Fabrication and Ablation Studies of 4D C/SiC Composite Nozzle Under Liquid Propulsion

Abstract

4D C/SiC composite nozzle was fabricated using LSI and characterized for mechanical, thermal, and ablation properties. Average flexural and compressive strengths in the Z-direction were found to be 119 and 110 MPa, while in the U-, V-and W-directions, they were 99 and 55MPa, respectively. Coefficient of thermal expansion was found to be varied in the range 0-1.5 9 10 À6 /°C (25-1050°C), while thermal diffusivity was 40-5 mm 2 /s (25-1200°C). Ablation behavior of the nozzle was evaluated under UH25/N 2 O 4 propulsion system for 30 s. The overall mass erosion rate and the linear ablation rate were found to be 0.119 kg/m 2 s and 0.05 mm/s, respectively.

Polycarbosilane based UD C/SiC composites: Effect of in-situ grown SiC nano-pins on mechanical properties

“…CTE of the carbon fiber along the axis is 0-1 Â 10 À 6 /K while in the radial direction it is about 9 Â 10 À 6 /K. Therefore, during pyrolysis and cooling, the composite have non-uniform shrinkage due to the CTE mismatch between Carbon fiber and SiC [4,26,27]. Although, these micro-cracks get filled to an extent during the subsequent infiltration/pyrolysis cycles, but, still some pores remain unfilled (Fig.…”

“…These composites can be prepared by chemical vapor infiltration (CVI), reaction bonding, hot pressing and polymer impregnation and pyrolysis (PIP) process [1][2][3][4]. A number of studies have been carried out by many researchers on the use of the polymer derived ceramics precursors (PDC), for the SiC, SiNC and SiOC based ceramics [5].…”

SiC-Based Composites Through Liquid Infiltration Routes

“…Carbon fiber-reinforced composites had been designed for limited life due to limitation of carbonaceous material under oxidizing environmental conditions which prevail in aerospace and defense products. The most recognized applications of these materials were rocket nozzles, throat inserts, jet-vanes, engine flaps, leading edges of the spacecraft, and brake disks of an aircraft [1][2][3][4][5]. Service duration of these components varies from few seconds (jet-vanes) to several hours (brake disks) under the specified and stringent conditions which call the stability of the C/SiC composites at the highest thermomechanical loads [1][2][3][4][5].…”

“…The most recognized applications of these materials were rocket nozzles, throat inserts, jet-vanes, engine flaps, leading edges of the spacecraft, and brake disks of an aircraft [1][2][3][4][5]. Service duration of these components varies from few seconds (jet-vanes) to several hours (brake disks) under the specified and stringent conditions which call the stability of the C/SiC composites at the highest thermomechanical loads [1][2][3][4][5]. Considering the oxidation resistance and service time requirement of these composites for the mentioned applications, several studies were carried out at different leading research laboratories across the world on replacing the carbon matrix by ceramic matrix, by oxidation protection coating on the carbon composite, and by modifying the matrix composition by adding refractory metals and ceramics [1][2][3][4][5].…”

Design, Manufacture, and Characterization of a Carbon Fiber‐Reinforced Silicon Carbide Nozzle Extension

“…Also, most tape‐wound structures use thermoplastic resins, whereas for C/C‐SiC materials in this study, phenolic precursors are required to produce the desired microstructure to provide good mechanical performance. Another recent example of carbon fiber‐reinforced silicon carbide composite nozzle material was presented by Kumar et al . In contrast to the material presented by Kumar et al ., which showed a rather high material density of about 2.3 g/cm and a lower overall mechanical performance due to carbon fiber degradation during siliconization, the presented C/C‐SiC material in this study provides an improved microstructure suitable for highly mechanically loaded CMC nozzle structures.…”