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    25 April 1998, Volume 18 Issue 02 Previous Issue    Next Issue
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    OPTIMAL BOUNDED THRUST TIME FIXED RENDEZVOUS OF SPACECRAFT
    Chen Ying Chen Zugui Liu Liangdong (Beijing Institute of Control Engineering,Beijing 100080)
    1998, 18 (02):  . 
    Abstract ( 2072 )   Save
    The problem of optimal bounded thrust time fixed rendezvous of two spacecraft is investigated in this paper.Several properties on optimal thrust arcs are presented on the basis of the rendezvous process of spacecraft.These results have provided the theoretical fundamentals for the engineering design of rendezvous and docking of spacecraft.
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    STUDY ON OPTIMIZATION OF LOW THRUST TRAJECTORIES
    Yan Hui Wu Hongxin Wu Xinzhen (Beijing Institute of Control Engineering,Beijing 100080)
    1998, 18 (02):  . 
    Abstract ( 1529 )   Save
    The trajectory optimization for low thrust electric propulsion has been researched in the paper.The orders of the acceleration are of 10 -2 ~10 -4 .The indirect approach is used in optimization.The adjoint equations are integrated backword to avoid the initial guess of adjoint variables by means of the transversality condition.The earth escape trajectory and low orbit transfer optimization are numerically resolved by iteration method.The results show the optimal transfer orbits are almost circular,and transfer time is long.The magnitude of low thrust is inverse proportion.
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    DYNAMICS OF BEAM LIKE MEMBER: LUMPED PARAMETER METHOD
    Yan Shaoze Wu Delong Huang Tieqiu (Beijing Institute of Astronautical Systems Engineering,Beijing 100076) Liu Youwu Zhang Dajun (Tianjin University,Tianjin 300072)
    1998, 18 (02):  . 
    Abstract ( 1762 )   Save
    The lumped parameter dynamic method of beam like members,the finite segment method,is analyzed and reviewed in detail.The dynamic equations of multibody systems are developed by means of Huston's method based on Kane's equations.The finite segment method is adopted to establish the models of the beam like members.The inertia effects of the nonlinear deformations of the beams are taken into account,and the mode transformation of relative displacements isintroduced into the calculating process to increase the efficiency.A typical experimental result verifies that the foregoing method can be used for dynamic analysis of multibody systems with the beams undergone nonlinear deformations.
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    OPTIMAL ORBITAL MANEUVERS FOR HOMING HASE OF SPACE RENDEZVOUS
    Jing Wuxing Geng Yunhai Yang Xu Wu Yaohua (Harbin Institute of Technology,Harbin 150001)
    1998, 18 (02):  . 
    Abstract ( 1584 )   Save
    Fuel optimization for homing phase of space rendezvous is studied.Based on C-W equations,an algorithm to compute optimal rendezvous time and optimal position of the first Δ v is presented.Simulationresults show that for two impulse rendezvous if the first Δ v is applied after some coasting time,fuel required is less than that if the first Δ v is applied at initial time.
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    TOLERANCING ANALYSIS OF COMPACT CORRUGATED HORN
    Wang Wutu (Xi′an Institute of Space Radio Technology,Xi′an 710000)
    1998, 18 (02):  . 
    Abstract ( 1483 )   Save
    Based on the analysis and design of compact corrugated horn by using the mode matching method and spherical wave expansion,the tolerancing analysis of compact corrugated horn is presented for the first time in the paper,and taking the on board compact corrugated horn for an example.The paper gives the effect of tolerances of design parameters on the cross polarization and return loss of compact corrugated horn and provides the important criteria for designing compact corrugated horn.
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    THEORETICAL ANALYSIS AND DISCUSSION ON ON GROUND TEST METHODS SIMULATING GAS HEAT AND MASS CONVECTION IN CABINS OF SPACECRAFTS
    Li Jindong (Beijing Institute of Spacecraft System Engineering,Beijing 100086)
    1998, 18 (02):  . 
