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    25 December 1999, Volume 19 Issue 06 Previous Issue    Next Issue
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    A Study on Dynamics and Control of Small Satellite Flying Around Space Station
    Lin Laixing (Beijing Institute of Control Engineering,Beijing 100080)
    1999, 19 (06):  . 
    Abstract ( 1571 )   Save
    With a small satellite flying around the space station, the operation and exterior state of the space station can be monitored,and the times of the astronaut's extravehicular activity are reduced.This is a new concept about the applications of the small satellite. With low consumption,the small satellite can fly around for long time.Mainly,the stability of flying around orbit is discussed and the control stratagem of overcoming the perturbation is presented.Flying around for one month consumes only 3~4m/s velocity increment .
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    Research on Model Matching Design for Linear Model Following Control System
    Wang Dayi Li Donglin Tian Ziyun Wei Shaoyi Guo Suyun (School of Astronautics Harbin Institute of Technology,Harbin 150001)
    1999, 19 (06):  . 
    Abstract ( 2502 )   Save
    This paper introduces the detailed research on the perfect model matching methods for linear model following control(LMFC).The model matching solution for LMFC is expanded.On the basis of this solution,a new algorithm for model following and error adjustment is presented.Finally,the control law is applied to the inertial navigation system and its feasibility is studied and verified in the simulation experiment.
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    A Discussion on Collision Checking for Constellation Design
    Yan Ye Ren Xuan (National University of Defense Technology,Changsha 410073)
    1999, 19 (06):  . 
    Abstract ( 1579 )   Save
    In process of designing a constellation which has a large quantity of satellites,the possibility of collision between satellites should be considered.The collision events must be avoided in constellation design.A research on proper collide above equator is introduced at first.Further,the movement rule of relative distance between satellites is given in terms of generalized collision.Some methods to avoid collision in constellation design are also given.This paper provide some useful results for constellation design.
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    Initial Value Method of Orbit Determination Using a Single GPS Satellites
    Liu Yanfang Hong Bingrong (Harbin Institute of Technology,Harbin 150001)
    1999, 19 (06):  . 
    Abstract ( 1552 )   Save
    Based on the research of orbit determination using a single GPS satellites,two effective methods of getting initial value and comparison of their performance are discussed.Computer simulation shows the second method can give a fixed and practical initial value.As a result,the amount of calculation is cut down greatly and the converge performance of the algorithm is improved.This technique is superior to the traditional guess method in the engineering field.
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    A New Approach to Relative Motion Between Two Satellites
    Yang Weilian (Beijing Institute of Spacecraft System Engineering,Beijing 100086)
    1999, 19 (06):  . 
    Abstract ( 1646 )   Save
    A study of the relative motion of satellites is widely applied in the area of spaceflight.The earliest way to solve this problem is to establish the relative motion equation and to have its linear approximate solution.That is the well kmown C W method which is very efficient and accurate as two bodies are closer,but the error would grow up rapidly as time goes on.The reason of error grown is the omitting an acceleration term,which causes the solution including a linear term with time,when linearizing the motion equation.An approximate analytical solution for three dimension is derived by establishing an analytical relation of relative motion and then using the exact results of elliptical motion.The solution is accurate to first order in the eccentricity and inclination difference and including no long term errors.The numerical testing is also presented in comparing with the exact solution and the result shows that the new solution is much more accurate than C W solution.
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    Features Changes and Development Trend of Satellite Radio Telemetry and Telecommand
    Chen Yiyuan (Chinese Academy of Space Technology,Beijing 100081)
    1999, 19 (06):  . 
    Abstract ( 1601 )   Save
    The development of satellite radio telemetry and telecommand both in China and in the world is introduced.Because of American advanced electronic technology,its early satellite telemetry and telecommand is suitable for the features of satellite,the main opinion is that it is a trend of technical development to synthesign radio and video frequencies of satellite telemetry and telecommand.
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    The Thermal Testing of Spacecraft
    Liu Feng Jin Xunshu (Beijing Institute of Satellite Environment Engineering,Beijing 100029)
    1999, 19 (06):  . 
    Abstract ( 1840 )   Save
    The paper discusses the importance and implementation of various types of thermal tests (thermal balance test,thermal vacuum test and thermal cycling test) during the spacecraft development phase.Refering to some problems existing in the testing practice,the thermal testing (thermal vacuum test and thermal cycling test) at component level,especially the electronic and electrical components,and the thermal vacuum test of flight model satellite are emphasized,which contributes greatly to the reliability of spacecraft.Several suggestions are presented.
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    The Experimental Study of Double Component Propellant with Mass Spectrometer Method
    Wang Rongzong Zhao Zhong Sun Tianhui (Lanzhou Institute of Physics,Lanzhou 730000)
    1999, 19 (06):  . 
    Abstract ( 1573 )   Save
    The propellant leak detection technology is one of the key technologies for spacecrafts launch and operation.Both components such as MMH and MON 1 have been adopted in the propulsion system.The mass spectrometer technology has the ability to detect them in the mean time.In the paper,the detection equipment is introduced briefly,and the experiment results of MMH and MON 1 are also given.
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    The Deceleration and Neutralization Systems for Microwave Dischange Atomic Oxygen Simulation
    Sun Gang Tong Jingyu Li Jinhong (Beijing Institute of Spacecraft Environment Engineering,Beijing 100029)
    1999, 19 (06):  . 
    Abstract ( 1655 )   Save
    By using an advanced Electron Cyclotron Resonance (ECR) technical, an ion source with 10 15 /(cm 3·s) has been attained. On the base of it, a new atomic oxygen simulator is developed successfully. There are deceleration and neutralization systems in this simulator, so that oxygen ion beam with high velocity can been converted into oxygen atom beam with low velocity. Energy and types of the particles in this simulator are similar that of LEO. Thus a real simulation of Low Earth Orbital environment is accomplished.
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    Optimal Placement and Sizing of Piezo Actuators and Experiment in Vibration Control of Smart Beams
    Sun Dongchang (Hebei University of Technology,Tianjin 300130) Zhang Honghua Wu Hongxin Li Yong Liu Wu (Beijing Institute of Control Engineering,Beijing 100080)
    1999, 19 (06):  . 
    Abstract ( 1628 )   Save
    The optimal location and size of the piezoelectric actuators in vibration control of smart beams are optimized.The basic equations of the piezoelectric smart beams are derived.According to these equations,a practical and simple criteria to find the optimal location ,size and even the number of the piezoelectric actuator patches is given.The criterion is independent of the initial condition of the vibration and the control gains.The simulation results show that the control energy can be decreased greatly by using the optimized actuators to control the vibration of smart beams.Moreover,inorder to demonstrate the effectiveness of the vibration control,the vibration control of the flexible beam using piezoelectric ceramic patches is experimented and good control results are obtained with the optimal placed actuator patches.
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