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Thermo-Structural Analysis and Failure Behavior of C/C Composite Throat

Author: ZhengQuan
Tutor: MengSongHe
School: Harbin Institute of Technology
Course: Engineering Mechanics
Keywords: Nozzle throat insert Carbon / carbon materials Thermal structure analysis Failure behavior
CLC: TB332
Type: Master's thesis
Year: 2011
Downloads: 85
Quote: 0
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Abstract

Nozzle throat insert is one of the key components of the solid rocket motor to withstand the high temperature and pressure, solid particle erosion, as well as high-temperature gas thermochemical erosion. The poor working conditions of a serious impact on the safety of the parts of the throat lining, the hose lining parts of the security of the solid rocket motor whether the normal security is critical. In this paper, as the research object, using the ABAQUS finite element software, established a solid rocket motor carbon / carbon composite nozzle throat insert under the influence of the thermal contact resistance, ablation moving boundary and interfacial debonding throat thermal structure calculation method reveals decision throat failure of key factors, the failure behavior of the throat. This article first components of the throat temperature field analysis. Were considered in the calculation of the thermal contact resistance and ablation moving boundary two influencing factors, analyze their impact on the temperature field. The results show that the thermal contact resistance greater than 1 × 10 ^{-4 m ^{2 · ° C / W a greater impact on the temperature field, must be taken into account in the calculation of the thermal contact resistance . , The temperature field is not obvious when the thermal contact resistance of less than 1 × 10 ^{-4 m ^{2 · ℃ / W, can be ignored in the calculation of the thermal contact resistance the impact. Ablation temperature distribution on the the throat lining the inner wall of the moving boundary, but have a greater impact on the throat lining the outer wall temperature distribution, and with the increase in working hours, more and more obvious impact. Finally, the combination of these two influencing factors calculated by the throat temperature field component in a complex environment. Secondly, on the basis of results of the temperature field is known, the use of sequential coupling method to calculate the stress field of the throat assembly. Analysis of the impact of the thermal contact resistance and ablation moving boundary corresponding force field, and consider the throat insert in the the interfacial debonding sticky case distribution of stress field, off the hose lining parts of stick before and after radial and axial stress extremal characteristics. The results show that the thermal contact resistance corresponding force field is consistent with the conclusion influence on the temperature field; ablation moving boundary on the the throat lining the outer wall of the radial and axial stress greater impact and ablation moving boundary radial stress Throat The impact is significantly higher than the axial. Comprehensive impact of various factors, calculated throat stress field in a complex environment. The results show that: the end of radial tensile stress of 88MPa, the compressive stress of 189MPa; axial tensile stress of 71 MPa compressive stress of 144MPa. Finally, on the basis of the analysis of temperature and stress field, using the extended finite element method failure behavior of initial damage to the throat. The results show that the throat will appear in the role of thermal stress fracture failure; throat compression expansion segment will lead to the expansion of the segment overall fracture; interfacial debonding phenomenon will lead to a narrow gap between the throat and the back wall, Throat contact with the expansion section staggered. The failure mode of the component structure of the solid rocket motor throat design and material selection has some practical value.}}}}

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