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25 February 2022, Volume 42 Issue 1 Previous Issue   

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Advances and prospects of the configuration design and control research of the LEO mega-constellations RUAN Yongjing, HU Min, YUN Chaoming 2022, 42 (1):  1-15.  doi: 10.16708/j.cnki.1000-758X.2022.0001 Abstract ( 841 )   PDF (4662KB) ( 2133 )   Save In recent years, the LEO constellation programs have developed rapidly and become a “new battlefield” in the global competition of space strategic resources. Firstly, up-to-date status of LEO megaconstellations was described, and the current status of LEO mega-constellations in China was introduced. Configuration design methods and characteristics of constellation were summarized from four aspects, including mission requirements, coverage characteristics, perturbation compensation and spare strategy. Then, according to the whole control process of satellite constellations configuration from orbit to departure, the methods and characteristics of initialization control, stationkeeping control, reconfiguration control, constellation collision avoidance control and de-orbit control were reviewed. Finally, the future research aspects of the configuration design and configuration control technology of the LEO mega-constellations were looked into. Related Articles | Metrics

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Case study of inorbit satellite failures and artificial intelligence based failure detection WANG Yakun, YANG Kaifei, ZHANG Jie, GUO Lifang, HAN Xiaodong, XING Chuan, WANG Rui 2022, 42 (1):  16-29.  doi: 10.16708/j.cnki.1000-758X.2022.0002 Abstract ( 697 )   PDF (1709KB) ( 613 )   Save Reducing satellite failures and keeping satellites healthy in orbit are important issues in satellite design. In order to analyze the causes of satellite failures and explore the latest satellite failures detection methods, we first collected typical satellite fault cases in orbit from 2003 to 2021, and then performed statistical analysis and correlation analysis of satellite failures from different aspects, including the correlation between satellite platforms and satellite failures, and the relationship between satellite in-orbit time and satellite failures, etc. Finally, the artificial intelligence based satellite failures detection research was introduced, including the artificial intelligence based failures detection systems and methods as well as the time-series data failures detection research. This research can provide reference for future failure case analysis and failure detection system design of satellite. Related Articles | Metrics

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A review for space-based ADS-B NI Jiushun, CHEN Lihu, YU Sunquan, LI Songting, GUO Jianming, LUO Aobo, LI Jinhua 2022, 42 (1):  30-37.  doi: 10.16708/j.cnki.1000-758X.2022.0003 Abstract ( 274 )   PDF (4911KB) ( 803 )   Save As an important technology of air traffic control in the future, space-based ADS-B technology can overcome the difficulties of ground equipment deployment in desert, ocean, polar and other places. The space-based ADS-B technology has the characteristics of a wide range of reconnaissance and reception, which can cover the whole world, and relevant studies have been carried out in many countries. According to the frontier characteristics of ADS-B technology, the research progress of ADS-B technology is investigated. First of all, the principle and related research of ADS-B are summarized. Secondly, the key technologies of ADS-B reception on board are reviewed from four aspects: antenna technology, radio frequency circuit technology, signal processing and constellation design method. Finally, the application of ADS-B data and its future development prospect are described. Related Articles | Metrics

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Influence of earth atmosphere radiation on the imaging of space object under tracking and gazing state ZHANG Luping, XIAO Shanzhu, HU Moufa, CHEN Sheng 2022, 42 (1):  38-46.  doi: 10.16708/j.cnki.1000-758X.2022.0004 Abstract ( 105 )   PDF (7239KB) ( 53 )   Save  In order to analyze the influence of earth atmosphere radiation on imaging characteristics of space object for different detection methods, a moving and detecting scene of space object was designed with STK, where the visible light imagers mounted on the GEO and MEO satellites were set as detecting platform, the HEO satellite was set as object. Models of space object and earth atmosphere radiation were built with infinitesimal method, and then the SNR of space object was derived. Furthermore, both tracking and gazing detectors were disposed on each detecting platform to analyze the change rule of SNR with different detecting models. The simulation results indicate that the target SNR obtained by the middle orbit detector is stronger than the high orbit detector; the target SNR of tracking detector is stronger than that of gazing detector on the same detecting platform; the difference of SNR is maximal as the space object entering or leaving the detecting field of view, yet it is minimal as the object is close to the center of detector's field of view.  Related Articles | Metrics

