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27 June 2022, Volume 48 Issue 3
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The development trend of high earth orbit space security and key technologies
HU Haiying, ZHU Yongsheng, JIANG Xinhua
2022, 48(3): 1-10. doi:
10.3969/j.issn.1674 1579.2022.03.001
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The rapid development of aerospace technology promotes the intensification of the militarization of space. The advantage of unique orbital resource advantage of high earth orbit makes it a strategic location for space games between major powers. The typical space security satellites are comprehensively investigated, which are deployed by the U.S. military in high earth orbits. Future, the execution capabilities of these missions are analyzed from the aspects of high earth orbit situational awareness and attack and defense capabilities, and the U.S. military’s high earth orbit space security application capabilities and related key technologies are reviewed and summarized. Finally, relevant suggestions are given for the construction and development of China's high earth orbit space security system.
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Research Progress of Spacecraft GNC Technology in Space Security
ZOU Kui, Ning Yu, LYU Nan, ZHANG Shijun
2022, 48(3): 11-21. doi:
10.3969/j.issn.1674 1579.2022.03.002
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The characteristics of spacecraft guidance, navigation and control (GNC) technology in space based situational awareness, offense and defense system are analyzed. Technical implications, realizing methods and engineering progresses for 6 key technologies of spacecraft GNC system are given. The development roadmap of spacecraft GNC technology in space security, which is expected to provide technical references for future development, is proposed.
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Analysis and Research on GSSAP Observation
WANG Dianjun, WU Guanqun, HAN Lu, JING Yaoxiang, LIU Chonghua, SHANG Xiaoyu
2022, 48(3): 22-28. doi:
10.3969/j.issn.1674 1579.2022.03.003
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Geosynchronous Earth Orbit (GEO) is regarded as a strategic area in the space. Analysis is made based on the space situational satellites, GSSAP (geosynchronous space situational awareness program), which are deployed on GEO by the US space force. Strategies including drifting, maneuvering and conducting are extracted from GSSAP orbit elements history in recent years and analyzed based on GSSAP typical observation scenery. Simulations are conducted based on three provided maneuver strategies. Efficiency are compared under different conditions and the mobility requirement under different inclinations are analyzed. The analysis results can effectively support technical development in Chinese in orbit service and space debris detection.
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Patrol Strategy of the GEO Targets Based on Muti Satellite Formation
LIU Fucheng, YE Lijun
2022, 48(3): 29-38. doi:
10.3969/j.issn.1674 1579.2022.03.004
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The semi major of GEO targets patrol satellite (simplified as “Ptrl sat”) is slightly different from the GEO. Considering the East West drift motion between Ptrl sat and GEO targets, the Ptrl sat can be used to observe the global GEO targets. Taking the Ptrl sat below GEO targets as an example, the patrol effectiveness of GEO targets by single satellite is analyzed. It is pointed out that patrol by single satellite has the problems of imaging blind area and low imaging probability. GEO targets patrol strategy of multi satellites with serial formation is proposed. This strategy not only solves the above problems, but also helps to realize the multi directional and multi angle imaging of GEO targets, which makes the imaging effect better. The design of the simplest serial formation parameters under some typical application condition is introduced.
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On orbit service mission modeling and reinforcement learning service sequence planning in GEO
CAI Yaxing, WANG Xinglong, ZHU Yuehe
2022, 48(3): 39-48. doi:
10.3969/j.issn.1674 1579.2022.03.005
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The on orbit service system for fault repair and function maintenance of geosynchronous satellites is one of the important aerospace projects that are being developed in China. Aiming at the multi target service mission planning problem in geosynchronous earth orbit, an on orbit service mission modeling and reinforcement learning service sequence planning method is proposed in this paper. The spacecraft orbit dynamic model and the Hohmann Lambert four pulses rendezvous model are derived. The mission models are established for several typical on orbit service missions in geosynchronous earth orbit. A target satellite service sequence planning method is developed based on reinforcement learning. Numerical simulations are carried out to verify the effectiveness of the mission planning method. The results illustrate that the proposed method can comprehensively reflect the change of orbit parameters and the consumption of velocity increment and time of the service satellite in both the target rendezvous process and the mission execution process. The optimal service sequence obtained by planning is more applicable in the engineering.
