Axial and radial compression behavior of composite rocket launcher developed by robotized filament winding: Simulation and experimental validation

Journal Article (Journal Article)

The principal objective of the work is to compare among carbon-glass filament wound epoxy matrix hybrid composites with a different fiber ratio made by robotized winding processes and optimize the geometry suitable for the Rocket Propelled Grenade Launcher. ANSYS based finite element analysis was used to predict the axial as well as radial compression behavior. Experimental samples were developed by a robot-controlled filament winding process that was incorporated with continuous resin impregnation. The experimental samples were evaluated for the corresponding compressional properties. Filament wound tubular composite structures were developed by changing the sequence of stacking of hoop layers and helical layers, and also by changing the angle of wind of the helical layers while keeping the sequence constant. The samples were developed from carbon and glass filaments with different carbon proportions (0%, 25%, 50%, 75%, and 100%) and impregnated with epoxy resin. The compressional properties of the tubular composites that were prepared by filament winding were compared with the predicted axial and radial compressional properties from computational modelling using the finite element model. A very high correlation and relatively small prediction error was obtained.

Full Text

Duke Authors

Cited Authors

  • Mishra, R; Behera, BK; Mukherjee, S; Petru, M; Muller, M

Published Date

  • February 2, 2021

Published In

Volume / Issue

  • 13 / 4

Start / End Page

  • 1 - 18

Electronic International Standard Serial Number (EISSN)

  • 2073-4360

Digital Object Identifier (DOI)

  • 10.3390/polym13040517

Citation Source

  • Scopus