Effect of density and fibre orientation on the ablation behaviour of carbon-carbon composites
Source abstract
Abstract
Five carbon-carbon composites were prepared with different fibre orientations in the preform and were densified by different methods. Their ablation behaviour was examined by an oxy-acetylene test and scanning electron microscopy. The densities of the composites were in the range of 1.77 to 1.85 g/cm3. Fibres having an angle of 30° with the oxy-acetylene flame turned into a sharp wedge shape, whereas fibres parallel to the flame had a needle-like shape with diameter up to 3.5–4.5 μm after ablation. The needled fibres were easily attacked and ultimately became blunt. Partially filled macropores with sizes of 1.0–1.26 mm, needle pores, interfacial cracks and gaps in non-woven cloth were easily attacked by the flame, resulting in macroscopic ablation pits that decreased with increasing density of the composites. The needled fibres around pitch carbon layers were severely denuded due to their discontinuity with the pyrolytic carbon matrix. A high density (1.85 g/cm3) composite had an excellent ablation resistance.
Source: expertdata · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Fiber-reinforced polymer composites · Flame retardant materials and properties · Diamond and Carbon-based Materials Research
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (20)
Show source-provided references
1. Applications of carbon/carbon[M]
2. Withers J C, Kowbel W, Loutfy R O. Carbon-Carbon composites in advanced aerospace applications [C]// Proc. Conference on Carbon, American carbon society, UK, 2006.
3. Leonard C P, Amundsen R M, Bruce W E. Hyper X Hot Structures Design and Comparison with Flight Data [C].// Proc. 13th AIAA/CIRA International Space Planes and Hypersonics Systems and Technologies Conference, 2005, AIAA-2005-3438.10.2514/6.2005-3438 ↗
4. Berdoyes M. Snecma propulsion solide advanced technology SRM nozzles. History and future [C]// Proc. Proceedings of the 42nd joint propulsion conference and exhibit, Sacramento, CA, US, 2006, AIAA 2006-4596.10.2514/6.2006-4596 ↗
5. Couzi J, de Winne J, Leroy B. Improvements in ablation predications for reentry vehicle nosetip[C]// Proc 3rd Eur Symposium on Aerothermodynamics for Space Vehicle. ESA, Noodwijk, the Netherlands, 1998: 493–499.
6. D'Aleio · 1971
7. Microscopic observations of the ablation behaviours of carbon fibre/phenolic composites [J]10.1007/BF00882533 ↗
8. Oxidation and ablation of 3D carbon-carbon composite at up to 3 000• • [J]10.1016/0008-6223(94)00172-V ↗
9. Application and development of C/C nozzle with high specific thrust rate [J]
10. Carbon-carbon composites [J]
11. Progress on the oxidation protective coating of carbon-carbon composites [J]
12. Investigation on ablation behavior of CFRC composites prepared at different pressure [J]10.1016/j.compositesa.2004.03.024 ↗
13. Influence of microstructure of pyrocarbon on ablation performances of C/C composites [J]
14. Microstructure and ablation properties of zirconium carbide doped carbon/carbon composites [J]10.1016/j.carbon.2009.09.035 ↗
15. Effect of HfC on the ablative and mechanical properties of C/C composites[J]
16. Microstructural interpretation of the effect of various matrices on the ablation performances of carbon-fiber-reinforced composites [J]10.1016/S0266-3538(00)00212-8 ↗
17. RAN Hong-xing, CUI Hong, HAO Zhi-biao, et al. Influence of carbon-matrix structure on anyiablative performances[C]//Proceedings of the 12th National Symposium on Composites, 2002: 563–566.
18. Microstructure and ablation performance of dual-matrix carbon/carbon composites [J]10.1016/j.carbon.2006.01.017 ↗
19. Ablation performance of C/C composites with different performs[J]
20. A novel thermal gradient chemical vapor infiltration process for carbon-carbon composites [J]10.1016/S1872-5805(07)60020-1 ↗