Study on Impact Resistance of C/SiC Ceramic Matrix Composites for Thermal Protection of the Aerospace Vehicle

Ye Lin,Bin Liu,Chengwei Fei

doi:10.1155/2021/6255014

Ye Lin, Bin Liu + Show 1 more

Open Access

https://doi.org/10.1155/2021/6255014

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Abstract

This paper evaluates the impact damage tolerance of ceramic matrix composites and contrasts their tensile and compression strengths under impact and nonimpact conditions. The representative C/SiC composites from PIP are examined under the dropped tip system. In this paper, the surface impact test of C/SiC composites is carried out. By testing a series of specimens of various impact energies, the tensile and compression properties after impact are studied. Meanwhile, by comparing the changes of the specimens after impact and nonimpact, the fracture process, fracture modes, and residual strength are investigated. The results indicate that the residual tensile strength after impact reduces greatly, compared with the nonimpact material, by about 25%–45%, while the compression strength reduces slightly. The residual strength of tension and compression illustrates that low-energy impact effect on the structural integrity must be given priority in the thermal protection structure design of astronautics and aeronautics.

Highlights

Ceramic matrix composites have been successfully used in high-temperature components in aerospace due to their excellent strength of high temperature, low density, good oxidation resistance, and wear resistance
Poor performance caused by foreign object damage (FOD)
With the increase of impact energy, the impact damage volume from both front and back of the specimen was increasingly serious. e impact damage dimension matrix for the two groups can be described in Tables 1 and 2

Summary

Introduction

Ceramic matrix composites have been successfully used in high-temperature components in aerospace due to their excellent strength of high temperature, low density, good oxidation resistance, and wear resistance. By applying in scramjets, C/SiC composite material can simplify the structure, reduce the weight, and significantly improve the comprehensive performance of the engine and the payload of the aircraft. It has become one of the pivotal high-temperature-resistant materials for the thermal protection structure of the hypersonic aircraft in nearby space [1, 2]. With the urgent demand of high thrustto-weight ratio and high working temperature for aeroengines, ceramic matrix composites are gradually used as hotend components of aeroengines, such as blades.

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