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首页> 外文会议>56th International Astronautical Congress 2005 vol.6 >A DESIGN APPROACH OF CMC RAM-COMBUSTOR WALL
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A DESIGN APPROACH OF CMC RAM-COMBUSTOR WALL

机译：CMC RAM-燃烧室壁的设计方法

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摘要

Ceramic matrix composite (CMC) is a candidate material for the combustor wall of a conceptual RAM jet engine studied in Japan Aerospace Exploration Agency (JAXA). The application, two-stage to orbit (TSTO) type future launch vehicle, may enable an orbital access with improved pay-load capacity of reduced cost through utilizing atmospheric oxygen at the first stage hypersonic flight. The RAM-jet operation has been estimated to complete in limited time, and the reusability maybe commercially acceptable with some ten times. Then, the lifetime of CMC RAM-combustor wall may be acceptable within only few hours, which enables the design standard focus less on the time-dependent factors such as creep and high-cycle fatigue. Distribution in the strength, however, remains a negative factor for the engineering design of CMC components. In this work, SA-Tyrannohex™ SiC/SiC CMC (UBE Industry Co.) was selected as a candidate material for the RAM-combustor wall panel due to the reported excellent performance in high temperature. The strength data of the reinforcement fibers was used in the strength distribution assessment to avoid the high-cost of the CMC component fracture test. The strength distribution leads to a safety margin on the tensile strength of the panels.
机译：陶瓷基复合材料（CMC）是日本航空航天局（JAXA）研究的概念RAM喷气发动机燃烧室壁的候选材料。该应用为两级入轨（TSTO）型未来发射飞行器，可以通过在第一级高超音速飞行中利用大气氧气来实现具有降低的成本的改善的有效载荷能力的轨道进入。据估计，RAM喷射操作将在有限的时间内完成，并且可重复使用性在商业上可以接受大约十次。然后，CMC RAM燃烧器壁的寿命仅在几个小时之内就可以接受，这使设计标准不再关注与时间有关的因素，例如蠕变和高周疲劳。但是，强度分布仍然是CMC组件工程设计的不利因素。在这项工作中，由于报道了高温下的优异性能，SA-Tyrannohex™SiC / SiC CMC（UBE工业公司）被选作RAM燃烧器壁板的候选材料。增强纤维的强度数据用于强度分布评估，以避免CMC组件断裂测试的高成本。强度分布导致面板抗拉强度的安全裕度。

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