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Rigid-flexible coupled nonlinear dynamics and analysis of space membrane structure SHAO Qi, LU Yifan, SHI Chuang, YUE Honghao, LIU Rongqiang 2022, 42 (1):  47-56.  doi: 10.16708/j.cnki.1000-758X.2022.0005 Abstract ( 266 )   PDF (2545KB) ( 327 )   Save The nonlinear dynamic responses with strong rigid-flexible coupling have horrible influence on structures and equipments. The rigid-flexible coupled nonlinear dynamic model of space membrane antenna was established, where the effect of second-order nonlinearity and rigid-flexible coupling on the stiffness, damping as well as loading was described. The influence of rigid body motion, such as initial velocity and acceleration, on elastic response was analyzed by numerical calculation. Besides, the natural frequency and damping were considered as well. It comes out that the frequency and the maximum deformation of the membrane response are both positively correlated with the rigid acceleration and velocity, but negatively correlated with damping; as natural frequency increases, the response frequency rises up while the deformation decreases. The rigid-flexible nonlinear model deduced in this paper will serve as the theoretical basis of dynamic analysis and surface control of flexible structures. In the meanwhile, the rigid-flexible coupling response characteristics can provide a significant reference for the maneuvering design and disturbance avoidance of membrane structure. Related Articles | Metrics

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Attitude maneuver and physical test of large-scale spacecraft with ultra-low frequency YUAN Quan, LIN Hanzheng, ZHANG Jun, WEI Chunling 2022, 42 (1):  57-64.  doi: 10.16708/j.cnki.1000-758X.2022.0006 Abstract ( 107 )   PDF (3239KB) ( 275 )   Save The attitude maneuver schemes for large-scale spacecraft with ultra-low vibration frequency were designed using Bang-Bang, filter attitude programming and classical phase control. The physical testbed of large-scale spacecraft with ultra-low vibration frequency was established to validate the different control schemes. Using different attitude programming methods and different attitude control actors including jets or control moment gyros, five attitude schemes were designed, i.e. attitude tracking controller with Bang-Bang programming and jets, attitude tracking controller with filter programming and jets, attitude tracking controller with Bang-Bang programming and control moment gyros, attitude tracking controller with filter programming and control moment gyros, phase controller with biased angular velocity and jets. The different control schemes were tested on the physical testbed. It is shown that the scheme of attitude tracking controller with filter programming and control moment gyros has the minimal vibration, whose vibration magnitude is reduced by 81.8% compared with the maximum vibration of classical phase control scheme. Related Articles | Metrics

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Multi-satellite TT&C scheduling method based on DNN LI Changde, XU Wei, XU Liang, WANG Yan 2022, 42 (1):  65-72.  doi: 10.16708/j.cnki.1000-758X.2022.0007 Abstract ( 182 )   PDF (2393KB) ( 200 )   Save The increase in the number of satellites has brought about huge challenges to the traditional multi-satellite TT&C scheduling methods. Problems such as long scheduling time and low task satisfaction make these methods no longer suitable for large-scale satellite scheduling. Therefore,deep neural networks(DNN) algorithm which has the characteristics of supporting big data, parallel computing and autonomous learning was introduced, and a multisatellite TT&C resource scheduling method based on DNN was proposed. According to the characteristics of multi-satellite TT&C resource scheduling and the requirements of the DNN algorithm, the relevant entities and constraints that affect the scheduling results during the scheduling process were analyzed. Factors that have great impact on the scheduling results were selected and discretized as eigenvalues of DNN. Moreover, this method changed the full matching between TT&C tasks and resources to an effective one through the preprocessing method, which reduced the solution space, the characteristic latitude of the DNN and the difficulty of training. Then a DNN model based on the extracted feature values and scheduling characteristics was built, and the training of the DNN model was completed through a large amount of historical scheduling data. Experiments show that the task satisfaction of the method proposed reaches 99%, and that the running time is reduced by 83% after feature dimension reduction. The results verify that the method proposed is feasible and effective. Related Articles | Metrics

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Fault-tolerant attitude control of Mars entry phase considering actuator failure DAI Qing, ZHOU Honggang, LIU Pengxuan, LI Shuang 2022, 42 (1):  73-82.  doi: 10.16708/j.cnki.1000-758X.2022.0008 Abstract ( 185 )   PDF (4095KB) ( 157 )   Save  Failure and external disturbance during the process of Mars entry inevitably degrade the performance of Mars entry guidance and control algorithms.The backstepping method was used to design the attitude fault-tolerant control algorithm for Mars entry, which is not sensitive to changes in the moment of inertia information. First, the derivative of the virtual control law was regarded as an interference quantity, and the adaptive technology was used to compensate it, which avoids the defect of differential explosion in the traditional backstepping method. Meanwhile, the saturation function was explicitly introduced in the control design process to ensure that the control law could still keep the attitude of probe stable in the presence of input saturation. Finally, the "Mars Science Laboratory" probe was used as a model for numerical simulation verification. The results show that the controller can achieve the accurate attitude tracking under input saturation,uncertainty of inertia and the actuator failure conditions. Related Articles | Metrics

