May 2022, Volume 6 Issue 4
    

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  • Special Contribution
    Suggestions on Artificial Intelligence Technology Application and Development in Deep Space Exploration
    YE Peijian, MENG Linzhi, MA Jinan, WANG Qiang, LI Ying, DU Yu, WANG Shuo
    2019, 6(4): 303-316,383. https://doi.org/10.15982/j.issn.2095-7777.2019.04.001
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    The detection target of deep space exploration mission is further and further away from the earth,the time-delay of TT&C increases gradually, and the priori knowledge of the target is limited. Therefore, the autonomous performance of the explorer is increasingly required to implement scientific exploration in a distance,unknown and uncertain environment. With the development and application of artificial intelligence technology, it is necessary and possible to apply artificial intelligence technology to improve spacecraft autonomy in the field of deep space exploration. In this paper, he development of artificial intelligence technology is introduced briefly, the application of artificial intelligence technology in the field of space flight is analyzed. According to the characteristics and application scenarios of the future planning of deep space exploration,the potential demands on the application of the artificial intelligence technology in the task are analyzed, and some views and development suggestions of the applications of artificial intelligence technology to deep space exploration are proposed.
  • Topic: Autonomous Control for Spacecraft
    Research of Autonomous Control Technology for Deep Space Probes
    WANG Dayi, FU Fangzhou, MENG Linzhi, LI Wenbo, LI Maodeng, XU Chao, GE Dongming
    2019, 6(4): 317-327. https://doi.org/10.15982/j.issn.2095-7777.2019.04.002
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    Deep space exploration is the first step in human investigation,exploration and settlement of other celestial bodies outside the Earth,and autonomous control technology of deep space probes is one of the key technologies to guarantee the success of deep space exploration mission. The research status of autonomous control technology of deep space probe is summarized from four aspects,including autonomous navigation,autonomous guidance and control,autonomous mission planning,autonomous fault diagnosis and reconfiguration. Moreover,the existing problems of autonomous control technology for deep space probes are analyzed. Finally,the prospects of the technologies are predicated according to the demands for deep space exploration technology development and task implementation.
  • Topic: Autonomous Control for Spacecraft
    A Novel Celestial Navigation Method Using Angle Relative to Solar Rotation Axis
    NING Xiaolin, CHAO Wen
    2019, 6(4): 328-334. https://doi.org/10.15982/j.issn.2095-7777.2019.04.003
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    Based on Solar explorer,A celestial navigation method usingthe angle relative to Solar rotation axis is proposed for Solar explorers. Measuring the speed difference between two sets of mutually perpendicular points on the edge of the Solar surface by the spectrometers, a mathematical model for speed difference and the angle is established and the angle is used as a new measurement to provide position information of the explorer. The simulation results show that the position error of the proposed methodis reduced by 17. 4% compared with the traditional method using the sun line-of-sight vector measurement. In addition,the influence of the accuracy of speed sensor,the filter period as well as the orbit inclination are analyzed. It will provide a new way for autonomous navigation of deep space exploration.
  • Topic: Autonomous Control for Spacecraft
    Dynamic Data Processing for X-Ray Pulsar Signal
    ZHANG Dapeng, LI Zhize, WANG Yidi, ZHENG Wei
    2019, 6(4): 335-340. https://doi.org/10.15982/j.issn.2095-7777.2019.04.004
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    X-ray pulsar-based navigation is a novel astronomical autonomous navigation method based on X-ray pulsar observation., The dynamic data processing is one of the key technologies for X-ray Pulsar-based navigation. Especially data processing under the condition of low-orbit and high-dynamic is more difficult than that under the conditions of high-orbit and lowdynamic. Aiming at the measured data with low signal-to-noise ratio,a target function re-estimation method is proposed for the condition of low-orbit and high-dynamic. Furthermore, the principle of the method is analyzed and the mathematical model is constructed. The performance of the method is verified by the measured data from HXMT and XPNAV-1 satellites.
