Thermo-structural design of a Ceramic Matrix Composite wing leading edge for a re-entry vehicle

Author:

Ferraiuolo Michele,Scigliano Roberto,Riccio AnielloORCID,Bottone Emanuele,Rennella Marco

Publisher

Elsevier BV

Subject

Civil and Structural Engineering,Ceramics and Composites

Reference32 articles.

1. Fossati FA, et al. Enabling technologies for hot structures of next generation RLV's – The asa program summary, In: 61th International Astronautical Congress 2010.

2. Aerothermal response of ceramic matrix composites to nitrogen plasma at temperatures above 2000 K;Panerai;Aerosp Sci Technol,2014

3. Damage characteristics and constitutive modeling of the 2D C/SiC composite: part I – experiment and analysis;Li;Chin J Aeronaut,2014

4. Damage characteristics and constitutive modeling of the 2D C/SiC composite: part II – material model and numerical implementation;Li;Chin J Aeronaut,2015

5. Multi-scale constitutive modeling of Ceramic Matrix Composites by Continuum Damage Mechanics;Shojaei;Int J Solids Struct,2014

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