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Nominal ground trace adjustment for regression SSO satellites based on revisit-circle LIN Zhuchong, WANG Jianfeng, ZHANG Wei, LIU Li, ZHU Ziheng, WEI Yinshan 2022, 42 (1):  83-91.  doi: 10.16708/j.cnki.1000-758X.2022.0009 Abstract ( 105 )   PDF (6743KB) ( 83 )   Save Satellite constellation is widely used in environmental monitoring, geographical mapping and other remote sensing applications. Ground-trace distribution of satellites in a constellation should be well designed so as to achieve better performance such as less revisit time to targets and longer access interval to ground stations. At present, accurate and useful method for the optimization and adjustment of groundtrace distribution is still lacking because of the soaring amount of calculation with increasing number of satellites and the coupling of requirements to be considered. In order to solve the optimization problem of ground trace distribution of remote sensing satellite constellation in regression Sunsynchronous orbit, an accurate and comprehensive method based on a “revisit-circle” was proposed. The simulation results show that this method can simultaneously consider satellite phase retention and coverage performance under a unified framework, and that it can provide an intuitive and effective solution to the optimization of multi-target coverage performance, which can be used for satellite constellation design and performance adjustment of on-orbit satellite constellation. Related Articles | Metrics

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Research on omnidirectional ambiguity characteristics and calculation method of spaceborne SAR TAO Manyi, HU Guangqing, HUANG Yuanbao, CHEN Guozhong, SU Xiaoming 2022, 42 (1):  92-98.  doi: 10.16708/j.cnki.1000-758X.2022.0010 Abstract ( 429 )   PDF (4954KB) ( 362 )   Save The conventional ambiguity calculation method of spaceborne SAR is based on range one-dimensional pattern and azimuth one-dimensional pattern, and the range ambiguity and azimuth ambiguity are analyzed independently. However, the azimuth ambiguity is based on range ambiguity signal, which is caused by image processing. In order to solve the problem that the estimated range ambiguity value in system design is inconsistent with the actual imaging effect and to restore the essence of azimuth ambiguity, a new method of ambiguity analysis and calculation for spaceborne SAR was proposed. Firstly, the causes of range and azimuth ambiguity and the relationship between them were analyzed. Then, the range conversion model between the arbitrary pointing angle of the pattern and the actual observation to the earth was established. At the same time, based on the twodimensional pattern, the calculation method and steps of the omnidirectional ambiguity were given. Finally, the simulation design was carried out and the results show that the omnidirectional ambiguity calculation method is more in line with the actual imaging effect, providing a reference for the subsequent high-resolution spaceborne SAR system design and ambiguity suppression.  Related Articles | Metrics

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Design optimization of modular configuration for deployable truss antenna reflector HU Fei, SONG Yanping, HUANG Zhirong, LI Yichen, MA Xiaofei, LI Wan 2022, 42 (1):  99-106.  doi: 10.16708/j.cnki.1000-758X.2022.0011 Abstract ( 302 )   PDF (4948KB) ( 375 )   Save For the modular configuration of the deployable truss antenna reflector, the degree of freedom (DOF) of the module and multi-module were analyzed based on the screw theory,and the module combination idea was adopted to reduce the design complexity of deployable antenna reflector. Firstly, the module with a planar working surface was composed of three 3RR-3RRR tetrahedral elements, then the truss antenna reflector was formed by the modules. Secondly, in view of the expected deployable motion of the antenna , the expansibility of the modular truss antenna was verified by the screw theory. Finally, the connecting motion pairs between two modules were designed and optimized to achieve the maximum storage ratio. The research shows that the modular deployable antenna reflector has good expansibility. When the adjacent parts of every two modules are connected with universal joints, the upper or lower disks can be on the same plane, and the antenna reflector can be completely folded with 8 DOFs.After modules networking, the truss antenna reflector has the advantages of high storage ratio and less DOFs, which can be deployed by the motor drivers to realize the controllable deployment, and has good application in the field of aerospace institutions. Related Articles | Metrics

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High precision deflection angle measurement of irregular light spot ZOU Yansheng, ZHANG Naiyuan, YUAN Hui, LIU Chen, LIU Deming 2022, 42 (1):  107-113.  doi: 10.16708/j.cnki.1000-758X.2022.0012 Abstract ( 117 )   PDF (3264KB) ( 111 )   Save For the space laser communication, the laser spot is usually distorted by the atmospheric turbulence and becomes the irregular shaped spot. To meet the challenge of insufficient angle measurement accuracy with four-quadrant detector (QD) for irregular light spot, a high precision deflection angle measurement method based on multi-source information fusion was proposed. The proposed method improves the measurement accuracy of the irregular spot deflection angle by integrating the data of QD and the image of charge coupled device (CCD), while maintaining high measurement resolution and high response speed of QD-based measurement method. Compared with the conventional QD algorithm, the results of both simulation and experiment show that, with the fusion algorithm, the root mean square error and the peak-to-peak measurement error are reduced by 55.56% and 42.98%, respectively. Related Articles | Metrics

