HSS GLARE), incorporates the 7475-T761 alloy and cures at 175 °C (347 °F) using FM906 epoxy pre-preg. HSS GLARE comes in three grades (HSS GLARE3, HSS GLARE4A, and HSS GLARE4B), mirroring the plies and orientations of their corresponding standard GLARE grades.[24] Russia gives its version of GLARE the name SIAL, a translation from the Russian acronym for fiberglass and aluminum/plastic (С.И.А.Л.). It defines the grades SIAL-1 through SIAL-4, which usually contain the second-generation Russian aluminum-lithium alloy 1441 and range in density from 2.35 to 2.55 g/cm3 (0.085 to 0.092 lb/cu in).[27] Airbus bases their material designations on the underlying aluminum alloy, using prefixes such as 2024-FML, 7475-FML, and 1441-FML[24][28] instead of GLARE and HSS GLARE.

Comparison of GLARE and aluminum[29]
Values in megapascals (MPa) and kips per square inch (ksi)
Material Al 2024-T3 GLARE3-4/3-0.4
Tensile strength 440 (64) 620 (90)
Yield strength 325 (47.1) 284 (41.2)
Compressive strength 270 (39) 267 (38.7)
Bearing strength 890 (129) 943 (136.8)
Blunt notch strength 410 (59) 431 (62.5)
Young's modulus 72,400 (10,500) 58,100 (8,430)
Shear modulus 27,600 (4,000) 17,600 (2,550)

Airbus parts production[edit]

GLARE contributes 485 square metres (5,220 sq ft) of material to each A380 plane. This material constitutes three percent by weight of the A380 structure,[2] which has an operating empty weight (OEW) of 277,000 kg (610,700 lb; 277.0 t; 305.4 short tons). Because of the ten-percent lower density of GLARE compared to a typical standalone aluminum alloy, GLARE's usage on the A380 results in an estimated direct (volume-based) savings of 794 kg (1,750 lb; 0.794 t; 0.875 short tons),[30] which doesn't include the follow-on weight savings in the entire aircraft structure that result from the lower material weight. For example, a 1996 internal Airbus study calculated that the weight savings from GLARE in the upper fuselage would be 700 kg (1,500 lb; 0.70 t; 0.77 short tons) from just the lighter material, but it would total 1,200 kg (2,600 lb; 1.2 t; 1.3 short tons) due to the "snowball effects" of smaller engines, smaller landing gear, and other positive changes.[31] (However, this is much smaller than an Airbus vice president's early claim that GLARE would result in 15,000 to 20,000 kg (33,000 to 44,000 lb; 15 to 20 t; 17 to 22 short tons) of savings,[13][32] presumably if it were used throughout most of the aircraft.)

To take advantage of GLARE's higher tensile strength, 469 m2 (5,050 sq ft) is used on the upper fuselage of the front and rear sections. GLARE was removed from the center upper fuselage in 2000[33] as shear strength precaution (although the GLARE supplier felt it could have handled that area),[34] and the fuselage underside is made of other materials with higher Young's modulus (stiffness) values to resist buckling.[2]

In the fuselage, GLARE2A is applied to stringers, GLARE2B to butt straps, and GLARE3 and GLARE4B to the fuselage skins.[35] Late in the A380 development process, the plane was found to be heavier than the original specifications, so Airbus replaced conventional aluminum with GLARE5 as a weight-saving measure for the leading edges of the horizontal stabilizer and the vertical stabilizer,[35] though at great expense.[3] The A380 GLARE fuselage skin panels have a minimum thickness of 1.6 mm (0.063 in; 63 mils)[28] but can be much thicker, as some areas of the shells may need up to 30 layers of aluminum and 29 layers of glass fiber.[36]

