新型耐烧蚀涂层防隔热性能
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兰州空间技术物理研究所

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钱蕴,1984 年出生,工程师,主要从事固体火箭发动机外防热材料研究。

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Thermal Protection Properties of An Innovative Ablation-Resistant Coating
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    摘要:

    介绍了一种新型发动机用外防热材料,该防热材料在短时间高热流的条件下,通过电弧风洞试验 考核,试样的背壁温度可降低至144℃,相较于无涂层试样,背温的降温幅度高于300℃。0. 5 mm 厚涂层与0. 8 mm 厚涂层相比,试样背温并无明显优势。且室温固化涂层比高温固化涂层试样背壁温度低30℃,均低于 234℃,均满足设计指标要求的背壁温度低于350℃的使用需求。

    Abstract:

    This paper presents an innovative thermal protection coating material for solid rocket motors, that was subjected to high heat flux in a short time for arc-heated wind tunnel test. It is observed that the back surface of the coated samples with thermal protection coating can be cooled to 144℃ with a drop of 300℃ at least in comparison with that of the uncoated samples. The results showed that the back temperature of the samples with 0. 5 mm coating was little superior to that in the case of 0. 8 mm coating. Moreover, the back temperature of the coated samples cured at room temperature with a drop of 30℃ by contrast with that of the samples cured at high temperature, and the samples in both cases have the back temperature below 234℃ in accordance with the design value of less than 350℃.

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钱 蕴,张利军,李兴刚,胡润芝,寇朝辉.新型耐烧蚀涂层防隔热性能[J].宇航材料工艺,2014,44(3):69-72.

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  • 收稿日期:2014-02-08
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  • 在线发布日期: 2016-11-28
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第十一届航天复合材料成形与加工工艺技术中心交流会 征文通知

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