The influence of a tension load on the behavior of laminates subjected to torsion was evaluated through test and analysis. Nine different 32-ply glass-epoxy laminates, typical of flexbeams in helicopter rotor systems, were tested under torsion and combined tension-torsion. The laminate configurations consisted of 30 45 or 60 deg of angle plies located between 0 deg of angle sublaminates. Superposing a tension load increased both the torsional load required to twist to a given angle and the torsional load to failure. An increase in the torsional load for a given twist increases the control load to the helicopter rotor system. All failures initiated with through-the-thickness shear cracks at the free edge, followed by deliminations. The failure locations depended on the load and the laminate configuration. The laminate layups are compared to determine the design efficiency with respect to the control loads required for, and the residual strength remaining following, a given twist angle.
The influence of a tension load on laminates under torsion
Der Einfluß einer Zugbelastung auf das Werkstoffverhalten von Laminaten unter Torsion im Hinblick auf deren Verwendung für Hubschrauber-Rotorblätter
Forum, Annual Forum, American Helicopter Society, 50 ; 2 ; 1017-1027
1994
11 Seiten, 14 Bilder, 12 Quellen
Conference paper
English
The Influence of Tension Load on Laminates under Torsion
British Library Conference Proceedings | 1994
|The influence of a tension load on laminates under torsion
Tema Archive | 1995
|The Influence of a Tension Load on Laminates Under Torsion
Online Contents | 1995
|COMPOSITE TENSION-TORSION LOAD CELL
British Library Conference Proceedings | 2003
|