Loading...

Table of Content

    25 December 1990, Volume 10 Issue 06 Previous Issue    Next Issue
    For Selected: Toggle Thumbnails
    DEVELOPMENT OF RETURN TECHNOLOGY AND RETURNABLE SPACECRAFT
    Wang Xiji (Chinese Academy of Space Technology)
    1990, 10 (06):  1-5. 
    Abstract ( 1738 )   Save
    According to stastics of spacecrafts launched, the number of returnable spacecrafts is more than 1/3 of the total of spacecrafts.The returnable spacecrafts play a role of pioneer and leading in development and utilization of space resources and make great contribution to manned space flight and human progress. The paper analyses in detail three phases of development of return technology and returnable spacecraft, which are preliminary development phase, application phase and nondamaged fixed-point return phase, and points out that it is the nondamaged fixed-point landing return that will become the main development approach in a quite long period in future.
    Related Articles | Metrics
    CHINESE RETURNABLE SATELLITE
    Min Guirong Lin Huabao (Chinese Academy of Space Technology)
    1990, 10 (06):  6-10. 
    Abstract ( 1862 )   Save
    Chinese returnable satellite is a low orbit, three-axis stabilized satellite with its return module being safely recovered, which can be used for remote sensing satellite, micro-gravity test platform, and scientific and technical test satellite.The paper briefly outlines various subsystems, launching, return and major application of the satellite. Up to 1990 China has launched and recovered successfully12returnable satellites and obtained better social and economic benefits.
    Related Articles | Metrics
    ESTABLISHING RECOVERY MOTION EQUATIONS OF SATELLITE WITH QUATERNION RULE
    Zhang Jian (Beijing Institute of Spacecraft System Engineering)
    1990, 10 (06):  11-21. 
    Abstract ( 2129 )   Save
    Euler angles are used to describe the angle motion and the relationship between coordinate systems, but there must be a adventitions solution in the angle motion equations when some euler angle is equal to π/2. Usually, attitude angles varied within a large range in all of a process of a satellite reentering, especially ballistic reentering, so it is difficult to avoid the singular point.By adopting a quaternion rule, the singular point problem has been settled once and for all, and the calculating speed and precision have effectivelly been impoved.In this fashion, this paper presents a simple method used to establish reentry motion equations of a satellite.
    Related Articles | Metrics
    DIGITAL ATTITUDE CONTROL SYSTEM AND FLIGHT TEST RESULTS OF CHINESE RETURNABLE SATELLITE
    Chen Yiqing Chen Zugui Sun Chengqi Wang Xudong Feng Xueyi Ding Guangcheng (Beijing Institute of Control Engineering)
    1990, 10 (06):  22-29. 
    Abstract ( 1652 )   Save
    In this paper the digital computer attitude determination and control system used in chinese returnable satellite for scientific exploration and technical experiments is described.The attitude determination algorithm and the jet control logic in phase plane are the major contents of this paper. The concept of quasi-steady gain matrix is introduced for periodic filtering system and a simplfied filtering algorithm has been developed. In the digital autopilot the variable step deadband control logic is developed and it remarkably improves the control quality. Some flight data are presented.The control system performed successfully in the flight test.
    Related Articles | Metrics
    CONTROL OF RECOVERY SYSTEM OF RETURNABLE SATELLITE
    Li Yili (Beijing Institute of Space Mechine and Electricity)
    1990, 10 (06):  30-33+43. 
    Abstract ( 2154 )   Save
    In this paper, a "overload-time" control program of returnable satellite is discussed on the basis of the return trajectory analyses for a imaginary satellite. It is explained that this control program is simple and feasible for the recovery of unmanned satellite.In this paper, it is proposed that a longer non-therm-shield coast flight phase can be adopted for some satellites in order to reduce the Mach number and the dynamic pressure when the parachute is employed.
    Related Articles | Metrics
    ABLATIVE THERMAL PROTECTIVE MECHANISM AND NUMERICAL SIMULATION FOR RETURNABLE SATELLITE
    Jiang Guiqing (Beijing Institute of Aerodynamics)
    1990, 10 (06):  34-43. 
    Abstract ( 1677 )   Save
    This paper discusses in detail the problem on the mass loss and endothermic mechanism for charring material.By using a lamination model, the energy conservative relations for each lager which has different chemical and physical property of material are presented.The numerical simulation of thermal protection for each lager is established by integral method.Comparison with analytic results of one-dimensional heat conduction shows a good agreement.The calculation results also consist tent with that of ablation experiments.
    Related Articles | Metrics
    ABLATIVE THERMAL PROTECTION STRUCTURE DESIGN OF RETURN MODULE
    Chen Qinghua (Beijing Institute of Spacecraft Systems Engineering)
    1990, 10 (06):  44-48. 
    Abstract ( 1639 )   Save
    This paper introduces ablative thermal protection structure design of a return module of some satellites. Some concepts, material selection, design appoach, analytical computation and evaluation are given.
    Related Articles | Metrics
    THERMAL DESIGN OF RETURNABLE SATELLITE
    Xu Jiwan (Beijing Institute of Spacecraft Systems Engineering)
    1990, 10 (06):  49-56. 
    Abstract ( 1862 )   Save
    This paper presents the thermal control subsystem of chinese returnable satellite. According to the characteristics of the satellite, a method of thermal inertia used in thermal design is described.The temperatures obtained from orbit telemetry data are in agreement with that from ground testing.Thermal control subsystem operated well the temperatures of the structure and the equipments met the design requirement.
    Related Articles | Metrics
    MAIN FACTORS ATTECTING PHOTOGRAPHIC QUALITY OF PRISM SCANNING PANORAMIC CAMERA
    Yang Bingxin (Beijing Institute of Machine and Electricity)
    1990, 10 (06):  57-63. 
    Abstract ( 1740 )   Save
    This paper briefly presents the basic principle and characteristics of the prism scanning panoramic camera. Based on the large amount of data acquired in tests and through detailed analyses,it is concluded that the main factors affecting the photographic quality of the camera are the prism, synchronization error between the speed of image and that of film movement and the temperature variance. It is also discussed in the paper how to improve the synchronization accuracy through technical approches.
    Related Articles | Metrics
    ELECTRICAL POWER SYSTEM OF RETURNABLE SATELLITE
    Jiang Zhujun (Beijing Institute of Spacecraft Systems Engineering)
    1990, 10 (06):  64-70. 
    Abstract ( 2117 )   Save
    Electrical power system is one of the important subsystem of a satellite.The successful fulfillment of a space mission depends on the proper and reliable functioning of the power system. Electrical power system includes power generation, power distribution and control, and harness. This paper first discusses the mission and property of a returnable satellite, then presents the design method of electrical power system. Especially, it gives a detailed description for distribution criterion, distribution program (Centralized regulation approach, decentralized regulation approach and mixed regulation approach) and power distributor design.
    Related Articles | Metrics