Abstract
One of the most significant problems in the processing of composite materials is residual stresses. The residual stresses may be high enough to cause cracking in the matrix even before external loads are applied and can degrade the integrity of composite structures. In this study, thermo-viscoelastic residual stresses occurred in the aluminum liner-inserted polymer composite cylinder are investigated. This type of a structure is used for the rocket fuselages due to its convenience to attach payloads and equipment to the metal liner by machining. The time and degree of cure dependent thermo-viscoelastic constitutive equations are developed and coupled with a thermo-chemical process model. These equations are solved with the finite element method to predict the residual stresses in the composite cylinder and also in the interface between the liner and the composite during cure.
| Original language | English |
|---|---|
| Pages (from-to) | 2469-2476 |
| Number of pages | 8 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 4 |
| State | Published - 2001 |
| Event | 42nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, amd Materials Conference and Exhibit Technical Papers - Seattle, WA, United States Duration: 16 Apr 2001 → 19 Apr 2001 |