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Table of Content

    25 August 1986, Volume 6 Issue 04 Previous Issue    Next Issue
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    THE APPLIED SOFTWARE SYSTEM OF THE SPACECRAFT T.T.C ENGINEERING
    Lu Zhenlin
    1986, 6 (04):  1-7. 
    Abstract ( 1696 )   Save
    This paper goes further into the construction, the procedure of the development and the appreciation of the quality on the applied software system of spacecraft T·T·C engineering, and raises some points in establishing a system of the applied software as well.
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    ON THE AERODYNAMIC CONFEGURATION DESIGN FOR THE RECOVERABLE SATELLTE
    ZHou Qicheng
    1986, 6 (04):  8-16. 
    Abstract ( 1923 )   Save
    In this paper, the outline of reentry atmosphere for the recoverable satellites is presented. From the point of view of the technical design, the maindesign principles of aerodynamic configurations for the satellite reentry modules are discussed. The characters of the present space reentry vehicles of-US and USSR are reviewed. Then, the differences of the aerodynamics between the satellite reentry modules and the missile noses are discussed and the special aerodynamic problems of the reentry modules are pointed out. At last, the future develoment tendency of the aerodynamic shape for the reentry modules is looked forward to and a new aerodynamic shape-double conewith a flat nose is recommended for the reentry satellite.
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    THE EXACT SOLUTION TO A PROBLEM ASSOCIATED WITH THE DISTRIBUTION OF TEMPERATURE IN A HONEYCOMB SANDWICH
    Li Da-yao
    1986, 6 (04):  17-24+16. 
    Abstract ( 1627 )   Save
    This paper deals with a mixed initial-boundary value problem for the one-dimensional heat-flow equation. This problem is closely associated with the distribution of the temperature in a honeycomb sandwich used in the shell construction of vehicle. The boundary conditions are more complicated than the usual ones for the one-dimensional heat-flow equation. Under certain hypotheses, the exact solution of this problem can be obtained by the method of the separation of the variables. This solution may be used to check the accuracy of finite difference approximation.
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    ANALYSIS OF THE PERFORMANCE FOR THE “STEP TYPE” FRENQUENCY GUIDANCE
    Chen Tao
    1986, 6 (04):  25-34. 
    Abstract ( 1788 )   Save
    This paper quots stress on discussing and analysing a guidance method of "step type" which is ideally designed, and the characteristics of the loop—locked control in combining with PLL by a brief introduction of a typical freqneney analyzer. Simply calculation is made to this guidance method for the work threshold and guidance probability. A brief description of the real engineering application for guidance technique is given.
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    ANALYSIS OF THE TANK PRESSURIZATION CALCULATION FORMULA FOR A LIQUID PROPELLANT ROCKET
    Qiu-Yulun
    1986, 6 (04):  44-50. 
    Abstract ( 2049 )   Save
    Propellant tank pressures of rocket which is provided by the pressurization system are the key to decision success or failure of rocket. However the pressurization pressure are only defined according to a theoretical calculated method. In the past, the theoretical calculating method of the pressurization pressures was to adopt a traditional pressurization calculating equation. Now this article doubtes whether the formula is right, and proposes that it is necessary for us to discuss it again. On the basis of the low of conservation of energy, a new basic pressurization calculating formula has been derived, and then it has been proved by test that this new formula is conformable to practice while the error of the traditional formula is bigger.
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    THE PRINCEPLE AND TEST OF A WIDE ANGLE AND HIGH PRECISION PHOTODETECTOR FOR SUN SENSOR
    Chen Guilin (Shanghai Institute of Technical Physics, Academia Sinica)
    1986, 6 (04):  51-55+34. 
    Abstract ( 1733 )   Save
    A new method is presented in this paper to detect the Sun direction for CdS photodetector. The advantage of the method is shown in comparison with normal ways. The performance test was made and the excellent result was obtained. The field of the view is larger than ±26. The resolution is smaller than 0.01°. The accuracy is better than 0.026°. It will be expected for application of a Satellite and other spacecraft.
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    Some Mathematical Problems of Astronautical Technics
    Huang Lei-de (Tung-ji University, Shanghai)
    1986, 6 (04):  62-70. 
    Abstract ( 1562 )   Save
    To determine once space flight, one should select the optimal space trajectories, discriminate the optimal thrust programme & determine the optimal design of freight rocket (vehicle) , etc. So they must use mathematical methods & "three C" (Computer, Communication, Control) technics. How to solve the mathematical problems of austronautical technics is full of meaning. This paper summarizes briefly the solving methods of some math- ematical problems of astronautical technics.①The singular equations of pressure distribution on a coplanar wing in supersonic flow.②The boundary value problem for wings at large angle of attack in steady & unsteady flow.③How to solve the equations of hypersonic interactions with surface mass transfer?④To solve the problem of viscous flow over cylinders in unsteady motion.⑤To evaluate the validity of turbulence calculations & models.⑥The problem for transverse vibrations of nonisotropic & nonuniform elastic plates.⑦How to solve the equations for the coupled interaction launch behavior of a flexible rocket and flexible launcher.In the last two decades a large number of investigations in different areas of astronautics & aeronautics have been devoted to the study of "astronautical mathematics"), which is an important and rising branch of applied mathematics.
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