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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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The heat protection design and experimental research of a high-pressue gas generator, which is a part of the dyhamic missile launcher, is introduced briefly in this paper. The high-energy and high burning-rate pro-pellant is used in the gas generator. In order to solve the problem of erosion, various types of heat-proof and erosion-proof materials are selected to provide for thr heat protection, according to the status of heat transfer and combustion product erosion in the chamber. The design of the heat protection...

The heat protection design and experimental research of a high-pressue gas generator, which is a part of the dyhamic missile launcher, is introduced briefly in this paper. The high-energy and high burning-rate pro-pellant is used in the gas generator. In order to solve the problem of erosion, various types of heat-proof and erosion-proof materials are selected to provide for thr heat protection, according to the status of heat transfer and combustion product erosion in the chamber. The design of the heat protection is laboratory tested. The experimental results show that the design is successful and the performance reliable.

本文简要介绍一种缩比弹射装置高压室研制过程中,有关热防护设计与试验研究。该高压室使用高能高燃速固体推进剂,为解决烧蚀问题,在高压室内根据受热和燃气冲刷不同,选用不同耐热耐烧蚀材料进行热防护设计,并进行了大量试验研究。试验结果表明,该高压室的热防护设计是成功的,工作是可靠的。

This paper applies the method of Godunov to calculate the internal flowfield of Vertical Launching System(VLS).The Secondary flow's formation after motor ignition and its effect on missile are described in detail. It provides scientific basis for the design of missile and the heating protection of the VLS.The paper gets more satisfactory numerical results by solving inviscid Eulerian Equation in the axsymmetric cylindrical coordinates,especially, it well "captures" the shock wave and spreads the thickness of...

This paper applies the method of Godunov to calculate the internal flowfield of Vertical Launching System(VLS).The Secondary flow's formation after motor ignition and its effect on missile are described in detail. It provides scientific basis for the design of missile and the heating protection of the VLS.The paper gets more satisfactory numerical results by solving inviscid Eulerian Equation in the axsymmetric cylindrical coordinates,especially, it well "captures" the shock wave and spreads the thickness of shock wave over two computational cell.The calculation results indicate that the Godunov's Method employed to solve the supersonic internal flow-field is very successful,its results are stable and reliable.The results are identical to the experimental data and complotely agree with the calculation by J. J.Yagla and L. P. Anderson.

本文应用Godunov方法对导弹垂直发射系统的内流场进行了数值模拟,详细描述了导弹点火后二次流的形成及其对弹体的影响,为导弹的设计和发射系统的热防护提供参考。本文通过解轴对称坐标系下的无粘欧拉方程组,得到了较为满意的解,捕获了压力箱内的激波,使激波展开在2个网格。计算结果表明:Gudunov方法用于解超音速内流场问题是很成功的,其结果是稳定的、可靠的。该计算所得的结果与实验结果相当吻合,与J.J.Yagla和L.P.Anderson等人的计算一致。

Simplified analysis for thermal protection of the Self-Contained Adaptive Transpiration (SCAT) nosetip is provided and the simplified calculation formulas of thermal protection are deduced. The calculation examples of thallium, indium, tin and water coolants are given. The deduced formulas in this paper are simple and convenient. An engineering calculation method of nosetip thermal protection design is obtained in this paper. It can be used in prediction before the ground simulation experiment.

本文对自适应发汗冷却(SCAT)弹头的热防护问题作了简化分析,并导得了热防护计算的简化计算公式。对铊,铟,锡和水四种冷却剂的情况,给出了算例。本文导行的公式,计算较简便,可作为弹头热防护设计的一种工程计算方法。这种工程计算方法亦可以用于地模拟实验前的予算。

 
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