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   热防护 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.043秒
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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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  heat protection
The heat protection of highly forced diesel pistons by anodic microarc oxide coating
      
Multicomponent, multiphase heat-protecting multicoats formed by anodic microarc oxidation (AMO) can optimally solve the problem of the heat protection of pistons of internal combustion engines.
      
Questions regarding the solution of different problems of heat and mass transfer during the design of heat protection systems are examined.
      
Theoretical principles of design of multilayer swelling heat protection with assigned properties
      
Heat protection of the brain extends tolerance to high deep body temperature in animals, and may be enhanced in humans if the head is cooled.
      
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  heat shield
Nonstationary gas filtration in a two-layered heat shield
      
A gas mist produced by supplying a cooling gas through a separate slot or a system of slots along the surface is a widespread method of obtaining a mass-transfer heat shield.
      
According to estimates in [1], the heat shield mass for entry of a probe into the atmospheres of the outer planets can make up 20-50% of its total mass; here the radiative component predominates in the aerodynamic heating.
      
The results are compared with the data of a space shuttle flight experiment on the effect of a discontinuity of heat shield catalyticity on the "overequilibrium" surface temperature jump.
      
One of the important problems has been to create reusable heat shield materials.
      
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This paper discusses in detail the problem on the mass loss and endothermic mechanism for charring material.By using a lamination model, the energy conservative relations for each lager which has different chemical and physical property of material are presented.The numerical simulation of thermal protection for each lager is established by integral method.Comparison with analytic results of one-dimensional heat conduction shows a good agreement.The calculation results also consist tent with that of ablation...

This paper discusses in detail the problem on the mass loss and endothermic mechanism for charring material.By using a lamination model, the energy conservative relations for each lager which has different chemical and physical property of material are presented.The numerical simulation of thermal protection for each lager is established by integral method.Comparison with analytic results of one-dimensional heat conduction shows a good agreement.The calculation results also consist tent with that of ablation experiments.

详细讨论了低温炭化材料的质量损失和吸热机理。利用分层模型,给出具有不同物理和化学特性的各层的能量守恒关系。用积分法给出各层热防护的数值模拟,数值模拟计算结果与一维热传导解析解结果一致,亦与地面烧蚀实验結果一致。

The integrated ramjet which consists of a liquid fuel ramjet and a solid fuel booster is a new type of engine.It is the best choice for the propulsion system of supersonic, small volume, medium-and long-range missile.The integrated ramjet has Wide field of application and is drawing attention from the world.In recent years, China has advanced greatly in the key technology of integrated ramjet. Since the liquid fuel ramjet and the booster share the same combstor,neither mechani cal flame-holder nor air film cooling...

The integrated ramjet which consists of a liquid fuel ramjet and a solid fuel booster is a new type of engine.It is the best choice for the propulsion system of supersonic, small volume, medium-and long-range missile.The integrated ramjet has Wide field of application and is drawing attention from the world.In recent years, China has advanced greatly in the key technology of integrated ramjet. Since the liquid fuel ramjet and the booster share the same combstor,neither mechani cal flame-holder nor air film cooling structure can be installed in the combustor.This causes some difficulty in design of ignition,combustion oscillation reduction and themal protection,However test results show :several methods can be used for solving the problem of ignition,and one of the keys is to meet the flame stability criteria.The flow field of combustor inlet,and the fuel distribution, etc.have a great effect on the combustion oscillation. The computation results also show: during flight, the high velosity airstream outside the wall of combustor can greatly reduce the temperature of the combustor wall,and as a result the challenge for thermal protection struction with the same cooling effect is reduc-ed.

整体式冲压发动机是将固体助推火箭与巡航用液体燃料冲压发动机组合成为一个整体的新型动力装置,它是超声速、小体积、中远程导弹动力系统的最佳选择.整体式冲压发动机的出现将冲压发动机的应用推向一个新阶段,引起世界各国的广泛重视.近几年我国在整体式冲压发动机很多关键技术的研究上有所突破.液体冲压发动机和助推火箭共用一个燃烧室,使燃烧室中无法安装专门的机械式火焰稳定器和空气冷却衬筒,这为解决燃烧室的点火起动问题、振动问题及热防护问题带来了很大的困难.试验表明:冲压发动机的点火起动问题有多种解决方案,其中火焰稳定性准则的满足是点火起动的重要条件;燃烧室的进口流场,燃油浓度分布等对振动有很大的影响;计算表明,冲压发动机在飞行状态时,流经燃烧室壳体外表面的高速气流的冷却作用可大大降低燃烧室壳体的温度,在相同的冷却效果下,可降低对热防护层的要求.

Physiological thermal state of the body was graduated onto five stages. They are respectively thermal comfort state, warm state, and light, middle and heavy heat load states. Rectal temperature,skin temperature, sweat rate, heart rate and heat store were used as physiological basis for the evaluation. And a complex evaluation index for the above five physiological indices was established by multivariate regression. It has been used successfully in the appraisal of personal heat protective equipments.

本文介绍了在不同热负荷下,身体所处的热生理功能状态,作了明确的5级分度。即分为舒适、温热及轻度、中度和重度热负荷状态。采用直肠温度、平均皮温、出汗率、心率及热积等5项生理指标,作为评定基础。并利用多元判别方法,建立了对5项生理指标的综合评价指数。已较好地用于评价个体热防护装备。

 
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