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   热防护 在 一般化学工业 分类中 的翻译结果: 查询用时:0.511秒
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热防护
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  thermal protection
Heat and mass transfer associated with low-velocity vapor flow in the plane channel of a thermal protection system of the radiat
      
Characteristics of the heat and mass transfer in evaporative thermal protection with variation of the external pressure
      
A thermal protection system with evaporation into an inner cavity is considered.
      
Modeling the unsteady heat and mass transfer in the vapor outlet channel of a radiative-evaporative thermal protection system
      
Efficiency of a radiative-evaporative aircraft thermal protection system
      
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A new thermal protection coating for supersonic aircrafts was studied in this paper. The performance of the coating was determined. Then, properties of a silicone modified epoxy resin, which was used as matrix, were studied, and fillers which can improve mechanical and thermal insulation properties of the coating were selected. Finally, properties of the coating were completely studied. Results indicate that the tensile strength and elongation at break of the silicone modified epoxy resin are 9.38MPa and 16%,...

A new thermal protection coating for supersonic aircrafts was studied in this paper. The performance of the coating was determined. Then, properties of a silicone modified epoxy resin, which was used as matrix, were studied, and fillers which can improve mechanical and thermal insulation properties of the coating were selected. Finally, properties of the coating were completely studied. Results indicate that the tensile strength and elongation at break of the silicone modified epoxy resin are 9.38MPa and 16%, and its thermal decomposition temperature is between 340℃ and 640℃. Results also indicate that mechanical, thermal and ablative properties of the coating are very good, and its tensile strength, elongation at break, adhesion, specific heat, thermal conductivity, coefficient of thermal insulation, linear ablation rate and mass ablation rate of oxyacetylene ablation are 7.1MPa, 1.04%, 498.4N/cm~2,1.627×10~3J/(Kg·K), 0.146W/(m·K), 0.087kg~2/(m~4·s),0.194mm/s and 0.0729g/s respectively.

研究了一种用于超音速飞行器的新型热防护涂料。分析了涂层材料应具有的特性,在此基础上对作为基体的有机硅改性环氧树脂的性能进行了研究,并筛选了改进涂层材料力学性能和隔热性能的填料,最后研究了涂层材料的综合性能。研究结果表明,有机硅改性环氧树脂的拉伸强度达到9.38 MPa,断裂伸长率达到16%,热分解温在340℃~640℃;涂层材料具有良好的力学性能、热性能和烧蚀性能,其拉伸强度为7.1MPa,断裂伸长率为1.04%,附着力为498.4 N/cm2,比热容为1.627×103J/(Kg.K),导热系数为0.146 W/m.K,隔热性能参数为0.087kg2/(m4.s),氧-乙炔烧蚀的线烧蚀率为0.194 mm/s,质量烧蚀率为0.0729 g/s。

The silicone heat protective coating was prepared with silicone resin and hollow glass microballons as fillers. The effect of compounding, addition, specification and solvent system of the filler on the coefficient heat conduction of silicone heat protective coating was discussed. The result showed that the heat protective coating, which was treated with the compound of hollow glass microballons and fumed silica A380, and ketone and aromatics solvent, had the thermal conductivity ≤0.1 W/(m·K), density ≤0.55...

The silicone heat protective coating was prepared with silicone resin and hollow glass microballons as fillers. The effect of compounding, addition, specification and solvent system of the filler on the coefficient heat conduction of silicone heat protective coating was discussed. The result showed that the heat protective coating, which was treated with the compound of hollow glass microballons and fumed silica A380, and ketone and aromatics solvent, had the thermal conductivity ≤0.1 W/(m·K), density ≤0.55 g/cm~3 and tensile strength≥2.0 MPa.

以硅树脂为基料,配合中空玻璃微球等填料,制备了有机硅热防护涂层;研究了填料的组合、添加量、规格以及溶剂体系等对有机硅热防护涂层热导率的影响。结果表明,采用表面经过处理的中空玻璃微球和气相法白炭黑A380的组合填料、中空玻璃微球的用量选择60份、并使用酮类溶剂和芳香类溶剂的混合溶剂制成的热防护涂层,其热导率≤0·1W/(m·K),密度≤0·55g/cm3,拉伸强度≥2·0MPa。

 
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