GLARE is currently made by GKN-Fokker and Premium AEROTEC. GKN-Fokker manufactures 22 of the 27 A380 GLARE fuselage shells at its 12,000 m2 facility (130,000 sq ft) in Papendrecht, Netherlands,[37] which uses an autoclave with a length of 23 metres (75 ft) and a diameter of 5.5 m (18 ft).[38] The company produces sheets of 3 by 12 m (9.8 by 39.4 ft),[36] which incorporates the milling of door and window cutouts on a 5-axis milling machine.[37] Premium AEROTEC manufactures the remaining five shells in Nordenham, Germany[37][39] in an autoclave with a usable length of 15 m (49 ft) and an internal diameter of 4.5 m (15 ft).[40] The company also produces the GLARE2A butt straps for the A400 program.[39][19] Its output was 200 m2 (2,200 sq ft) per month as of 2016.[41]

With Airbus ending production of the A380 in 2021,[42] GLARE will go out of volume production unless it is selected for another airplane manufacturing program.

Future developments[edit]

Since around 2014, Airbus, its two current GLARE suppliers, and Stelia Aerospace have been collaborating to manufacture GLARE in a high-volume, automated production setting that will deliver larger fuselage panels for aluminum aircraft. Using robots for tape laying and other tasks, automated production will involve a single-shot bonding process that will cure aluminum, pre-preg, stringer, and doublers simultaneously in the autoclave, followed by a single nondestructive testing (NDT) cycle, instead of the stringers and doublers requiring a second bonding and NDT cycle in the existing process.[41][43] The belief is that the material will reduce fuselage weight by 15 to 25 percent compared to the aluminum sections they would replace on single-aisle aircraft such as the Boeing 737 and the Airbus 320.[44][43] (Before the announcement of the A380 production stoppage,[42] the automation program was also intended to lower the weight the A380 GLARE sections by 350 kilograms (770 pounds; 0.35 metric tons; 0.39 short tons) at a manufacturing cost of 75% of the existing A380 GLARE panels.)[36]

To support these single-aisle aircraft production goals, GKN-Fokker planned to open an automated production line at its site in 2018, with a goal of manufacturing panels of up to 8 by 15 m (26 by 49 ft) in size and increasing the production rate by a factor of ten.[36] In targeting a fifty-fold increase of GLARE production capacity to 10,000 m2 (110,000 sq ft) per month, Premium AEROTEC[41] planned to update its automated test cell in summer 2018 to manufacture demonstrator panels of 4 by 12 m (13 by 39 ft). This size will match the largest GLARE panels to be potentially used by Airbus in short-range and medium-range aircraft.[43] The GLARE automation process for 2 by 6 m (6.6 by 19.7 ft) prototypes reached technology readiness level (TRL) 4 in late 2016,[36] exceeded TRL 5 as of 2018,[45] and has an eventual target of TRL 6.[46]

In 2014, Embraer built and tested a 2.2 m diameter (7.2 ft; 2,200 mm; 87 in), 3 m long (9.8 ft) technology demonstrator that was partially made of FML and was based on the central fuselage of its ERJ-145 aircraft.[47] Later, Embraer worked with Arconic (formerly Alcoa) to build a demonstrator for a lower wing skin composed of fiber-metal laminates, which contained sheets of 2524-T3 aluminum alloy and unidirectional plies of glass fiber. Embraer built and tested the wing demonstrator to increase the TRL of the FML manufacturing process so that it can be applied to future structural applications.[48][49] Lower wing skins on single-aisle aircraft are thicker than fuselage skins, measuring at least 8 mm (0.31 in; 310 mils) thick overall and between 10 to 15 mm (0.39 to 0.59 in; 390 to 590 mils) thick between the fuselage and the engine mount,[50] so larger aluminum layer thicknesses of 0.8 to 1.6 mm (0.031 to 0.063 in; 31 to 63 mils) will probably be required[51] to reduce the number of layers for manufacturing ease.