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Optimization method for multi constrained space close sweep trajectory of spacecraft
ZHANG Qingze, YIN Longxun, ZHANG Qiang, WANG Bo, YE Dong, WANG Zuowei,
2022, 48(3): 49-56. doi:
10.3969/j.issn.1674 1579.2022.03.006
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As an important means of space situational awareness, close range skimming can realize the close observation of space targets with less fuel consumption. After approaching the target spacecraft, the mission spacecraft needs to meet many conditions such as appropriate observation distance and illumination angle. This process has strong constraints. Therefore, it is necessary to find an optimization algorithm that can not only quickly optimize, but also can make the optimized orbit meet the mission requirements. In this paper, an optimization algorithm combining multi step optimization and sequential quadratic programming synthesis is designed, and a simplified model is proposed for the constraints of short range observation missions to deal with the nonlinear constraints in the operation process, The most fuel efficient orbital maneuver is achieved under the mission requirements and constraints. The validity of the algorithm and the rationality of the simplified model are verified by the program calculation and simulation.
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Correction Method of Target Control Amount to Final Stage of Fire Control
Mechanism on Space Maneuvering Vehicle
NING Yu, WANG Lusha, DENG Jiaquan, GONG Jinggang, WANG Mingming
2022, 48(3): 57-62. doi:
10.3969/j.issn.1674 1579.2022.03.007
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The space combat environment places high requirements on the pointing accuracy of the platform’s fire control system. A novel approach to improve the control input accuracy of final stage on a space platform fire control mechanism, is presented by using multiplicative measurement model of unit vector. Motivation comes from the situation that the algebra calculation is in contradiction with geometry reality, because of the linearized error of existing additive measurement model. Full correction equation and practical correction equation for the problem are developed. The effects are tested with respect to simulated Gaussian input and sinusoidal input, and the results highlight a non negligible error affecting mirror motion compensation. It is proved that correction equations can be directly utilized by compensation programs. The proposed algorithm is validated by computer simulations of the attitude control correction of a satellite. Numerical tests show the improvements on compensation accuracy.
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Pose Estimation of UltraShort Range Space Non Cooperative Target
Based on TOF Camera
JIANG Lihui, ZHENG Xunjiang, YANG Yifeng, ZHAO Yang, ZHANG Xuwei, SUN Shuodong
2022, 48(3): 63-71. doi:
10.3969/j.issn.1674 1579.2022.03.008
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Based on TOF (time of flight) camera, this paper designs a pose estimation algorithm framework integrating two dimensional gray information and three dimensional point cloud information of the target to solve the relative pose between the tracking star and the non cooperative target. The algorithm framework uses the gray image and three dimensional point cloud data of the target obtained by TOF camera, and uses the arc based ellipse extraction method and ICP (iterative close point) point cloud iteration method to solve the relative pose information of non cooperative targets. This paper combines the image processing algorithm based on gray image and the pose optimization iterative algorithm based on point cloud, which improves the accuracy and robustness of the pose solution algorithm. A ground test verifies the performance of the proposed algorithm framework. The in orbit test shows that the proposed algorithm framework can stably and effectively solve the relative pose of the ultra short range space non cooperative target, provide reliable navigation information for the tracking satellite GNC subsystem, and the relative pose accuracy of TOF camera is better than 2° and 5 cm.
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An In Orbit Calibration Method for Space Manipulator Based on
Hand Eye Cameras
XIAO Shuai, WANG Tao, ZHANG Shuhua, LIANG Jingjing, ZHANG Shijun, LV Wenhua
2022, 48(3): 72-77. doi:
10.3969/j.issn.1674 1579.2022.03.009
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In this paper, an in orbit calibration method for space manipulator based on hand eye cameras is proposed. The nonlinear model of the space manipulator is built via D H method, and calibration cases are designed to obtain calibration data by hand eye cameras. Then, numerical iteration method is utilized directly to solve the nonlinear problem. Thus the D H parameters can be achieved. A case study is carried out on a 7 DOFs space manipulator through simulations, and the results show the validation of the proposed method. The proposed method is directly based on non linear model of space manipulator, so the accuracy loss of linearization can be avoided, which improves the accuracy of in orbit calibration.
