| 夏吝时,杨凯威,孔维宣,景昭,邹样辉,杨驰.金属尖化前缘模型主动式热疏导性能试验研究[J].装备环境工程,2017,14(10):82-86. XIA Lin-shi,YANG Kai-wei,KONG Wei-xuan,JING Zhao,ZOU Yang-hui,YANG Chi.Experimental Study on the Active Heat Transfer Performance for Leading Edges of Metallic Model[J].Equipment Environmental Engineering,2017,14(10):82-86. |
| 金属尖化前缘模型主动式热疏导性能试验研究 |
| Experimental Study on the Active Heat Transfer Performance for Leading Edges of Metallic Model |
| 投稿时间：2017-05-31 修订日期：2017-10-15 |
| DOI：10.7643/issn.1672-9242.2017.10.016 |
| 中文关键词: 主动式热疏导 高温液态合金 尖化前缘 仿形加热器 |
| 英文关键词:active heat transfer high temperature liquid alloy leading edge profiled heater |
| 基金项目:中国运载火箭技术研究院2016年创新基金课题“高超声速飞行器端头/尖化前缘主动式热防护技术研究” |
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| Author | Institution |
| XIA Lin-shi | Hypersonic Vehicle Thermal Protection & Insulation Technology Center, Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
| YANG Kai-wei | Hypersonic Vehicle Thermal Protection & Insulation Technology Center, Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
| KONG Wei-xuan | Hypersonic Vehicle Thermal Protection & Insulation Technology Center, Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
| JING Zhao | Hypersonic Vehicle Thermal Protection & Insulation Technology Center, Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
| ZOU Yang-hui | Hypersonic Vehicle Thermal Protection & Insulation Technology Center, Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
| YANG Chi | Hypersonic Vehicle Thermal Protection & Insulation Technology Center, Beijing Institute of Space Long March Vehicle, Beijing 100076, China |
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| 中文摘要: |
| 目的 为了更好地解决高超声速飞行器舵、翼前缘及头锥等气动热环境恶劣区域的热防护问题。方法 采用主动式热疏导技术，以高温液态合金为工质，设计并制作具有主动式热疏导功能的尖化前缘金属试验模型（R=5 mm）。根据模型外尺寸设计加工一套石英灯仿形加热器和热流测试模型，开展地面热环境模拟试验。结果 试件在前缘中心温度530 ℃左右时具有瞬态启动特性。前缘中心和大面积中心最大辐射热流密度分别为1000 kw/m2和580 kw/m2，试件在该环境中长时间受热状态下仍具有较好的热疏导能力。试验后试件无工质泄漏和结构破坏，具有一定的可重复使用性。结论 可以此热疏导方式结合现有成熟热防护技术进一步开展工程设计与应用。 |
| 英文摘要: |
| Objective To solve the thermal protection of hypersonic vehicle rudder and wing leading edge and nosecones, etc, in severe aerodynamic thermal environment. Methods A metallic experimental model of the R=5 mm leading edge was designed and fabricated with high temperature liquid alloy according to the active heat transfer technology. A set of profiled quartz lamp heater and heat flux test model was designed and manufactured to carry out thermal environment simulation test on thermal environment on the ground. Results The metallic experimental model had transient start characteristics at 530℃ of leading edge center. The maximum radiant heat flux at the center of the leading edge and the surface was 1000 kw/m2 and 580 kw/m2 respectively. The model had the advantages of good heat conduction ability. The specimen had no medium leakage and structure damage after test, they had certain repeatability. Conclusion It can be used to further engineering design and application in combination with existing mature thermal protection technology. |
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