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25 December 2014, Volume 34 Issue 6 Previous Issue    Next Issue

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Variable Universe Self-tuning Fuzzy PID Controller of Attitude Maneuver for Flexible Spacecraft WEI Feng-Mei, ZHAO Yu-Shan, SHI Peng 2014, 34 (6):  1.  doi: 10.3780/j.issn.1000-758X.2014.06.001 Abstract ( 1294 )   PDF (935KB) ( 1125 )   Save The attitude dynamical equations of flexible spacecraft with solar panels were established,and the attitude kinematic equations were described by modified Rodrigues parameters (MRPs)in orderto preventthe singularity of thelarge angle maneuver. A variable universeself-tuning fuzzy PID controller was proposed for model uncertainties and environmental disturbances. A new shrinkable factor was designed, and it was easy to calculate and could achieve the accuracy. Numerical simulation based on Matlab/Simulink shows that the response of the variable universeself-tuning fuzzy PID controller are 350s fasterthan that ofthe conventional PID and fuzzy PID controllers,and thatit has no vershoot and can realize the effective control of attitude maneuver and effectively suppress the vibration of solar panels. Related Articles | Metrics

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A Data Association Method of Double Fence Radar Based on Estimating Doppler Velocity XING Dong-Xu, LIU Zhong-Gui 2014, 34 (6):  8.  doi: 10.3780/j.issn.1000-758X.2014.06.002 Abstract ( 1280 )   PDF (810KB) ( 1209 )   Save The observation data association of the same object before computing the initial orbit is a crucial problem for the double fence radar system. An estimating Doppler velocity method was proposed, which was independent of initial orbit determination with iteration computation, and a corresponding data ssociation rule was designed. The simulation analysis shows that the exactness of the proposed data association rule is similar with that of the rule which is dependent on the Doppler velocity computed by the orbit determination, but the computing time is less than 10% of the latter one. Related Articles | Metrics

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Research on Tether Assisted Interplanetary Orbital Capture LIU Bin-Bin, HUANG Pan-Feng, MENG Zhong-Jie 2014, 34 (6):  15.  doi: 10.3780/j.issn.1000-758X.2014.06.003 Abstract ( 2125 )   PDF (923KB) ( 1152 )   Save Tether control of the momentum exchange tether assisted interplanetary orbital capture in deep space exploration was studied. Firstly, the dynamic model of a detector system in a hyper bolic flying orbit was established. Secondly,the consistent condition of orbital capture and the optimum tether cut off point were derived to analyze the dynamic characteristics.Finally, considering the sub detectors post capture orbit maneuver requirements and limitation of the tether deployment/retrieval velocity, a new optimal control problem was proposed and numerically solved by the simulated annealing algorithm.Simulation results show that the tether orientation is appropriate at the cut off point and will be beneficial for the following orbit maneuver,and the  maximum tether deployment/retrieval velocity is about 30m/s. Related Articles | Metrics

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Coupling Analysis of the Spacecraft Attitude and Orbit Model Based on the Spiral Theory MA Jia-Jin, ZHU Zhan-Xia 2014, 34 (6):  24.  doi: 10.3780/j.issn.1000-758X.2014.06.004 Abstract ( 1362 )   PDF (835KB) ( 1243 )   Save The coupling between spacecraft attitude and orbit movement in an integrated model based on the spiral theory was analyzed.The method parameters analysis method was used,which changed the coupling parameters successively,to get the curves and the laws of coupling terms.The validity of theoretical analysis was proved.To verify the coupling impact on the control effect,the control law was designed.The result shows that the coupling seriously affects the attitude and the orbit of relative motion,and the attitude influences the orbit motion a lot,and can converge easily,while the orbit has little effect on the attitude. Related Articles | Metrics

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Modeling and Simulation of Driving Data Transmission Antenna ZHOU Yong, ZHANG Jian 2014, 34 (6):  31.  doi: 10.3780/j.issn.1000-758X.2014.06.005 Abstract ( 1517 )   PDF (977KB) ( 1841 )   Save The high gainantenna was drived with the stepper motor,the harmonic gear and the microstep driver.The over all antenna pointing error shall be 0.1°(3σ)or less.The model of driving antenna was described.On account of the torque model of stepper motor,the nonlinear dynamics model of the harmonic gear and the dynamic model of the microstep driver,as well as the nonlinear model was built,the step response,pointing error and output torque were provided by the proposed model.Comparing with the simulation and experiment results,the math model is correct and reliable.The pointing  error is 0.017°(3σ)or less,meeting the requirements for pointing precision. Related Articles | Metrics

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Development and Technical Difficulties of Deployable Space Masts ZHOU Si-Da, ZHOU Xiao-Chen 2014, 34 (6):  38.  doi: 10.3780/j.issn.1000-758X.2014.06.006 Abstract ( 1529 )   PDF (1789KB) ( 3168 )   Save Deployable space masts are the fundamental deployable space structures to construct the large complex space structures.Ther esearch  and applications of the different deployable space masts were investigated,and the comprehensive performances of the different structural forms were compared and analyzed.Additionally,the technical difficulties of the study and design of the deployable space masts were deeply analyzed based on the mechanics, material,space environment and vibration control considerations.Finally,the development trends of the deployable space masts were discussed in order to give necessary support to its design,selection and analysis in the future. Related Articles | Metrics