  • Topic: Autonomous Control for Spacecraft
    Autonomous Attitude Estimation Method for Non-Cooperative Target Based on Stereo VISION
    HU Qiyang, WANG Dayi
    2019, 6(4): 341-347. https://doi.org/10.15982/j.issn.2095-7777.2019.04.005
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    An estimation method based on stereo vision is proposed for the requirement of autonomous relative navigation to a non-cooperative target in on-orbit servicing mission. First, a dynamic model of Markley variables and a measurement model of stereo vision are built. Second,the relation between the motion of the feature points and the rotation of target is researched. Then the Cubature Kalman filter is used to estimate the spinning angular velocity and direction of the spinning axis. Finally,the validity of the proposed estimation algorithm is verified through numerical simulation.
  • Topic: Autonomous Control for Spacecraft
    Research of Autonomous Navigation and Control Scheme Based on Multi-Information Fusion for Mars Pinpoint Landing
    HUANG Xiangyu, XU Chao, HU Ronghai, LI Maodeng, GUO Minwen, HU Jinchang
    2019, 6(4): 348-357. https://doi.org/10.15982/j.issn.2095-7777.2019.04.006
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    An autonomous guidance,navigation and control(GNC)scheme based on multi-information fusion is proposed for Mars pinpoint landing mission. Before entering the Mars atmosphere,an autonomous navigation scheme fusing X-Ray pulsars and Mars landmark images is employed to satisfy the requirement of high precision navigation. Then,during Mars entry,descent and landing(EDL)phase,a multi-information fusion navigation scheme is constructed for absolute and relative navigation with high precision, which consists of Mars landmark images, inertial measurement unit (IMU) and ranging and velocity sensors. With the demands of pinpoint landing, a guidance and control algorithm is also designed for Mars atmosphere entry phase and powered descent phase. Finally,numerical simulation is performed,which indicates that the landing accuracy is better than 100 m and the hazard avoidance accuracy is around 0.5 m when adopting the proposed GNC scheme.
  • Topic: Autonomous Control for Spacecraft
    Design and Realization for Autonomous Operation of Chang' E-4 Mission
    YE Zhiling, HUANG Xiaofeng, GU Ming
    2019, 6(4): 358-363. https://doi.org/10.15982/j.issn.2095-7777.2019.04.007
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    The autonomous operation of Chang' E-4 is researched, including the acquirement of requirements, design of operation strategy and realization of the autonomous operation. The autonomous operation of Chang' E-4 addresses the unknown risks and assures the reliability and accuracy of key equipment based on the autonomous diagnosis, reconfiguration and management, which have been verified during the successful on-orbit demostration. The significant experiment of Chang' E autonomous operation will provide reference for the design of autonomous operation mission in deep space in the future.
  • Topic: Autonomous Control for Spacecraft
    Heuristic Search Based on State Transition Graphs for Deep Space Task Planning
    JIN Hao, XU Rui, CUI Pingyuan, ZHU Shengying
    2019, 6(4): 364-368. https://doi.org/10.15982/j.issn.2095-7777.2019.04.008
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    In view of the complex system and coupling operation constraints of deep space probes,state transition graphs are defined based on the timeline knowledge representation. With the analysis of involved constraints in task planning,the computation procedure of cost estimate for state transition is designed. In addition,the state transition graph based heuristic planning algorithm is proposed and is able to prune irrelevant search space,and accelerate the searching process. Simulation results indicate that the algorithm can reduce unnecessary planning steps and make certain improvements in planning efficiency.
  • Topic: Autonomous Control for Spacecraft
    Neural Network based Fault Diagnosis Methodfor Satellite Attitude Control System
    SUN Bowen, HE Zhangming, WANG Jiongqi
    2019, 6(4): 369-375. https://doi.org/10.15982/j.issn.2095-7777.2019.04.009
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    The closed-loop in control system usually brings difficulties for fault identification, because it may destroy the identification ability of the parameters andenhance the false alarm rate as well as the missed alarm rate,leading to the abnormality of multiple variables under the same faulty mode. Firstly, the effect of close loop is analyzed for the single-input single-output (SISO)system,while for the multiple-input multiple-output(MIMO)system the fault propagation is derived theoretically,and the influences on system variables are analyzed. Secondly,the neural network is used to construct the fault identification method. Finally,the mathematical simulation validates the negative effect of closed-loop on fault diagnosis,and the simulation of satellite attitude control systemverifies thattheproposed methodis more effective, comparing with the traditional ones.