See also[edit]


  1. ^ King, David; Inderwildi, Oliver; Carey, Chris (January 2009). "Advanced aerospace materials: past, present and future". Aviation and the Environment. 3 (March 2009): 22–27. ISSN 1755-9421. OCLC 500326779. Archived (PDF) from the original on June 29, 2011.
  2. ^ a b c Pacchione, M.; Telgkamp, J. (September 5, 2006). "Challenges of the metallic fuselage" (PDF). 25th International Congress of the Aeronautical Sciences (ICAS 2006). Congress of the International Council of the Aeronautical Sciences. 4.5.1 (25 ed.). Hamburg, Germany. pp. 2110–2121. ISBN 978-0-9533991-7-8. OCLC 163579415. Archived (PDF) from the original on January 27, 2018. Lay summary.
  3. ^ a b Weber, Austin (August 4, 2005). "Assembling the super jumbo - The Airbus A380 presents numerous production challenges". Assembly Magazine. Vol. 48 no. 9 (published August 2005). p. 66. ISSN 1050-8171. OCLC 99186153. Archived from the original on March 14, 2017. Retrieved 17 December 2018.
  4. ^ Vlot 2001, pp. 88-90
  5. ^ EP patent 0312151, Vogelesang, Laurens Boudewijn & Gerardus Hubertus Joannes Joseph Roebroeks, "Laminate of metal sheets and continuous glass filaments-reinforced synthetic material", issued 1991-03-27, assigned to AKZO NV 
  6. ^ US patent 5429326, Garesche, Carl E.; Gerandus H. J. J. Roebroeks & Buwe V. W. Greidanus et al., "Laminate of aluminum sheet material and aramid fibers", issued 1995-07-04, assigned to Structural Laminates Co. 
  7. ^ Morinière, Freddy D.; Alderliesten, René C.; Tooski, Mehdi Yarmohammad; Benedictus, Rinze (26 July 2012). "Damage evolution in GLARE fibre-metal laminate under repeated low-velocity impact tests". Central European Journal of Engineering. 2 (4): 603–611. Bibcode:2012CEJE....2..603M. doi:10.2478/s13531-012-0019-z. ISSN 1896-1541. OCLC 5652832381.
  8. ^ Vlot 2001, pp. 48-50
  9. ^ US patent 4489123, Schijve, Jacobus; Laurens B. Vogelesang & Roelof Marissen, "Laminate of metal sheet material and threads bonded thereto, as well as processes for the manufacture thereof", issued 1984-12-18, assigned to Technische Universiteit Delft 
  10. ^ US patent 4500589, Schijve, Jacobus; Laurens B. Vogelesang & Roelof Marissen, "Laminate of aluminum sheet material and aramid fibers", issued 1985-02-19, assigned to Technische Universiteit Delft 
  11. ^ a b Berends, Hans; van Burg, Elco; van Raaij, Erik M. (October 22, 2010). "Contacts and contracts: Cross-level network dynamics in the development of an aircraft material". Organization Science (published July–August 2011). 22 (4): 940–960. doi:10.1287/orsc.1100.0578. hdl:1871/38079. ISSN 1047-7039. JSTOR 20868905. OCLC 746052937. Retrieved January 17, 2019.CS1 maint: Date format (link)
  12. ^ Vlot 2001, pp. 100-109
  13. ^ a b c Van Burg, Elco; Berends, Hans; van Raaij, Erik M. (August 8, 2013). "Framing and interorganizational knowledge transfer: A process study of collaborative innovation in the aircraft industry" (PDF). Journal of Management Studies (published May 2014). 51 (3): 349–378. doi:10.1111/joms.12055. hdl:1871/47108. ISSN 0022-2380. OCLC 1021160083. Archived (PDF) from the original on January 8, 2019. Lay summary.
  14. ^ Vlot 2001, pp. 101-102
  15. ^ McMullin, David (January 2002). "Lockerbie insurance: Hardened luggage containers can neutralize explosives". Scientific American Magazine. Vol. 286 no. 1. ISSN 0036-8733. OCLC 120857020. Archived from the original on January 10, 2002. Retrieved 16 December 2018.