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Control Strategy for Multi Arm Cooperative Dexterous Operation of Space
Robotic Arms Based on Axis Invariant Theory
WANG Haiming, ZENG Hong, YU Zhaoji, LUO Ying, JU Hehua, HAN Jianbin, ZHANG Yumei, WANG Yuchao
2022, 48(3): 78-83. doi:
10.3969/j.issn.1674 1579.2022.03.010
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Owing to the future demands of on orbit assembly and repair tasks, a set of multi spacecraft cooperative operation systems composed of information processing satellite, operation satellite, and maintenance satellite for the operation of large targets in space is simulated in this study. In addition, a configuration design for each satellite in combination with on orbit operation task planning is conducted. The dynamic model of a manipulator based on Ju Kane theory is studied, and a fuzzy variable structure controller is designed, which provides a control strategy for multi arm cooperative operation. After measuring the Denavit–Hartenberg engineering parameters of the robotic arm principle prototype, it is introduced into the developed multi body dynamic simulation system to conduct the dynamic simulation and test of the multi arm cooperative operation process. Therefore, the feasibility of the multi spacecraft cooperative operation system is verified, and a technical foundation is laid for future studies on invalid target on orbit operation tasks.
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Equivalent Model of Liquid Sloshing under the Excitation of Small Pulse in
Microgravity Environment
CHEN Zongyu, SONG Zhijun, LV Jing, WANG Tianshu
2022, 48(3): 84-92. doi:
10.3969/j.issn.1674 1579.2022.03.011
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The liquid sloshing problem in the microgravity is studied in this paper. The conclusions of this research are suitable for spacecraft docking, capture and other mission conditions in the field of space attack defense. In this paper, the method of CFD numerical experiment is used to study the sloshing characteristics of liquid in a microgravity environment. The experimental results show that the liquid swaying can be divided into four stages, and the liquid flow law in each stage differs greatly, among which, the response of the liquid filled system in the initial time period of stage 1 is proportional to the excitation. Using this law, the equivalent inertia model of the liquid filled system under small pulse excitation is proposed, and numerical experiments are designed to verify its correctness, with model error of 3.2%, respectively. In addition, the applicability of the equivalent inertia model is also investigated and the optimal range of application of the model is derived in this paper.
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Real Time Identification of the Time Varying Moment of Inertia for Spacecraft
during Fast Orbit Maneuver
WEI Yuanming, WANG Menglei, GENG Yunhai, WU Baolin
2022, 48(3): 93-101. doi:
10.3969/j.issn.1674 1579.2022.03.012
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In mission of space situational awareness, the inertia matrix changes greatly due to the fast fuel consumption, while spacecraft maneuver fast to observe the target in close range. Extended Kalman Filter is modified to identify the time varying inertia matrix in real time when spacecraft maneuver. Firstly, a linear state observer is designed to estimate the angular accelerations of spacecraft. Then, considering the variation of the moment of inertia of the spacecraft, the covariance matrix of prediction error is modified. A filter model is obtained with angular acceleration estimates for time varying inertia matrix identification in real time. Finally, the traditional PD like controller is used for attitude tracking with inertia matrix identification, and the attitude tracking and parameter identification are achieved.
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Intelligence Algorithm for Satellite Based Trigger Mode Detecting System of
Transient Object
XU Anlin, GUO Shaogang, HE Yingbo, JI Yueming
2022, 48(3): 102-108. doi:
10.3969/j.issn.1674 1579.2022.03.013
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The trigger mode intelligence detection system of transient object adopts a new solution: dynamic vision sensor with traditional integral frame sensor. This solution solves the problems of fast moving object detection and recognition via a single sensor. This work studies the intelligence algorithm for fast moving dark objects’ detection, tracking and recognition. By designing the spiking neural network (SNN) de noising algorithm and joint probabilistic data association filter (JPDAF) algorithm, the intelligence object detection, tracking and recognition are achieved.
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Experimental and Simulation Research on the Laser Irradiation
Effects of Star Tracker
HUANG Luming, YANG Yuchuan, WU Zhihua, FU Huailong, GUO Feng, REN Weiyan, ZHANG Xinyu, ZHANG Wei
2022, 48(3): 109-114. doi:
10.3969/j.issn.1674 1579.2022.03.014
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Star sensor is the attitude measurement equipment that satellite mainly depends on in orbit operation stage. It is an important part of satellite guidance, navigation and control subsystem. The star sensor is easily damaged by laser irradiation during its on orbit operation. This paper studies this problem, designs and carries out the damage experiment of laser irradiation and simulation modeling of the star sensor, and completes the model verification. The results show that the laser power density is in the range of 1.2~3.5 ×105 W/cm2, and the APS detector of star sensor has damage effects such as line damage, cross damage and large area damage. The micro morphology observation shows that the circuit layer above the photosensitive element of the detector is damaged. Based on the finite element analysis method, the probability model of APS detector damaged by laser is established. The simulation results are in good agreement with the experimental values, which provides data support and analysis model for studying the damage effect of laser on star sensor.
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