    Abstract ( 1564 )   Save
    Three on ground test methods for simulating the gas convection,heat and mass transfer in the cabin of spacecrafts,have been analysed theoretically and discussed in the present paper,including thermal reducing scale modelling,reducing pressure modelling and mass convection comparison modelling.The laws or criteria of similitude and their application constraints in accordance with different simulating test methods are given.Their advantages and disadvantages were compared in principle.It is indicated that:(1)thermal Reducing scale modelling can obviously reduce the influence of natural convection if reynolds number is constant,but this test method can not be used for an engineering model;(2)reducing pressure modelling can be used for an engineering model,however,it can not be used for liquid flows:(3)mass convection comparison modelling can completely eliminate the natural convection,but it is very complicated and difficult in engineering applications.
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    THE DYNAMIC OF SPACE RENDEZVOUS WITHIN A SHORT DISTANCE
    Lin Laixing (Beijing Institute of Control Engineering,Beijing 100080)
    1998, 18 (02):  . 
    Abstract ( 1750 )   Save
    In this paper,the dynamic equation of relative motion between two spacecraft in a short distance is first studied,based on both simple (linearized)model and accurate model.A useful ellipse equation in relation the trajectory of a station keeping point in an orbital plane is obtained.Dynamic characteristics of the station keeping point and orbit perturbations are finally discussed.
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    STUDY OF STRUCTURAL,OPTICAL AND ELECTRICAL PROPERTIES OF VO 2 THERMOCHROMATIC FILMS
    Cui Jingzhong Da Daoan Jiang Wanshun (Lanzhou Institute of Physics,Lanzhou 730000)
    1998, 18 (02):  . 
    Abstract ( 1588 )   Save
    VO 2 thermochromic films were prepared by reactive magnetron sputtering method.The macro and micro structures of the samples were characterized by XRD,XPS and AFM methods.The effects of sputtering parameters on the optical/electrical properties of VO 2 films were studied.The transitional properties of VO 2 films were characterized by the electrical resistance change in the phase transition process.
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    THERMODYNAMIC MODELS OF PSGI AND THEIR USAGE FOR LIQUID PROPELLANT REMAINING MEASUREMENT ON SATELLITE
    Zhang Tianping Da Daoan (Lanzhou Institute of Physics,Lanzhou 730000)
    1998, 18 (02):  . 
    Abstract ( 1516 )   Save
    This paper is theoretical studies about the method of the pressure stimula ted by gas injecting(PSGI),which was nominated for the most suitable candidate applicable to the chinese telecommunication satellite to measure liquid propellant remaining.Two main thermodynamical models,the isothermal model and the adiabatic model,were established and the dominant equations corresponding to the models were derived for practical measurement usage.Lastly,some problems associated with actual operations were discussed in details.
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    NEURAL NETWORK BASED HIERARCH DIAGNOSIS METHOD AND ITS APPLICATION
    Cheng Huitao Huang Wenhu Jiang Xingwei (Harbin Institute of Technology,Harbin 150001)
    1998, 18 (02):  . 
    Abstract ( 1860 )   Save
    Neural network and hierarch classification method in fault diagnosis are studied.Neural network technology connected with hierarch classification model is to rea lize hierarch diagnosis.Satellite energy sources is taken for the research object,and the hierarch classification model of fault analogue test bed of this system is established.Based upon this,proper hierarch neural network is established and system fault is diagnosed.This method is verified and validated by two examples.
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    DEVELOPMENT AND DESIGN OF A 32 BIT RISC BASED EMBEDDED MINIMAL COMPUTER SYSTEM
    Guo Zhen Wang Dongsheng Wang Yuanxi (Beijing Institute of Control Engineering,Beijing 100080)
    1998, 18 (02):  . 
    Abstract ( 1566 )   Save
    The development and design of a 32 bit RISC based embedded minimal computer system is an important project in the development of satellite on board compu ter. The specificity of the design of the minimal computer system is given,and a simple but effective novel debugging method is presented in this paper.
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