  16. ^ Vlot 2001, p. 137
  17. ^ Warwick, Graham (24 June 1998). "Global Express Canadian approval approaches". Flight International. Wichita, Kansas, USA. Archived from the original on February 9, 2019. Retrieved February 9, 2019. European certification of the Learjet 45 business jet is expected by mid-July. US certification was received last September, but deliveries did not begin until May, following approval for flight into known icing. Only one aircraft has been handed over so far, but Bombardier expects to deliver 35-40 this financial year, with production set to reach 60 next year.
  18. ^ Rans, C. D. (2011-10-12). "Chapter 2: Bolted joints in glass reinforced aluminium (Glare) and other hybrid fibre metal laminates (FML)". In Camanho, P.; Hallett, Stephen R. (eds.). Composite Joints and Connections: Principles, Modelling and Testing. p. 42. doi:10.1533/9780857094926.1.35. ISBN 9780857094926. OCLC 952548128. Lay summary.
  19. ^ a b Plokker, Matthijs; Daverschot, Derk (May 20, 2009). "Hybrid structure solution for the A400M wing attachment frames: From concept study to structural justification" (PDF). In Bos, Marcel J. (ed.). ICAF 2009: Bridging the Gap between Theory and Operational Practice. Symposium of the International Committee on Aeronautical Fatigue. 25. Rotterdam, Netherlands: Springer Netherlands. pp. 375–385. doi:10.1007/978-90-481-2746-7. ISBN 978-90-481-2745-0. OCLC 873603795. Archived (PDF) from the original on May 28, 2016. Lay summary.
  20. ^ a b c Park, Sang Yoon; Choi, Won Jong (November 5, 2018). "5. The guidelines of material design and process control on hybrid fiber metal laminate for aircraft structures". In Maalawi, Karam Y. (ed.). Optimum composite structures. IntechOpen (published January 30, 2019). doi:10.5772/intechopen.78217. ISBN 978-1-78985-067-3. OCLC 1084316066. Archived from the original on March 13, 2019. Retrieved March 13, 2019.
  21. ^ "Advanced materials: Solutions for demanding applications" (PDF). 2004. Retrieved December 18, 2018.
  22. ^ a b Breuer, Ulf Paul (2016). "Material technology". Commercial aircraft composite technology (corrected publication May 2018 ed.). Kaiserslautern, Germany: Springer International Publishing Switzerland. pp. 50–51. doi:10.1007/978-3-319-31918-6. ISBN 9783319319186. OCLC 1040185833. Retrieved 11 December 2018.
  23. ^ "GLARE types & configurations". Fibre Metal Laminates Centre of Competence (FMLC). Delft, Netherlands. Archived from the original on February 20, 2018. Retrieved 13 December 2018.
  24. ^ a b c Alderliesten, René (2017). "Chapter 2: Laminate concepts & mechanical properties" (PDF). Fatigue and fracture of fibre metal laminates. Solid Mechanics and its Applications. 236. Springer, Cham. pp. 7–27. doi:10.1007/978-3-319-56227-8_2. ISBN 978-3-319-56226-1. OCLC 1048940338. Retrieved 11 December 2018.
  25. ^ a b "Results & cases". Fibre Metal Laminates Centre of Competence (FMLC). Delft, Netherlands. Archived from the original on 20 February 2018. Retrieved 16 December 2018.
  26. ^ Paper weight chart. Jam Paper & Envelope. Archived from the original on August 9, 2017. Retrieved January 17, 2019.
  27. ^ "Laminated alumoglassplastics (SIALs)". All-Russian Scientific Research Institute of Aviation Materials (VIAM). Archived from the original on March 20, 2019. Retrieved March 19, 2019.
