Details
| Original language | English |
|---|---|
| Publication status | Published - 2001 |
| Externally published | Yes |
| Event | 19th AIAA Applied Aerodynamics Conference 2001 - Anaheim, CA, United States Duration: 11 Jun 2001 → 14 Jun 2001 |
Conference
| Conference | 19th AIAA Applied Aerodynamics Conference 2001 |
|---|---|
| Country/Territory | United States |
| City | Anaheim, CA |
| Period | 11 Jun 2001 → 14 Jun 2001 |
Abstract
The extend of impact damage in sandwich structures depends on the core material and the stacking sequence of the sandwich skin laminate, the size, mass and velocity of the impactor and on the ability of the component to absorb the shock at the impact point. Because of the complex interaction between these parameters the forecast of the damage and the progress under Tension-Tension (T-T), Tension-Compression (T-C) and Compression- Compression (C-C) fatigue loading is difficult to conduct. Impact damage is most critical, 'when the skin remains intact. Except of a small dent or blister in the skin surface the impacted zone is often barely visible. Nevertheless, the damage may grow under fatigue loading to a critical size, where the component is endangered. In sandwich structures with foam core a delamination will be detected most likely around the impacted zone between skin and core. The damage progress is triggered by the local buckling of the delaminated skin layer. In structures with Honeycomb core delaminations are hardly detected after impact (see Figure I). The core is crumpled in the vicinity of the impacted zone and the elastic support of the skin layers is reduced. Under compressive loading the core shrinks in thickness direction and the skin layer may buckle in core direction.
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
- Engineering(all)
- Mechanical Engineering
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2001. Paper presented at 19th AIAA Applied Aerodynamics Conference 2001, Anaheim, CA, United States.
Research output: Contribution to conference › Paper › Research › peer review
}
TY - CONF
T1 - Impact behavior and residual strength of sandwich structural elements under static and fatigue loading
AU - Gaedke, Michael
AU - Baaran, Jens
AU - Christian Goetting, Hans
AU - Rolfes, Raimund
PY - 2001
Y1 - 2001
N2 - The extend of impact damage in sandwich structures depends on the core material and the stacking sequence of the sandwich skin laminate, the size, mass and velocity of the impactor and on the ability of the component to absorb the shock at the impact point. Because of the complex interaction between these parameters the forecast of the damage and the progress under Tension-Tension (T-T), Tension-Compression (T-C) and Compression- Compression (C-C) fatigue loading is difficult to conduct. Impact damage is most critical, 'when the skin remains intact. Except of a small dent or blister in the skin surface the impacted zone is often barely visible. Nevertheless, the damage may grow under fatigue loading to a critical size, where the component is endangered. In sandwich structures with foam core a delamination will be detected most likely around the impacted zone between skin and core. The damage progress is triggered by the local buckling of the delaminated skin layer. In structures with Honeycomb core delaminations are hardly detected after impact (see Figure I). The core is crumpled in the vicinity of the impacted zone and the elastic support of the skin layers is reduced. Under compressive loading the core shrinks in thickness direction and the skin layer may buckle in core direction.
AB - The extend of impact damage in sandwich structures depends on the core material and the stacking sequence of the sandwich skin laminate, the size, mass and velocity of the impactor and on the ability of the component to absorb the shock at the impact point. Because of the complex interaction between these parameters the forecast of the damage and the progress under Tension-Tension (T-T), Tension-Compression (T-C) and Compression- Compression (C-C) fatigue loading is difficult to conduct. Impact damage is most critical, 'when the skin remains intact. Except of a small dent or blister in the skin surface the impacted zone is often barely visible. Nevertheless, the damage may grow under fatigue loading to a critical size, where the component is endangered. In sandwich structures with foam core a delamination will be detected most likely around the impacted zone between skin and core. The damage progress is triggered by the local buckling of the delaminated skin layer. In structures with Honeycomb core delaminations are hardly detected after impact (see Figure I). The core is crumpled in the vicinity of the impacted zone and the elastic support of the skin layers is reduced. Under compressive loading the core shrinks in thickness direction and the skin layer may buckle in core direction.
UR - http://www.scopus.com/inward/record.url?scp=85067320480&partnerID=8YFLogxK
U2 - 10.2514/6.2001-1222
DO - 10.2514/6.2001-1222
M3 - Paper
AN - SCOPUS:85067320480
T2 - 19th AIAA Applied Aerodynamics Conference 2001
Y2 - 11 June 2001 through 14 June 2001
ER -