Details
| Originalsprache | Englisch |
|---|---|
| Seiten (von - bis) | 135-146 |
| Seitenumfang | 12 |
| Fachzeitschrift | Aerospace science and technology |
| Jahrgang | 5 |
| Ausgabenummer | 2 |
| Publikationsstatus | Veröffentlicht - Feb. 2001 |
| Extern publiziert | Ja |
Abstract
Thermo-mechanical design aspects for primary carbon fibre reinforced plastics (CFRP) components, especially wings, of future large transport aircraft are discussed. Numerical simulations of the heating of a wing under intensive sun irradiation and of cooling during taxiing and take-off result in the recommendation of an appropriate design temperature. The study of flat stringer-stiffened panels reveals the influence of imperfections and boundary conditions on the buckling load under simultaneous thermal and mechanical loading.
ASJC Scopus Sachgebiete
- Ingenieurwesen (insg.)
- Luft- und Raumfahrttechnik
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in: Aerospace science and technology, Jahrgang 5, Nr. 2, 02.2001, S. 135-146.
Publikation: Beitrag in Fachzeitschrift › Artikel › Forschung › Peer-Review
}
TY - JOUR
T1 - Thermo-mechanical design aspects for primary composite structures of large transport aircraft
AU - Petersen, Dieter
AU - Rolfes, Raimund
AU - Zimmermann, Rolf
PY - 2001/2
Y1 - 2001/2
N2 - Thermo-mechanical design aspects for primary carbon fibre reinforced plastics (CFRP) components, especially wings, of future large transport aircraft are discussed. Numerical simulations of the heating of a wing under intensive sun irradiation and of cooling during taxiing and take-off result in the recommendation of an appropriate design temperature. The study of flat stringer-stiffened panels reveals the influence of imperfections and boundary conditions on the buckling load under simultaneous thermal and mechanical loading.
AB - Thermo-mechanical design aspects for primary carbon fibre reinforced plastics (CFRP) components, especially wings, of future large transport aircraft are discussed. Numerical simulations of the heating of a wing under intensive sun irradiation and of cooling during taxiing and take-off result in the recommendation of an appropriate design temperature. The study of flat stringer-stiffened panels reveals the influence of imperfections and boundary conditions on the buckling load under simultaneous thermal and mechanical loading.
KW - Composites
KW - Fuselage
KW - Heat transfer
KW - Structural stability
KW - Thermal analysis
KW - Thermally induced buckling
KW - Thermo-mechanics
KW - Transport aircraft
KW - Wing
UR - http://www.scopus.com/inward/record.url?scp=0035579120&partnerID=8YFLogxK
U2 - 10.1016/S1270-9638(00)01089-0
DO - 10.1016/S1270-9638(00)01089-0
M3 - Article
AN - SCOPUS:0035579120
VL - 5
SP - 135
EP - 146
JO - Aerospace science and technology
JF - Aerospace science and technology
SN - 1270-9638
IS - 2
ER -