  28. ^ a b R. C. Alderliesten; C. D. Rans; Th. Beumler; R. Benedictus (June 1–3, 2011). "Recent advancements in thin-walled hybrid structural technologies for damage tolerant aircraft fuselage applications" (PDF). In Komorowski, Jerzy (ed.). ICAF 2011 Structural integrity: Influence of efficiency and green imperatives. International Committee on Aeronautical Fatigue (ICAF) Symposium. 26. Montréal, Quebec, Canada: Springer, Dordrecht. pp. 105–117. doi:10.1007/978-94-007-1664-3_8. ISBN 978-94-007-1663-6. OCLC 800760887. Archived (PDF) from the original on November 9, 2016. Retrieved 14 December 2018. Lay summary.
  29. ^ "GLARE properties" (DOCX). Fibre Metal Laminates Centre of Competence (FMLC). Delft, Netherlands. Retrieved 14 December 2018.
  30. ^ Wu, Guocai; Yang, J. M. (January 2005). "Overview: Failure in structural materials: The mechanical behavior of GLARE laminates for aircraft structures". JOM: The Journal of the Minerals, Metals & Materials Society. 57 (1): 72–79. doi:10.1007/s11837-005-0067-4. ISSN 1047-4838. OCLC 5650014694.
  31. ^ Vlot 2001, pp. 157-162
  32. ^ Versteeg, Ferry (January 22, 1997). Written at Toulouse, France. "Einde superjumbo verrast Airbus". NRC Handelsblad (in Dutch). Amsterdam, Netherlands. p. 15. Archived from the original on January 22, 2019. Retrieved January 22, 2019. Jarry: 'Stel dat we glare voor de A3xx gebruiken, dan zou dat zeker 15 tot 20 ton aan gewicht schelen. We gaan nu een rompdeel van glare-materiaal bouwen en uitgebreid testen om te zien hoe het zich onder extreme omstandigheden houdt.'
  33. ^ Vlot 2001, pp. 187-188
  34. ^ Phelan, Michael (13–19 May 2003). "Stork sees bright future for Glare applications: Composite material manufacturer begins A380 upper fuselage skin panel deliveries" (PDF). Flight International. 163 (4882). Papendrecht, Netherlands. ISSN 0015-3710. OCLC 1069406808. Archived from the original on January 23, 2019. Retrieved January 23, 2019. 'We didn't put Glare on the centre fuselage because of the high shear loads, but we think we can tailor Glare's properties to suit the location,' says de Koning.CS1 maint: Date format (link)
  35. ^ a b Wanhill, R.J.H. (November 12, 2016). "Chapter 13: GLARE: A versatile fibre metal laminate (FML) concept" (PDF). In Prasad, N. Eswara (ed.). Aerospace materials and material technologies: Volume 1: Aerospace materials. Indian Institute of Metals Series. Springer Science+Business Media Singapore 2017. pp. 291–308. doi:10.1007/978-981-10-2134-3_13. ISBN 978-981-10-2133-6. OCLC 6869372125. Lay summary.
  36. ^ a b c d e "Fokker to automate FML production". Inside Composites. 2nd International Composites Conference, Düsseldorf, Germany. December 5, 2016. Archived from the original on January 18, 2018. Retrieved 12 December 2018.
  37. ^ a b c "Reducing A380 weight. GLARE is key: Perhaps the best known technological innovation aboard the A380 is the GLARE (glassfibre reinforced aluminium) composite material which will be used for much of the upper fuselage skins". Supplement. Flight International (published May 20–26, 2003). May 20, 2003. p. X. ISSN 0015-3710. OCLC 1069406808. Archived from the original on December 13, 2018. Retrieved 13 December 2018.CS1 maint: Date format (link)
  38. ^ "Dutch minister of economic affairs opens Stork Aerospace GLARE factory". Stork Aerospace (Press release). Papendrecht, Netherlands. November 24, 2003. Archived from the original on December 18, 2018. Retrieved 14 December 2018.
