RT Journal Article
T1 Hot stamping of aerospace aluminium alloys: 												Automotive technologies for the aeronautics industry
A1 Atxaga, G.
A1 Arroyo, A.
A1 Canflanca, B.
AB This paper proposes the use of the hot stamping process that provides ready to use parts for the obtention of aircraft components as an alternative manufacturing technology to e.g. machined parts. The development has been focused on the study of the high temperature formability of aluminium alloys. The feasibility of hot forming the AA2198 aluminium‑lithium alloy into complex shapes component has been studied. A wide experimental campaign has been carried out to set up the optimum hot stamping process parameters. In addition, forming trials with different geometries (omega and B-pillar shapes) have also been performed and, after the corresponding heat treatment, material properties have been recovered. Simulations of the hot stamping process have been carried out with Pamstamp® 2G software. These results have been correlated with the ones obtained in the experimental campaign. As a final step of the development, a demonstrator corresponding to a wing rib has been successfully manufactured. Characterization carried out to the prototype indicate specifications are fulfilled.
SN 1526-6125
YR 2022
FD 2022-09
LA eng
NO Atxaga , G , Arroyo , A & Canflanca , B 2022 , ' Hot stamping of aerospace aluminium alloys : Automotive technologies for the aeronautics industry ' , Journal of Manufacturing Processes , vol. 81 , pp. 817-827 . https://doi.org/10.1016/j.jmapro.2022.07.032
NO Publisher Copyright: © 2022 The Society of Manufacturing Engineers
NO The study presented in this paper was carried out in the frame of OUTCOME project within Airframe ITD of Clean Sky 2 Programme. The project received funding from the Clean Sky 2 Joint Undertaking (JU) under ITD Airframe Grant Agreement for Members. The JU received support from the European Union's Horizon 2020 (H2020) research and innovation programme and the Clean Sky 2 JU members other than the Union. The authors want to acknowledge Airbus Defence and Space S.A.U for providing the design of the developed prototype, Aernnova Aerospace S.A.U for OUTCOME project coordination and facilitator and fruitful technical discussions and RIB-ON Consortium for developing and building the die and final manufacturing of the wing ribs. The study presented in this paper was carried out in the frame of OUTCOME project within Airframe ITD of Clean Sky 2 Programme. The project received funding from the Clean Sky 2 Joint Undertaking (JU) under ITD Airframe Grant Agreement for Members. The JU received support from the European Union's Horizon 2020 (H2020) research and innovation programme and the Clean Sky 2 JU members other than the Union.
DS TECNALIA Publications
RD 3 jul 2024