Investigations on thermally resistant structures for future aerospace vehicles

verfasst von: J. Block, M. Frövel, H. Klein, R. Rolfes, K. Schmidt, H. Twardy, D. Petersen
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.
Externe Organisation(en): DLR-Institut für Systemleichtbau
Typ: Paper
Publikationsdatum: 1993
Publikationsstatus: Veröffentlicht
Peer-reviewed: Ja
ASJC Scopus Sachgebiete: Luft- und Raumfahrttechnik
Elektronische Version(en): https://doi.org/10.2514/6.1993-5086 (Zugang: Offen)

BibTeX

@conference{b721a2a0e0074366944bc9aa7081159d,
title = "Investigations on thermally resistant structures for future aerospace vehicles",
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.",
author = "J. Block and M. Fr{\"o}vel and H. Klein and R. Rolfes and K. Schmidt and H. Twardy and D. Petersen",
year = "1993",
doi = "https://doi.org/10.2514/6.1993-5086",
language = "English",
note = "AIAA/DGLR 5th International Aerospace Planes and Hypersonics Technologies Conference, 1993 ; Conference date: 30-11-1993 Through 03-12-1993",
}