Details
| Original language | English |
|---|---|
| Pages (from-to) | 725-732 |
| Number of pages | 8 |
| Journal | European Space Agency, (Special Publication) ESA SP |
| Issue number | 581 |
| Publication status | Published - 2005 |
| Event | European Conference on Spacecraft Structures, Materials and Mechanical Testing 2005 - Noordwijk, Netherlands Duration: 10 May 2005 → 12 May 2005 |
Abstract
Thin-walled shell structures like circular cylindrical shells are prone to buckling. Imperfections which are defined as deviations from perfect shape and perfect loading distributions can reduce the buckling load drastically compared to that of the perfect shell. Design criteria monographs like NASA-SP 8007 recommend that the buckling load of the perfect shell shall be reduced by using a knock-down factor. The existing knock-down factors are very conservative. Furthermore, the structural behaviour of composite material is not considered. A new experimental approach to determine the lower bound of the buckling load of thin-walled cylindrical composite shells is presented. Based on test results the numerical analysis is validated.
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
- Earth and Planetary Sciences(all)
- Space and Planetary Science
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In: European Space Agency, (Special Publication) ESA SP, No. 581, 2005, p. 725-732.
Research output: Contribution to journal › Conference article › Research › peer review
}
TY - JOUR
T1 - A new approach for robust design of composite cylindrical shells under axial compression
AU - Hühne, Christian
AU - Rolfes, Raimund
AU - Tessmer, Jan
PY - 2005
Y1 - 2005
N2 - Thin-walled shell structures like circular cylindrical shells are prone to buckling. Imperfections which are defined as deviations from perfect shape and perfect loading distributions can reduce the buckling load drastically compared to that of the perfect shell. Design criteria monographs like NASA-SP 8007 recommend that the buckling load of the perfect shell shall be reduced by using a knock-down factor. The existing knock-down factors are very conservative. Furthermore, the structural behaviour of composite material is not considered. A new experimental approach to determine the lower bound of the buckling load of thin-walled cylindrical composite shells is presented. Based on test results the numerical analysis is validated.
AB - Thin-walled shell structures like circular cylindrical shells are prone to buckling. Imperfections which are defined as deviations from perfect shape and perfect loading distributions can reduce the buckling load drastically compared to that of the perfect shell. Design criteria monographs like NASA-SP 8007 recommend that the buckling load of the perfect shell shall be reduced by using a knock-down factor. The existing knock-down factors are very conservative. Furthermore, the structural behaviour of composite material is not considered. A new experimental approach to determine the lower bound of the buckling load of thin-walled cylindrical composite shells is presented. Based on test results the numerical analysis is validated.
UR - http://www.scopus.com/inward/record.url?scp=28444493363&partnerID=8YFLogxK
M3 - Conference article
AN - SCOPUS:28444493363
SP - 725
EP - 732
JO - European Space Agency, (Special Publication) ESA SP
JF - European Space Agency, (Special Publication) ESA SP
SN - 0379-6566
IS - 581
T2 - European Conference on Spacecraft Structures, Materials and Mechanical Testing 2005
Y2 - 10 May 2005 through 12 May 2005
ER -