Abstract
This paper presents an extensive experimental campaign carried out, in the framework of the Horizon2020 project C3HARME, for the characterization of a new class of Ultra-High-Temperature Ceramic Matrix Composite (UHTCMC) materials for Thermal Protection Systems (TPS) of hypersonic vehicles. Eight different material formulations, all based on an Ultra-High-Temperature Ceramic (UHTC) matrix and carbon fiber reinforcement, but with slightly different compositions, fiber architectures and densification techniques, were tested in the arc-jet wind tunnel L3K at DLR in Cologne (Germany), in different configurations, according to an upscaling logic. First, flat button-shaped samples, with a diameter of 50 mm, were tested in a stagnation point configuration, reproducing conditions typical of atmospheric re-entry. These tests were divided into three phases to match different aerothermodynamic requirements extracted by a reference re-entry mission: 1) tests at nominal heat flux (around 2 MW/m2) and pressure below specification; 2) tests at nominal pressure (around 70 kPa) and heat flux above specification; 3) reusability tests at nominal heat flux. The most promising materials were then upscaled in order to manufacture and test a complete TPS assembly, with a large UHTCMC tile (240x190x4 mm3) and UHTCMC integration elements. The assemblies survived repeated tests without damage nor relevant erosion, thus achieving the objective Technology Readiness Level of 5.
Original language | English |
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Journal | Proceedings of the International Astronautical Congress, IAC |
Volume | 2020-October |
Publication status | Published - 2020 |
Event | 71st International Astronautical Congress, IAC 2020 - Virtual, Online Duration: 12 Oct 2020 → 14 Oct 2020 |
Bibliographical note
Funding Information:The C3HARME research project has received funding by the European Union's Horizon2020 research and innovation programme under the Grant Agreement n? 685594.
Funding Information:
The C3HARME research project has received funding by the European Union’s Horizon2020 research and innovation programme under the Grant Agreement n° 685594.
Publisher Copyright:
© 2020 by the International Astronautical Federation (IAF). All rights reserved.
Copyright:
Copyright 2021 Elsevier B.V., All rights reserved.
Keywords
- Arc-jet wind tunnel test
- Near-zero ablation
- Stagnation tests
- TPS assemblies
- Ultra-high temperature ceramic matrix composites
ASJC Scopus subject areas
- Aerospace Engineering
- Astronomy and Astrophysics
- Space and Planetary Science