  • Topic: Autonomous Control for Spacecraft
    Reconfigurability Evaluation and Autonomous Reconfigurable Strategy of Deep Space Probes
    XU Heyu, WANG Dayi, LIU Chengrui, LI Wenbo, FU Fangzhou, ZHANG Kebei
    2019, 6(4): 376-383. https://doi.org/10.15982/j.issn.2095-7777.2019.04.010
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    In view of the severely limitation of resources (including computing resources, hardware resources and energy resources) and unmaintainable characteristics in the process of deep space exploration,the comprehensive evaluation method and autonomous reconfigurable strategy of deep space probes are studied. In this paper,the reconfigurability of the deep space probe control system is considered in the ground design stage, and the quantitative comprehensive evaluation index of the system reconfigurability is given.
    The autonomous reconfigurable strategy is given based on the proposed evaluation index,which improves the operation of the control system of the deep space probe from the perspective of design and achieves the goal of autonomous fault handling and autonomous operation of deep space probes.
  • Article
    Study on Path Planning Method of Lunar Rover
    YU Tianyi, FEI Jiangtao, LI Lichun, CHENG Xiao
    2019, 6(4): 384-390. https://doi.org/10.15982/j.issn.2095-7777.2019.04.011
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    During the process of lunar detection tele-operation,scientific exploration target is determined by sensing data and analyzing stage by stage in order to achieve planning of different level. According to planning requirements of different level and considering the complex terrain constrains in exploration on the far-side of the moon,an integrated environment cubic model of the lunar surface is established and a search algorithm of multiple constrained navigation points in the exploration period planning is proposed, through which the navigation points determination is realized considering detection point attainability, illumination condition,communication attainability and other factors comprehensively. For the navigation unit planning, a smooth curve path search algorithm is designed considering terrain attainability cost, mobile mileage cost and operation cost. The result shows the effectiveness and real-timeby the verification in simulation experiment environment.
  • Article
    Trajectory Optimization and Parameter Analysis for Lunar Ascent
    ZHANG Lei
    2019, 6(4): 391-397. https://doi.org/10.15982/j.issn.2095-7777.2019.04.012
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    According to requirements of the lunar sampling return mission,the lunar ascent trajectory optimization and some of influence factors for the fuel consumption are studied. Based on the ascent motion equations,the trajectory optimization model for optimal fuel consumption with orbit insertion constraints is constructed and then the optimal control of the thrust direction is solved by the Gauss pseudospectral method and the sequential quadratic programming. Using the ascent motion equations with different initial thrust to weight ratio and terminal constraints with different orbit insertion parameters,relevant results on the fuel consumption are acquired by solving the relevant trajectory optimization model and the effects of these parameters on the fuel consumption are analyzed. Three schemes for the non-coplanar ascent,i. e. the yaw steering in ascent,the ascent node maneuver on orbit and the inclination maneuver on orbit,are proposed and the applicable situations are analyzed respectively in term of the fuel consumption.
  • Article
    Self-Recognition and Self-Calibration Kalman Filtering Method
    FU Huimin, YANG Haifeng, WEN Xinlei
    2019, 6(4): 398-402. https://doi.org/10.15982/j.issn.2095-7777.2019.04.013
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    In many engineering fields,such as deep space exploration,navigation,fault diagnosis and so on,due to the influence of environmental factors, improper selection of models and parameters, the system state equation often contains unknown inputs (systematical errors). Traditional Kalman filters cannot eliminate the influence of unknown inputs, resulting in larger filtering errors. In this paper,a self-recognition and self-calibration Kalman filtering method is proposed. The linear and nonlinear systems are discussed, and the corresponding formulas and filtering steps are given. This method can automatically recognize whether there are unknown inputs in the state equation. When there are unknown inputs, they can beautomatically estimated, compensated and corrected them. A large number of examples and simulation results show that compared with the traditional method,the proposed method can effectively improve the accuracy of state estimations,and the calculation is simple, which is convenient for engineering application.