首页> 外文会议>International Astronautical Congress >Design and Thermo-Structural Analysis of the Interface between Subscale Versions of Carbon-Carbon (C-C) Nozzle Divergent to Metallic flange hardware for a Ground Simulation Test
【24h】

Design and Thermo-Structural Analysis of the Interface between Subscale Versions of Carbon-Carbon (C-C) Nozzle Divergent to Metallic flange hardware for a Ground Simulation Test

机译:碳 - 碳(C-C)喷嘴段界面界面的设计与热结构分析,用于地面模拟试验的金属法兰硬件

获取原文

摘要

Carbon-carbon and carbon fiber reinforced materials are promising materials for use in space applications, due to their excellent thermal and mechanical properties. Carbon-carbon (C-C) is the material which is having lower density and lower coefficient of thermal expansion compared to metals under higher temperature environment. Their dimensional stability, low outgassing and insignificant change in mechanical properties at elevated temperatures make C-C as ideal candidate for various space structural applications especially the throat and divergent of Nozzle in the Solid Motor. Carbon-carbon nozzle divergent extension with supersonic film cooling provides performance improvement and ultimately payload gain. To demonstrate the performance of supersonic film cooling concept with 2-D carbon-carbon nozzle divergent, a sea level static test was conducted with a lesser Aluminium fuel content in a sub scale Solid Motor simulating the flow condition closer to that of liquid engine. The motor was configured w ith 17 area ratio nozzle (metallic configuration up to area ratio 10 and remaining per as C-C). A supersonic injection module was used to inject gaseous hydrogen at 2 bar pressure through the conduit mounted at AR10. Design of the C-C divergent to metallic fanged joint was carried out according the preload capability of the joint at higher temperature for a 10 sec burn time. Thermo structural analysis of this set up was carried out using the temperature distribution from the thermal analysis. Loads were applied in these load steps viz., i) Preload ii) varying temperature at 10 sec and iii) varying internal pressure. This paper covers the details of the thermo structural analysis and the results viz., preload loss, final bolt stress, O-ring compression, stresses in the C-C and metallic flange, gap opening at Hydrogen injection point etc. and also covered the details of the post test inspection.
机译:碳 - 碳和碳纤维增强材料是有希望用于太空应用的材料,因为它们具有优异的热和机械性能。与在较高温度环境下的金属相比,碳 - 碳(C-C)是具有较低密度和较低的热膨胀系数的材料。其尺寸稳定性,升高温度下的机械性能低,使C-C为各种空间结构应用的理想候选,尤其是固体电机中喷嘴的喉部和发散。碳 - 碳喷嘴具有超音速薄膜冷却的发散延伸提供性能提高,最终有效载荷增益。为了证明用2-D碳 - 碳喷嘴发散的超音速膜冷却概念的性能,通过较小的铝燃料含量在亚级固体电动机中进行海平静态试验,模拟更靠近液体发动机的流动状态。电机配置了17个面积比喷嘴(金属配置直至面积比10,并且剩余的每C-C)。超声波喷射模块用于通过安装在AR10处的导管在2巴压力下喷射气态氢气。根据接头的预载能力在较高温度下进行10秒燃烧时间,对金属传递接头进行分歧的设计。使用热分析的温度分布进行该设置的热结构分析。在这些负载步骤Viz中施加负载,i)预载II)在10秒和III的不同温度下变化的内部压力。本文涵盖了热结构分析的细节和结果viz。,预加载损耗,最终螺栓应力,O形圈压缩,CC和金属法兰的应力,氢注射点处的间隙开口等后测试检查。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号