Details
| Original language | English |
|---|---|
| Publication status | Published - 1993 |
| Externally published | Yes |
| Event | AIAA/DGLR 5th International Aerospace Planes and Hypersonics Technologies Conference, 1993 - Munich, Germany Duration: 30 Nov 1993 → 3 Dec 1993 |
Conference
| Conference | AIAA/DGLR 5th International Aerospace Planes and Hypersonics Technologies Conference, 1993 |
|---|---|
| Country/Territory | Germany |
| City | Munich |
| Period | 30 Nov 1993 → 3 Dec 1993 |
Abstract
The feasibility of future aerospace vehicles depends on advanced structured concepts to achieve sufficient mechanical load capacity combined with high resistance against strong heat fluxes and large temperature gradients. Experiments on metallic structures such as I thermal protection system, hot load carrying panels, and a wing box were carried out in DLR test facilities within the temperature m g e up to 1000 °C. As an alternative to metals, fiber-reinforced polymers and glasses for applications under moderate and/or cryogenic temperatures and under steep temperature gradients were also investigated. Complementary to this technological, and experimented approach, corresponding numerical procedures have been published. Analytical and numerical methods deriving thermal conductivities and the and elongations of laminates from the fiber and matrix properties were validated. Special Finite Elements based on thermal lamination theories have been developed to analyse efficiently the temperature field of multi-directional laminates.
ASJC Scopus subject areas
- Engineering(all)
- Aerospace Engineering
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1993. Paper presented at AIAA/DGLR 5th International Aerospace Planes and Hypersonics Technologies Conference, 1993, Munich, Germany.
Research output: Contribution to conference › Paper › Research › peer review
}
TY - CONF
T1 - Investigations on thermally resistant structures for future aerospace vehicles
AU - Block, J.
AU - Frövel, M.
AU - Klein, H.
AU - Rolfes, R.
AU - Schmidt, K.
AU - Twardy, H.
AU - Petersen, D.
PY - 1993
Y1 - 1993
N2 - The feasibility of future aerospace vehicles depends on advanced structured concepts to achieve sufficient mechanical load capacity combined with high resistance against strong heat fluxes and large temperature gradients. Experiments on metallic structures such as I thermal protection system, hot load carrying panels, and a wing box were carried out in DLR test facilities within the temperature m g e up to 1000 °C. As an alternative to metals, fiber-reinforced polymers and glasses for applications under moderate and/or cryogenic temperatures and under steep temperature gradients were also investigated. Complementary to this technological, and experimented approach, corresponding numerical procedures have been published. Analytical and numerical methods deriving thermal conductivities and the and elongations of laminates from the fiber and matrix properties were validated. Special Finite Elements based on thermal lamination theories have been developed to analyse efficiently the temperature field of multi-directional laminates.
AB - The feasibility of future aerospace vehicles depends on advanced structured concepts to achieve sufficient mechanical load capacity combined with high resistance against strong heat fluxes and large temperature gradients. Experiments on metallic structures such as I thermal protection system, hot load carrying panels, and a wing box were carried out in DLR test facilities within the temperature m g e up to 1000 °C. As an alternative to metals, fiber-reinforced polymers and glasses for applications under moderate and/or cryogenic temperatures and under steep temperature gradients were also investigated. Complementary to this technological, and experimented approach, corresponding numerical procedures have been published. Analytical and numerical methods deriving thermal conductivities and the and elongations of laminates from the fiber and matrix properties were validated. Special Finite Elements based on thermal lamination theories have been developed to analyse efficiently the temperature field of multi-directional laminates.
UR - http://www.scopus.com/inward/record.url?scp=84983143548&partnerID=8YFLogxK
U2 - 10.2514/6.1993-5086
DO - 10.2514/6.1993-5086
M3 - Paper
T2 - AIAA/DGLR 5th International Aerospace Planes and Hypersonics Technologies Conference, 1993
Y2 - 30 November 1993 through 3 December 1993
ER -