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    25 April 1997, Volume 17 Issue 02 Previous Issue    Next Issue
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    ORBITAL DESIGN OF HITTING MOON DETECTOR UNDER MULTI-CONSTRAINT CONDITIONS
    Xi Xiaoning Wang Haili Xiao Qiying (National University of Defense Technology,Changsha 410073)
    1997, 17 (02):  . 
    Abstract ( 1914 )   Save
    In this paper,the problem of orbital design of landing moon detector is discussed which starts from near earth circular parking orbit,produces thrust in velocity direction ,entries landing moon orbit,and hits the moon with on guiding and free flight.Constraint condition are:①the sunshine of landing moon point;②successive ground based observation of the detector;③the limits of initial velocity and flight time of landing moon orbit;④the limits of relative moon velocity and its direction.Using theoretical analysis and simplified hypothesis,considering energy save and constraint conditions①and②,the method and examples are given about selection of the region,the date segment,and the time segment of landing the moon.Basing on numerical analysis and a large numbers of calculation,considering constraint conditions ③ and ④,the method and examples are given about determination of standard orbit.The idea and method in this paper are verified efficient and practical,they may be of important reference value to orbital design of the landing moon orbit of practical project.
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    GROUND THERMAL SCALE MODELING OF RADIATION-CONVECTIVE HEAT AND MASS TRANSFER SYSTEM IN MICROGRAVITY ENVIRONMENT
    Liu Yunlong Liang Xingang Ren Jianxun Guo Zengyuan (Tsinghua University,Beijing 100084)
    1997, 17 (02):  . 
    Abstract ( 1559 )   Save
    Through theoretical analysis and numerical verification,the temperature-material-Nusselt number preservation technique is further developed and extended to ground thermal scale modeling of radiation-convective heat and mass transfer systems under microgravity by the technique of wall heat flux compensation and modification.When the model size is properly reduced,the natural convection can be dramatically suppressed.And the similarity between the model and the prototype in temperature,humidity and flow field is obtained.
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    EFFECTS OF INTERFERING FACTORS ON PERFORMANCE OF LIQUID ROCKET ENGINE
    Shen Chibing Wu Jianjun Chen Qizhi (National University of Defense Technology, Changsha 410073)
    1997, 17 (02):  . 
    Abstract ( 1564 )   Save
    An improved nonlinear mathematical model for the steady state operation of a liquid rocket engine is presented By using this model, the effects of each interfering factor on the parameters of liquid rocket engine are computed and analyzed.The comparative analysis is carried out for the effects of the interfering factors on the engine parameters by using nonlinear model and linear method The results obtained can be used for the ana lysis of rocket engine test results, the reliability analysis and the fault analysis, and also for bringing to light the variation of the engine parameters with various interfering factors.
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    UTILITY PLATFORM AND CRITICAL TECHNOLOGIES FOR MINIATURE SPACECRAFT
    Zhu Yilin (Chinese Academy of Space Technology,Beijing 100081)
    1997, 17 (02):  . 
    Abstract ( 1523 )   Save
    In the paper the concept and application of Integrated Utility Module (IUM) are introduced first,and then the critical technologies for miniaturization of spacecraft,such as cableless interconnects,multifunction structures,advanced lightweight materials.autonomous thermal management and miniature thermal control,high density electrical packaging and interconnects and integrated design environment are presented and finally,the development processes for the microspacecraft using IUM is described.
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    THE DEVELOPMENT OF LIQUID CONTENT MEASUREMENT METHODS APPLICABLE TO SPACE MISSIONS
    Da Daoan Zhang Tianping (Lanzhou Institute of Physics, Lanzhou 730000)
    1997, 17 (02):  . 
    Abstract ( 1615 )   Save
    The developments of liquid content measurement methods applicable to space missions is outlined. A series of methods are introduced in principle and assessed comparatively. Some suggestions for our study are proposed at last.
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    APPLICATION OF“SWEATING”THERMAL MANIKIN IN THE DESIGN AND EVALUATION OF THERMAL CONDITIONING FUNCTION OF SPACE SUIT
    Pang Cheng Chen Jingshan (Institute of Space Medico-engineering,Beijing 100094)
    1997, 17 (02):  . 
    Abstract ( 1643 )   Save
    This article presented the application of thermal manikin to the design and evaluation of proctective clothing in detail,which included air ventilated suit,water cooled garment and cold weather clothing in respect of distribution of air flow,thermal insulation ,surface heat fluxes and the rate of heat removal affected by inlet water temperature and water flow rate et al. Its purpose is providing some suggestion in the practice of thermal manikin technique for the design and evaluation of thermal conditioning function of space suit.
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    AN INTELLIGENCE CONTROL METHOD FOR REALIZING PEAK-POWER-TRACKING OF A SOLAR ARRAY
    Yan Wanjuan (Beijng Institute of Spacecraft System Engineering,Beijing 100086)
    1997, 17 (02):  . 
    Abstract ( 1593 )   Save
    This paper discusses the general concept and principle of peak power trac king and gives an approach to the intelligence control scheme which utilizes fuzzy self seeking optimum principle to realize peak power tracking of the SA(solar array).Fuzzy self seeking optimum controller is used to send out a reference voltage to the SA,which compares to the real SA output voltage.The derived error signal controls the duty ratio of pulse width modulator of switching regulator until the SA output voltage equals to the reference value.Since the problem of approaching peak power point is fully considered in the algorithm of the reference voltage,the operating point of the SA will near the peak power point after the above process proceeds repeatedly.
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    THE ORTHOGONAL UNBALANCED MOMENT OF DYNAMICALLY TUNED GYROSCOPES WITH DOUBLE GIMBALS
    Feng Daojun (Beijing Coal Mining Management Institute,Beijing 100024)
    1997, 17 (02):  . 
    Abstract ( 1558 )   Save
    The calculation of orthogonal unbalanced moment of dynamically tuned gyroscopes with single gimbal have been given in some literatures.There,however,are improprieties in that calculation,therefore the calculation of orthogonal unbalanced moment in single gimbal condition is discussed again in part 1 of this paper.The calculation in double gimbals condition is given in part 2.
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    A NEW WAY ABOUT MEASURING BEARING FRICTION TORQUE AND IT’S MEASURING SYSTEM
    Zhang Duzhou Zhou Xianfang Ma Shugui (Beijing Institute of Control Engineering,Beijing 100080)$$$$
    1997, 17 (02):  . 
    Abstract ( 1478 )   Save
    In this paper,a new way for measuring bearing friction torque is presented,in which the outer force is applied by magnetic coins.The measurement system diagram is given also.Finally,the method of processing data is introduced in brief.
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