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空间飞行器
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  spacecraft
    s: Objective To study the method of preventing dewing on the cabin wall of a spacecraft.
    目的探讨防止载人空间飞行器舱内结露的方法。
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    Theoretical Analysis and Simulation Study of Dewing in Spacecraft.
    空间飞行器内结露的理论分析及模拟实验
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  spacecraft
This collection can be used to test spacecraft production materials, in order to determine their resistance to biodegradation.
      
Studying Stability of the Flexible Spacecraft with a Discrete Control System
      
Stability of the spacecraft was considered with regard for its elastic structural oscillations arising under discrete control.
      
Consideration was given to the possibility of estimating jointly the motion coordinates and parameters of the elastic spacecraft using algorithms based on the discrete Kalman filtering and the theory of testing statistical hypotheses.
      
Design of the Suboptimal Profiled Relay Control of Orientation of the Spacecraft Having Elastic Structural Elements with Regard
      
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This is a brief review on microgravity combustion, along with the discussion of the fundamental characteristics of combustion and fire processes under microgravity. Recent research activities in micogravity combustion and space fire prevention were emphasized. In addition, the potential use of flame-inhibiting atmospheres in the space cabin was introduced. The technique of fire detection and extinguishment in spacecraft environments was also discussed.

本文介绍了国际上微重力条件下燃烧科学的研究现状,论述了微重力条件下燃烧过程的基本特点及其火灾特性。在此基础上,对空间飞行器的防灭火技术进行了简单介绍和探讨,并着重阐述和介绍了国际上微重力条件下燃烧和灭火研究的内容及航天舱内采用阻燃气氛来抑制火灾发生的方法,并讨论了国际上空间飞行器内的火灾探测和扑救技术。

s: Objective To study the method of preventing dewing on the cabin wall of a spacecraft. Method Theoretical analysis and experimental study of the factors and process of dewing on the cabin wall in a spacecraft were carried out according to principles of thermodynamics and heat transfer.Several factors relating to dewing were discussed and evaluated. Result Thermal insulation could be used to prevent dewing on the wall.Ventilation might be beneficial for suppressing the dewing.Effects of these methods were limited...

s: Objective To study the method of preventing dewing on the cabin wall of a spacecraft. Method Theoretical analysis and experimental study of the factors and process of dewing on the cabin wall in a spacecraft were carried out according to principles of thermodynamics and heat transfer.Several factors relating to dewing were discussed and evaluated. Result Thermal insulation could be used to prevent dewing on the wall.Ventilation might be beneficial for suppressing the dewing.Effects of these methods were limited if they were used singly.Decrease of the emmisivity of the outer surface of the wall was favorable for preventing dewing on the inner surface of the cabin wall. Conclusion Dewing on the wall could be prevented effectively by thermal insulation together with local ventilation.

目的探讨防止载人空间飞行器舱内结露的方法。方法从热力学和传热学的角度分析和研究了空间飞行器舱内壁面的结露条件及过程 ,对影响舱内结露的几个因素进行了探讨。结果壁面隔热有利于防止结露 ,局部通风有可能抑制结露。但单独采用隔热或通风的方法均存在一定的局限性。降低外壁黑度有利于防止舱内结露。结论采用壁面隔热和局部通风相结合的方法 ,可以有效地达到防止结露的目的。

Objective In order to provide a reliable basis for the design of the optimal structure,it is necessary to investigate the wall mass constitutes of a pressurized spacecraft when thermal insulation and ventilation means are applied to prevent dewing on its inner wall. Method Physical and mathematical models for heat transfer process in the wall of a spacecraft were used to calculate the mass variation.Several factors associated with operation parameters and configurations of the wall were evaluated.These factors...

Objective In order to provide a reliable basis for the design of the optimal structure,it is necessary to investigate the wall mass constitutes of a pressurized spacecraft when thermal insulation and ventilation means are applied to prevent dewing on its inner wall. Method Physical and mathematical models for heat transfer process in the wall of a spacecraft were used to calculate the mass variation.Several factors associated with operation parameters and configurations of the wall were evaluated.These factors influence the mass minimization on condition that the condensation on the inner surface is prohibited. Result The wall mass of a spacecraft reduces at first to a minimum value and then increases with the increasing ventilation flow rate while other conditions are kept unchanged.There exists a minimum wall mass,corresponding to a critical ventilation flow rate.The effects of ventilation,surface emissivity and thermal conductivity of the insulation on the mass minimization were presented.The influence of different dew points on the mass minimization was also investigated. Conclusion Lower thermal conductivity of thermal insulation layer,lower emissivity of outer surface and higher emissivity of inner surface with suitable ventilation flow rate are expected because of their benefit to the reduction of wall mass of the spacecraft.

目的研究采用隔热及通风的防结露措施后空间飞行器密封舱壁的质量构成特点 ,为舱壁的轻量化设计提供依据。方法建立了舱壁传热过程的物理数学模型和质量构成模型 ,对结露临界工况下影响质量增量的几个因素进行了分析。结果在其它条件不变时 ,随着通风量的增加 ,系统的质量增量会先减小然后增大 ,存在最小值及相应的临界通风量。找出了通风量、隔热层表面黑度及隔热层导热系数对质量增量的影响规律以及露点变化的影响。结论较小的隔热层导热系数 ,较低的外表面黑度和较高的内表面黑度 ,均有利于舱壁质量增量的降低。

 
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