Standard

Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures. / Labans, Edgars; Bisagni, Chiara.

ECSSMET 2018: 15th European Conference on Spacecraft Structures: 2018, Noordwijk, Netherlands. 2018.

Research output: Chapter in Book/Report/Conference proceedingConference contributionScientificpeer-review

Harvard

Labans, E & Bisagni, C 2018, Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures. in ECSSMET 2018: 15th European Conference on Spacecraft Structures: 2018, Noordwijk, Netherlands. ECSSMET 2018: 15th European Conference on Spacecraft Structures, Noordwijk, Netherlands, 28/05/18.

APA

Labans, E., & Bisagni, C. (2018). Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures. In ECSSMET 2018: 15th European Conference on Spacecraft Structures: 2018, Noordwijk, Netherlands

Vancouver

Labans E, Bisagni C. Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures. In ECSSMET 2018: 15th European Conference on Spacecraft Structures: 2018, Noordwijk, Netherlands. 2018

Author

Labans, Edgars ; Bisagni, Chiara. / Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures. ECSSMET 2018: 15th European Conference on Spacecraft Structures: 2018, Noordwijk, Netherlands. 2018.

BibTeX

@inproceedings{3a56185d88dc46a480b0bdd1afc859d8,
title = "Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures",
abstract = "The ability to steer the carbon fibre tape, varying the tow angle can open new designs of cylindrical shells – the main structural component of the space launcher vehicles. This research presents experimental and numerical investigation of two carbon-epoxy cylindrical shells – a cylinder with conventional layup made of unidirectional prepreg and a variable-stiffness cylinder manufactured by applying advanced fibre placement technology. The shells were tested in compression until buckling, measuring load-shortening and capturing the buckling shape by digital image correlation systems. For the purpose of modelling the variable-stiffness cylinder, a simplified stiffness approximation approach was applied. The obtained load-shortening curves and buckling shapes demonstrated good correlation with non-linear numerical models. The results of the investigation contributes to the understanding the phenomenon of buckling of variable-stiffness cylindrical shells, and the influence of initial geometric imperfections and thickness variations.",
author = "Edgars Labans and Chiara Bisagni",
year = "2018",
language = "English",
booktitle = "ECSSMET 2018: 15th European Conference on Spacecraft Structures",

}

RIS

TY - GEN

T1 - Mechanical Response of Variable and Constant-Stiffness Cylindrical Shells for Launcher Structures

AU - Labans, Edgars

AU - Bisagni, Chiara

PY - 2018

Y1 - 2018

N2 - The ability to steer the carbon fibre tape, varying the tow angle can open new designs of cylindrical shells – the main structural component of the space launcher vehicles. This research presents experimental and numerical investigation of two carbon-epoxy cylindrical shells – a cylinder with conventional layup made of unidirectional prepreg and a variable-stiffness cylinder manufactured by applying advanced fibre placement technology. The shells were tested in compression until buckling, measuring load-shortening and capturing the buckling shape by digital image correlation systems. For the purpose of modelling the variable-stiffness cylinder, a simplified stiffness approximation approach was applied. The obtained load-shortening curves and buckling shapes demonstrated good correlation with non-linear numerical models. The results of the investigation contributes to the understanding the phenomenon of buckling of variable-stiffness cylindrical shells, and the influence of initial geometric imperfections and thickness variations.

AB - The ability to steer the carbon fibre tape, varying the tow angle can open new designs of cylindrical shells – the main structural component of the space launcher vehicles. This research presents experimental and numerical investigation of two carbon-epoxy cylindrical shells – a cylinder with conventional layup made of unidirectional prepreg and a variable-stiffness cylinder manufactured by applying advanced fibre placement technology. The shells were tested in compression until buckling, measuring load-shortening and capturing the buckling shape by digital image correlation systems. For the purpose of modelling the variable-stiffness cylinder, a simplified stiffness approximation approach was applied. The obtained load-shortening curves and buckling shapes demonstrated good correlation with non-linear numerical models. The results of the investigation contributes to the understanding the phenomenon of buckling of variable-stiffness cylindrical shells, and the influence of initial geometric imperfections and thickness variations.

M3 - Conference contribution

BT - ECSSMET 2018: 15th European Conference on Spacecraft Structures

ER -

ID: 47725420