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Reflector Antenna Precision Prediction Based on Neural Network ZHOU Yang, ZHANG Shu-Jie, ZHANG Hua-Zhen 2014, 34 (6):  51.  doi: 10.3780/j.issn.1000-758X.2014.06.007 Abstract ( 1655 )   PDF (1450KB) ( 968 )   Save The precision of reflector antenna on orbit is an important design specification,and the reasonable structure design can improve the reflector precision. By taking full advantages of the high strength,high modulus,low coefficient of thermal expansion of the composite material,and the surface precision of the antenna could be improve dsignificantly.By using the artificial neural networks highly nonlinear mapping capability,and based on the principle of the minimum RMS,the design parameters were optimized.The calculation results indicate that the computing time can be effectively saved. The results show that the optimization method is reasonable,and the structure design meets the design requirements. The design scheme and analytical  methods provide a direction for the structure design of the reflector. Related Articles | Metrics

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Impedance Control of Space Flexible Manipulator System Assisted Docking of Space Station WEI Qing-Qing, LIU Zhi-Quan, WANG Yao-Bing, SHAO Li-Min 2014, 34 (6):  57.  doi: 10.3780/j.issn.1000-758X.2014.06.008 Abstract ( 2696 )   PDF (976KB) ( 1755 )   Save Control and measurement errors could lead to great contact forces during the space flexible manipulator assisted spacecraft docking.Theforce sensor could not get rid of the inertia force and it would make the manipulator more flexible.To solve these problems,a dynamic model of space manipulator was established as the feed forward input of the joints torque.The impedance control scheme was established,and a dynamic model of a system consisted of a space manipulator and a space station was built by the software of ADAMS. The co-simulation was done by the software of Matlab and  ADAMS.The results show that the space manipulator system works correctly even through the interfering forces during the simulation.The space manipulator system  also operates correctly in the docking direction,and is free in the other directions so that it can adapt to thes pace manipulator system assisted spacecraft docking.Atthesametime,thesystem canovercometheinfluenceofthebigload of the space station to the force measurement by measuring the joints parameters.While,it will not make the space manipulator more flexible. Related Articles | Metrics

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Thermal Control Design for Topography Camera of Chang'e-3 Under High Temperature Environment o fLunar Surface SONG Xin, ZHANG You-Wei, ZHOU Xiang-Dong, LIU Zi-Jun 2014, 34 (6):  65.  doi: 10.3780/j.issn.1000-758X.2014.06.009 Abstract ( 1840 )   PDF (904KB) ( 1710 )   Save Topography camera of Chang'e-3 probe is installed directly exposed to the high temperature environment of the lunar surface.The high temperature environment is great challenge to the thermal control design. To solve the high temperature problem,the best radiation position was presented as the core  of thermal design based on the heat flow analysis.The topography camera could obtain suitable initial temperature and fastest cooling rate when it was located at the best position.Meanwhile,the infrared radiation of the lunar surface was reduced as much as possible by arranging the radiator position appropriately and wrapping the camera with multilayer insulation.The telemetrydata of the topography camera meet the requirements of the storage stage temperature and have a large margin.Considering one-circle photograph,the topography camera temperature meets the operating temperature requirements,and the results are in good agreement with the thermal analysis.The thermal control design for the topography camera is proved to be correct and can be referred by the devices with similar problems of the deep space exploration field. Related Articles | Metrics

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Analysis on Attitude Angle Impacting Stereo Positioning Accuracy for Agility Satellite SUN Jun, ZHAO Hong-Zhi, YANG Fang, ZHAO Jian 2014, 34 (6):  72.  doi: 10.3780/j.issn.1000-758X.2014.06.010 Abstract ( 1527 )   PDF (847KB) ( 1658 )   Save In order to accurately evaluate the agility satellite effectiveness and set the reasonable indices of maneuvering ability and measuring component,the influence on the stereo position accuracy was compared between the satellite with single-linear-array CCD camera(SLAC) and the one with three-linear-array, based on the agility satellite mapping synchronously during the maneuvering.The agility satellite stereo mapping position accuracy evolution model was established.The approximate analytic algorithm of the errors were given according to the correlation between the inner and outer elements with angular orientation elements. Mathematical calculation shows that the indices of the agility satellite stereo mapping angle elements and measurement accuracy meet the requirements of the position accuracy. Related Articles | Metrics

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Substrate Integrated Waveguide Switch Matrix Based on LTCC Fabrication Process YANG Fei, YU Hong-Xi 2014, 34 (6):  79.  doi: 10.3780/j.issn.1000-758X.2014.06.011 Abstract ( 1487 )   PDF (1085KB) ( 2724 )   Save A nove limplementation of high frequency switch matrix for satellite usage was proposed by using substrate integrated waveguide (SIW)technology in low temperature co-fired ceramic (LTCC)fabrication process.The SIW channels transition between layers and isolation capability between different channels were discussed.By utilizing the single-pole-double-throw switch chips as channel choosing units,and SIW channels as the radio frequency signal transition, connection and cross transmission channels,a K band 4x4 switch matrix was designed and measured,with insertion loss less than 8 dB and isolation more than 38 dB from 20 GHz to 21 GHz,which showed good transition performance within SIW RF channels and high isolation between adjacent  RF  ways in high frequency,to solve the conundrum that high frequency switch matrixin LTCC always have high insertion loss and low isolation,asthe higher radiation loss and lower isolation capability of the strip-line embedded in LTCC substrate. Related Articles | Metrics