Abstract： Presently, the development of Wolter-I optical system is becoming a new focus, due to the load demand of the X-ray telescope for future pulsar navigation and space astronomical observation mission. And electroforming-nickel replication (ENR) is the optimum technology for manufacturing the mirrors of X-ray optical system. In the present study, the ENR technology process, as well as the development status and future applications of ENR X-ray optical system are introduced. The key technologies and difficulties of the ENR X-ray optical system development are summarized. The methods for improving the development technologies are discussed. This study is consequently beneficial for promoting the development of pulsar autonomous navigation and space exploration in China.

Abstract： Considering disturbance torque, model uncertainty and control torque and angular velocity constraint, a novel PD+ attitude controller for satellite smoothly and quickly tracking a dynamic target is proposed in this paper. The standard PD controller is modified and some additional terms are added so that system can converge along the desired trajectory. The variable structure method is implemented to improve system convergence rate. The coupled terms are added in the Lyapunov function and system stability analysis is much simplified. The worst condition is discussed and the lower and upper bands of V function are considered to ensure the global stability under all conditions. The numerical simulation results are demonstrated to show the effectiveness and superiority of the proposed controller.

Abstract： The maintenance of the satellite formation configuration is crucial to the formation mission. The problem is addressed that the highprecision satellite formation control strategy is complex and difficult to implement. A bionic intelligent satellite formation based on bat flight is proposed. Firstly, the formation dynamics and graph theory are analyzed, and the behavior of bat groups in nature is summarized.A mathematical model of bat flight is given. The virtual center of formation is designed to measure the overall and partial benefits of the satellite formation, and then the bionic formation management strategy is given, the algorithm of which is clear and practical. Finally, the satellite format algorithm is used to control and verify the satellite formation configuration to achieve the stable control with high accuracy and low energy consumption.

Abstract： An intelligent control model is proposed to solve the problem of attitude cooperative control for multisatellite closerange monitoring of space targets. Firstly, a neural network adaptive control model for arbitrary attitude control method is designed. The model does not change the attitude control method itself, but receives the ideal amount of control generated by the ideal control model. The ideal control amount directly generates the control amount suitable for the satellite after passing through the neural network. The multisatellite attitude cooperative control model is derived, utilizing systemlevel state prediction of control system by neural networks, and consensus control protocol. The correctness and effectiveness of prediction control, control result prediction, and cooperative control are demonstrated by numerical simulation using equivalent attitude angle.

Abstract： In view of the phenomenon that the solar wings of multiple MEO navigation satellites have obvious interference torque after deployment, which has certain influence on the stability control of the satellite, this paper presents the calculation method of interference torque according to the dynamic model, attitude, angular velocity and the change of reaction wheel speed. According to the telemetry data of several satellites in orbit, the interference moment produced during deflation is obtained. Using this interference moment for simulation, the results of the satellite simulator are basically the same as those in orbit. This study is helpful for optimizing the process of satellite flight control and guiding the design of satellite exhaust hole.

Abstract： Configuration based on internal 1553B bus is widely usede in attitude and orbit control system of international spacecraft. Aiming at the problems of poor integration,poor extensibility and poor generality caused by the nonuniform bus data protocol of attitude and orbit control system for Chinese spacecraft,internal 1553B Bus data protocol based on ECSS is designed.A fourlayer data protocol architecture is proposed based on the analysis of the data sevice requirments of the internal bus of attitude and orbit control system.The design of the bus protocol based on ECSS in application support layer and link sevice layeris is mainly introduced and the application of the protocol is explained.The application of this international standard protocol is helpful to standardize the 1553B data protocol in attitude and orbit control system for Chinese spacecraft.The integration and extensibility of the attitude and orbit control system and the generalization of onboard equipment(including software) are improved.

Abstract： Knowledge graph technology has developed rapidly in recent years. However, the research on domain knowledge graph construction is preliminary. There are mainly two methods to construct a knowledge graph, one is the topdown, and the other is the bottomup. The former method is more common. However, the topdown has a disadvantage, that ontology learning is too artificial, so that it does not support the construction of a domain knowledge graph which is strong professional and massive. In order to solve this problem, this paper proposes a novel domain knowledge graph construction method, which combining the topdown and the bottomup. We also propose an improved skeletal methodology to ensure the accuracy and coverage in ontology construction. We use rulesbased and semisupervision technology to improve the speed of knowledge extraction. After that, we illustrate the procedure of construction in detail. Moreover, instances prove that the method in this paper is feasible.

Abstract： Hexapod multi-degree-of-freedom micro excitation system is mainly used to simulate onorbit micro vibration environment of the spacecraft payload. However, the existing control method can’t track the low frequency given sinusoidal acceleration, in view of the system which was strongly coupled and seriously nonlinear in the lowfrequency band, and the large phase lag of the controlled object. Aiming at this problem, an improved offline iteration control method combining lead compensation with the multiple frequency notch filter was proposed. The offline iteration performs compensation control, and the lead compensation further compensates the system phase, and the notch filter removes the nonlinear interference. The test results show that when tracking lowfrequency sinusoidal acceleration, compared with the classical offline iteration control method, the improved method has fast convergence and high control precision, compared with the existing adaptive sinusoidal vibration control method, and widens the lower limit of the acceleration control band from 14.5 Hz to 8 Hz, accorded with the requirement of accuracy. The effectiveness of the proposed method can be validated by the experimental results.

Abstract： Based on micro twoaxis turntable and sunlight simulator, an optical signal dynamic excitation system of sun sensor is designed, which is suitable for closedcircuit verification of satellite control subsystem. Through the reasonable selection and design of light source, optical path, integrator and collimator, the irradiance, collimation, irradiance nonuniformity and irradiance instability of the simulated light meet the performance requirements of closedcircuit verification of the control system. Through the designs of structure, slip ring and servo control, the turntable angle control accuracy of 0.02°and 360°angle space can be achieved. The comprehensive test results show that the excitation system can excite the sun sensor effectively during the satellite’s maneuvering in the whole sky, and can be applied to the closedcircuit verification system of the control system.

Abstract： Image component is the key of space optical sensor and camera. Therefore, the antimechanical properties directly affect measurement accuracy. In order to improve the mechanical properties, mechanical analysis of the image component is carried out firstly, which indicates that stiffness and strength meet the requirement. Since simulation analysis can only be used to evaluate the stability qualitatively, experimental method is applied for quantitative evaluation in this paper. Accordingly, a mechanical stability evaluation method is proposed for image component, which includes two indicators, structure slip and optical axis change. Lastly, the evaluation method is applied for mechanical stability analysis, test and measurement. It is confirmed that the evaluation method proposed in this paper is consistent with the evaluation results of the three structures by simulation and experimental. The method can be applied to the space optical instruments which are sensitive to position changes.
Keywords： space optical sensor; image component; mechanical stability; mechanical analysis; quantitative evaluation method