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Table of Content

    25 June 2002, Volume 22 Issue 03 Previous Issue    Next Issue
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    Design of Neck and Side Door Shroud
    Pang Hewei Huang Bencheng (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1478 )   Save
    The designs of KM6 shroud of neck and side door are two typical sectors. Neck shroud is horizontal. Side door is vertical and flake. First, the thermal load of neck and side door is determined by calculating total thermal load. Secondly, the space between shoring tubes is calculated after selecting aluminous. Thirdly, it is determined the frame work, compensation of thermal distortion, configuration of inlet and exit and thermal isolation. Finally, it is proved that the design and manufacturing are rational and meet the requirement by test running.
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    Development of Liquid Nitrogen System of KM6 Large Space Simulator
    Liu Botao Huang Bencheng Yu Pinrui Tong Hua (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1656 )   Save
    The liquid nitrogen system is one of the key subsystem of KM6 large space simulator. This paper presents design option and design results of the liquid nitrogen system. The liquid nitrogen system of KM6 is the first one successfully applied in the Chinese space environment simulator, so this paper is useful to the design of similar systems.
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    Development of a New Helium Refrigerator System
    Cai Chaoen Huang Bencheng Li Gao Wang Zijuan (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1698 )   Save
    The new helium refrigerator of space environment simulator supplies the cold environment for in cryo pump. Sucessful development of helium refrigerator represens the superiority of design. The advanced helium screw compressor, turbine dismantled vessel with integral functions and in purfier system with particular configuration are designed. This system is of high automatization We have conducted the thermal test of "shenzhou" experimental spacecraft by using this system In the future it will creat the guarantee condition for all kinds of spacecraft the tests of which need a 20K cold background.
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    The Realization of Temperature Varying Speed in Thermal Vacuum Test
    Jia Yang Wang Yirong Hao Yaxin Zheng Lide (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1388 )   Save
    On the basis of the thermal mathematics model of spacecraft, the flux adjustment method to simulate the given temperature varying speed is introduced in this paper, the simulation results and the application examples are introduced, and the correctness of the thermal mathematics model is proved.
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    Space Environment Test Facility for Manned Spacecraft
    Huang Bencheng (Beijing Institute of Spacecraft Environment Engineering ,Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1715 )   Save
    KM6 is the largest China's space environment test facility for manned spacecraft. It is one of five typical space environment test facilities in the world 9 sub system has been completed. The vacuum chamber consists of three parts. The main chamber is of 12m in diameter and 22 4m in height. Ultimate vacuum is 4 5×10 -6 Pa. Shroud temperature is 100K. It is of international advanced performance in the space environment simulation field. The paper describes the technical specification, systems, and performance characteristic. It provides test results. Important technical issues in the facility development are analyzed.
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    Vacuum Chamber Design
    Huang Bencheng Chen Jinming Qi Yan Su Wen Huang Wei (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 2075 )   Save
    The structure of KM6 vacuum chamber, the design of the rotary door and some engineering treatments for the important structure are presented in this paper. The finite element calculation and the result of the calculation for the reinforcement of large opening and the stiffness of the chamber are introduced. It is proved that the designs are reasonable.
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    Design of a Thermal Shroud Attached to KM6 Space Simulator
    Zou Dingzhong Liu Min Liu Guoqing (Beijing Institute of Spacecraft Environment Engineering , Beijing 100029)$$$$
    2002, 22 (03):  . 
    Abstract ( 1486 )   Save
    KM6,the new large space simulator, is in operation now. The thermal shroud is one of the key subsystem of the KM6 facility. This paper presents the material selection,structure configuration,fixture and the main design results of the thermal shroud.
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    Characteristic of Stainless Steel-Copper Heat Sink in Manned Module
    Wang Li Chen Weijun Jiao Baoxiang Sun Hongjin (Beijing Institute of Spacecraft Environment Engineering ,Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1703 )   Save
    The heat sink not only has the functions of simulating the "cold" and "dard" conditions of space, but also is a radiation heat exchanger and a vacuum pump. So the choice of heat sink materials is important. The characteristics and the test results of the stainless steel copper heat sink are described in detail. They show that the stainless steel copper heat sink design provides a new way for heat sink development.