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Masscenter location identification of large space debris based on binocular vision and inertial measurement units fusion YAO Jinming, LI Guangping, ZHANG Huibo, TIAN Hao, YOU Bindi, DAI Shijie 2022, 42 (1):  114-124.  doi: 10.16708/j.cnki.1000-758X.2022.0013 Abstract ( 104 )   PDF (8457KB) ( 33 )   Save The mass center of the large free-tumbling debris is the relatively fixed point in the on-orbit operation frame, and is also the benchmark for the conversion of dynamic parameters from the debris conjoined base to the satellite coordinate system. The precise identification of mass-center location is the key to improving the identification accuracy of debris dynamic parameters. A method for the mass-center-location identification of large space debris was proposed based on inertial measurement units and binocular vision. Based on the torque-free Euler equation and dyadic coordinate transformation, the conversion relationship between the inertial measurement units attached to the surface of the space debris was established. Based on the conversion relationship of the inertial measurement units, the redundant inertial measurement units’ data was denoised. Using the denoising data, the distances from the inertial measurement units to the mass center were optimized. Using the binocular vision, the dynamic coordinates of the markers on the inertial unit were obtained. Then the distances from the inertial measurement units to the mass center were used, and the large space debris’ mass-center location was identified. Simulations with Gaussian white noise data of inertial measurement unit and binocular vision were carried out, and the results show that the error of the inertial measurement units’ data is reduced to less than 1% after real-time denoising and that the mass-center-location triaxial error is less than 0.47mm. Ground experiments were carried out, and the results show that the triaxial error of the mass-center-location is less than 0.49mm. Simulations and experiments prove that the method can provide a more accurate data benchmark for the de-tumbling and capture mission of large space debris. Related Articles | Metrics

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Remote sensing image segmentation based on PSPNet with neighborhood color difference YUAN Wei, XU Wenbo, ZHOU Tian 2022, 42 (1):  125-130.  doi: 10.16708/j.cnki.1000-758X.2022.0014 Abstract ( 169 )   PDF (10294KB) ( 192 )   Save Traditional semantic segmentation of remote sensing image is to classify the pixels with similar values by using the spectral characteristics of images, but it is unable to distinguish the same kind of objects with different spectra. Aiming at this problem, a method was proposed in which the color difference information of neighborhood is integrated into the original image as input to PSPNet. Firstly, RGB was transformed into LAB. Then CIELAB formula was used to calculate the color difference value between each pixel and eight neighboring pixels, and the average value was taken as the neighborhood color difference value of the pixel. Experiment was done by using PSPNet on WHU building dataset and Massachusetts building dataset. The results show that the MIoU, ACC and F1score with neighborhood color difference are better than without. Therefore, the proposed method of merging neighborhood color difference is an effective way to improve the segmentation accuracy of PSPNet. Related Articles | Metrics

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Carbon materials with high thermal conductivity and its application in spacecraft TONG Yelong, TAO Zechao, LI Yifan, LIU Zhanjun, JIANG Lifeng, YIN Yazhou 2022, 42 (1):  131-138.  doi: 10.16708/j.cnki.1000-758X.2022.0015 Abstract ( 207 )   PDF (5437KB) ( 226 )   Save The requirement and typical application of graphite materials with high thermal conductivity in spacecraft were summarized. High thermal conductivity flexible graphite film can be used to improve the thermal conductivity of the complex or as a flexible thermal strap. Thermal louvers can be used for heat dissipation of high-power components or electronics. Aiming at the application bottlenecks of existing flexible thermal conductive materials such as poor flexibility, small size, and thin thickness, a new type of flexible graphite film with high thermal conductivity was promoted and developed. Graphitic films with wrinkles at surfaces were prepared by mechanical rolling using graphitic bubble as precursor which derived according to “solid foaming” method. Subsequently, millimeter-level thick tape with thermal conductivity above 750W/(m·K) were fabricated based on thermoplastic processing. Furthermore, the tensile strength of this thermal conductive tape was elevated from 6 MPa to 20 MPa while the dimension can be extended under mechanical stress. Applying the flexible graphite film to the large-scale load installation structure of the spacecraft, the temperature gradient is reduced from 8.9°C to 2.5°C, which can effectively improve the equivalent thermal conductivity of the spacecraft's low thermal conductivity structure. High thermal conductive graphitic blocks were prepared by hot-pressing method. Then graphite products as thermal louvers were completely coated with metal layer in order to prevent the graphite particle at surface from peeling off, which was successfully applied to heat dissipation of a high-power solid-state memory device for satellite. Related Articles | Metrics