About twenty years ago, the process of Creep Age Forming (CAF) was invented, and since then has been developed for the manufacture of heat treatable aluminium alloy panel components particularly, it has been successfully used for aircraft wing panels. Significant research work has been carried out in recent years and process applications have been expanded. This paper contains a review of recent research and development of this novel forming process. It covers process applications in the aircraft industry and scientific research, including the development of forming tools, experimental studies, materials and process modelling and springback prediction. Some potential future applications and challenges for deeper understanding of this novel process are also discussed.

A review of the development of creep age forming: Experimentation, modelling and applications

Influence of multi-step heat treatments in creep age forming of 7075 aluminum alloy: Optimization for springback, strength and exfoliation corrosion

Aeronautics and astronautics are two closely related disciplines, sometimes found under the joint term aerospace, that have progressed at a formidable pace during the 20th century. Their im...

Aeronautics and astronautics: Recent progress and future trends

http://spiral.imperial.ac.uk/bitstream/10044/1/18817/2/Journal%20of%20Materials%20Processing%20Technology_219_2015.pdf

Creep-age forming AA2219 plates with different stiffener designs and pre-form age conditions: Experimental and finite element studies

Influences of residual stresses and initial distortion on springback prediction of 7B04-T651 aluminium plates in creep-age forming

After a quick reminder of the principles of creep form process, a detailed comparison of the 6056, 2022, and 7475 alloys will be presented using experimental techniques for creep relaxation under tension and bending. Microstructural investigations using transmission electronic microscopy and small angle scattering techniques show the evolution of the hardening precipitation during the ageform process of the different alloys investigated. Damage tolerance and static properties of creep-formed products are discussed in detail. The results of an industrial sized demonstrator of an Airbus A340 fuselage panel are presented as a conclusion showing the strong potential of this cost-efficient process.

/pdf/ageformable-panels-for-commercial-aircraft-3i5f66ye5z.pdf

Ageformable panels for commercial aircraft

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Ageformable panels for commercial aircraft