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    Structure Design and Finite Element Calculation of KM6 Manned Test Chamber
    Chen Jinming  Huang Bencheng  Yuan Xiugan  Wang Li  Cao Yuzhong  (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029) (Beijing Universitg of Aeronautics and Astronautics, Beijing 100083)
    2002, 22 (03):  . 
    Abstract ( 1653 )   Save
    KM6 manned test chamber is developed for the Chinese manned space environment testing in a simulated space environment. The design for the manned test chamber is introduced in the paper, and the design is optimized with the method of finite element calculation. The final chamber structure and the results of the finite element optimizing calculation is afforded. The ultimate pressure in the chamber reached 5 2×10 -4 Pa. The design of the test chamber meets the demands for structure design.
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    Temperature-Adjusting System With Jetting Liquid Nitrogen
    Han Qiwen Pei Yifei Zhao Lijun Huang Bencheng (Beijing Institute of Spacecraft Environment Engineering,Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1552 )   Save
    Temperature adjusting system is an important system of space environment simulator to carry out the T/V & T/B tests for spacecraft. It can adjust thermal shroud temperature continuously between -100℃ and +100℃, and stabilize the temperature at any point within the range. Compared with such temperature adjusting equipments as cooler with liquid nitrogen tank or thermal shroud at liquid nitrogen temperature with infrared heating cage, the temperature adjusting system with jetting liquid nitrogen can reduce energy consumption and decrease expenditure. It is difficult to use the system in large environmental simulator for its thermal lag and unevenness between different heat sink branches. The jetting liquid nitrogen system fits the facts and requirements of KM6 in design . The results of temperature adjusting system with jetting liquid nitrogen of a large space environment simulator indicate that it has achieved comparative level in the same field in the world.
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    Vacuum Thermal Test Technology for Large Spacecraft
    Pang Hewei Huang Bencheng Qian Beixing Jia Yang (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1466 )   Save
    The vacuum thermal test technologies for large spacecraft in KM6 space environment simulator, including thermal balance test technology and thermal vacuum test technology, are introduced in this paper. Test objectives, test description, test phases, flux control and support hardware are introduced too.
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    Simulation Research of Shroud Temperature Field
    Jia Yang Liu Min Huang Bencheng (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1897 )   Save
    The mathematics model of KM6 shroud normal status is built to make sure of the control method of shroud temperature field, and the simulation model is built and solved on MATRIX platform. The dynamic characteristic and equivalent model are established, and some advice on the design of the KM6 shroud is put forward.
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    Design of Vacuum System
    Zhang Chunyuan Huang Wei Shao Rongping Ru Xiaoqin Xu Zhongxu (Beijing Institute of Spacecraft Environment Engineering,Beijing 100029)$$$$
    2002, 22 (03):  . 
    Abstract ( 2541 )   Save
    Vacuum system of oil free and high speed is an integrated component of a modern large simulator. The article discusses in detail the design of KM6 simulator vacuum system in project and method, including vacuum attain, vacuum measure, vacuum detection, vacuum pumps choosing, vacuum pumps configuration, conductance calculating. The aim is to offer a kind of helpful idea and means for design of large vacuum equipment.
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    Leakage Detection Techniques of Large Test Equipment
    Zhang Chunyuan Huang Eencheng Xu Zhongxu Huang Wei Ru Xiaoqin Shao Rongping (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)
    2002, 22 (03):  . 
    Abstract ( 1595 )   Save
    The general leakage detection techniques of space simulator based on a 3200m 2 chinese space simulator are presented. The intention of the paper is providing some helpful thoughts and means for leakage detection of a space simulator. The paper discusses in detail the helium mass spectrometer leakage detector and analyzes sensitivity of helium mass spectrometer leakage detector based on theory and practice. In the end the paper discusses how to design the whole leakage detection scheme of a large simulator.
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    Study on Large Scale Cryo-Pumping System
    Liu Guoqing Huang Bencheng (Beijing Institute of Spacecraft Environment Engineering, Beijing 100029)$$$$
    2002, 22 (03):  . 
    Abstract ( 1415 )   Save
    The main pumping system of modern large space simulators is a large scale cryo pumping system. The theory of molecular distribution in large space simulators was discussed and applied to optimize the cryo pumping system of KM6 large space simulator. The satisfying results were obtained.
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