  39. ^ a b Gardiner, Ginger (August 16, 2016). "The resurgence of GLARE: Airbus pursues fiber metal laminates for future narrowbody construction, citing cost, weight, repair and lightning strike benefits". CompositesWorld. ISSN 2376-5240. OCLC 943597826. Archived from the original on September 8, 2017. Retrieved December 13, 2018.
  40. ^ "Autoclave for production of new Airbus A350 XWB arrives in Nordenham". Airframer Limited (Press release). Nordenham, Germany. August 23, 2009. Archived from the original on January 25, 2019. Retrieved January 25, 2019.
  41. ^ a b c "Aerospace: New chance for fiber metal laminates — GLARE production amped by automation" (PDF). Trends. CompositesWorld. Vol. 2 no. 10. October 2016. pp. 30–31. ISSN 2376-5232. OCLC 943597826. Retrieved February 1, 2019.
  42. ^ a b Katz, Benjamin D; Kammel, Benedikt (February 13, 2019). "Economics: Airbus will stop making the world's largest passenger jet". Bloomberg. Archived from the original on February 15, 2019.
  43. ^ a b c Apmann, Hilmar; Busse, Matthias; Du, Jia-Yang; Köhnke, Patrick (August 31, 2017). "Automated manufacture of fibre metal laminates to achieve high rate of production". Lightweight Design Worldwide. Springer Fachmedien Wiesbaden (published August 2017). 10 (4): 28–33. doi:10.1007/s41777-017-0037-x. ISSN 2510-2877. OCLC 974210407. Archived from the original on June 17, 2018.
  44. ^ Black, Sara (July 12, 2017). "Fiber-metal laminates in the spotlight: Interest in FMLs is growing again as aeroengineers search for lightweight solutions adaptable to new narrowbody commercial aircraft" (PDF). Inside manufacturing. CompositesWorld. Vol. 3 no. 9 (published September 2017). pp. 86–93. ISSN 2376-5232. OCLC 7160489307. Archived from the original on September 19, 2017. Retrieved December 11, 2018.
  45. ^ Fraunhofer Institute for Manufacturing Technology and Advanced Materials (IFAM) (November 14, 2018). "Automation solutions developed in the 'Autoglare' project funded by the Federal Ministry for Economic Affairs and Energy (BMWi): Automated adhesive film placement and stringer integration for aircraft manufacture" (Press release). Stade, Germany. Archived from the original on January 4, 2019. Retrieved January 4, 2019.
  46. ^ Canaday, Henry (March 30, 2016). "Airbus, Fokker seek less expensive fiber metal laminate". Aviation Week Network. Archived from the original on September 25, 2017. Retrieved 13 December 2018.
  47. ^ Bertoni, Marcelo; Fernandez, Fernando; Miyazaki, Marcos (June 16, 2014). Fuselage technology demonstrator. 25th advanced aerospace materials and processes (AeroMat) conference and exposition. Orlando, Florida, USA. Retrieved March 20, 2019.
  48. ^ "Manufacturing of a fiber metal laminate lower wing cover demonstrator". Charleston, South Carolina, USA. April 10, 2017. Archived from the original on March 12, 2019. Retrieved March 12, 2019.
  49. ^ "FML Outlook programme". November 2–3, 2017. Archived from the original on March 12, 2019. Retrieved March 12, 2019.
  50. ^ Roebroeks, Geert H. J. J.; Hooijmeijer, Peter A.; Kroon, Erik J.; Heinimann, Markus B. (September 25–28, 2007). The development of CentrAl. First International Conference on Damage Tolerance of Aircraft Structures. Delft, Netherlands.
  51. ^ Kulak, Mike (November 2, 2017). A material supplier’s assessment of FML for single aisle lower wing skins. FML Outlook - a world of opportunities. Delft, Netherlands. Archived from the original on March 20, 2019. Retrieved March 18, 2019.


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