Advanced ceramic matrix composite materials for current and future propulsion technology applications

Schmidt, Stephan; Beyer, Steffen; Knabe, H.; Immich, H.; Meistring, R.; Gessler, A.

doi:10.1016/j.actaastro.2004.05.052

Cited by 531 publications

(176 citation statements)

References 2 publications

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“…At Astrium, nozzle extensions made of SICARBON R have been developed for upper-stage (scale 1:1) and main-stage (scale 1:5) engines and successfully tested under real space conditions. Further test campaigns with radiation-cooled combustion chambers were carried out in the ¦eld of satellite propulsion, whereby the SICARBON R material was able to demonstrate its long-term stability and high chemical compatibility vs. the propellants and combustion products in hot-¦ring tests carried out at sea level conditions [10] (Fig. 9).…”

Section: Nozzle Technologiesmentioning

confidence: 99%

“…The work packages of DLR Institute of Space Propulsion include the e¨usion-cooled C/C liner and throat technology which has been developed over the last ten years in cooperation with the DLR Institute of Structures and Design, a propellant injection system which relies on a porous face plate and simple oxidizer holes, quali¦cation test of all components and subsystems as well as the ¦nal ceramic thrust chamber assembly test at the high pressure facility P8 [1,37,9,1315]. Within the project, the most critical issues, adjustment of material properties to the local cooling needs, proof of reproducibility and robustness of design methodology and production processes and leakages and, most important, development and validation of scaling laws will be dealt with.…”

Section: Introductionmentioning

confidence: 99%

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Development of technologies for a CMC-based combustion chamber

Haidn¹,

Riccius²,

Suslov³

et al. 2009

Progress in Propulsion Physics

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Within the ¢Propulsion 2010£ Memorandum of Understanding (MoU) which was signed in 2006, Astrium and DLR agreed to work jointly on Ceramic Matrix Composite (CMC) materials and related technologies with the aim to have ¦nally within the next three years all components and subsystems available for an entirely CMC-based thrust chamber assembly. Hence, propellant injection, combustion chamber liner, and appropriate cooling technologies as well as CMC nozzle parts will be developed and tested within the years to come. The paper reports the current status and focuses on propellant injection applying a porous face plate, heat and mass transfer within and along an e¨usion-cooled porous combustion chamber liner and design and heat transfer issues of a cooled thrust nozzle.

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Section: Nozzle Technologiesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development of technologies for a CMC-based combustion chamber

Haidn¹,

Riccius²,

Suslov³

et al. 2009

Progress in Propulsion Physics

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“…Ceramic matrix composites (CMCs) such as C/SiC have emerged as a novel strategic structure material in various industry areas such as astronautics, automobile and nuclear energy [1]. However, due to the existence of hard ceramic matrix, CMCs are regarded as typical difficult-to-machine materials.…”

Section: Introductionmentioning

confidence: 99%

Preliminary Investigation on Rotary Ultrasonic Face Milling of Ceramic Matrix Composite C/Sic: Design of Experiments

Wang¹,

Zhang²,

Feng³

2017

Proceedings of the 2017 International Conference on Mechanical, Electronic, Control and Automation Engineering (MECAE 2017)

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Abstract. The feasibility of rotary ultrasonic face milling (RUFM) of ceramic matrix composites was evaluated experimentally in this study. Preliminary experimental results show that, comparing with conventional grinding (CG), RUFM can reduce cutting forces dramatically though with a little enlargement of surface roughness. Both in CG and RUFM, a positive dependency of surface roughness on cutting force can be deduced. For machining of 2D-C/SiC composites, the fiber direction significantly affects the cutting force and surface roughness. When fibers are parallel to the cutting plane, the cutting force and surface roughness are much larger than that when fibers are perpendicular to the cutting plane.

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“…The scope ranges from the nozzle design, flow field interactions, shock wave-boundary layer interactions, base drag and advanced concepts for these investigations. For example, in Europe, high area ratio concept is gaining strength for future engines, therefore is investigated to par with the requirements [1]. The performance is highly dependent on the aerodynamic design of the expansion nozzle, the main parameters being the area ratio and length to diameter ratio [2].…”

Section: Introductionmentioning

confidence: 99%