Xray pulsar navigation test satellite is a dedicated test satellite developed by China. This satellite has obtained a great mount of science data during the flight of more than 4 months. In this paper, the first analysis result of science data that was collected by the focusing Xray detector carried by the satellite in recently 4 months. The observation mode of this detector is introduced, the method of the science data analysis as well as the pulsar parameters correction are provided, the refined pulsar parameters are estimated, the performance of the detector in orbit is tested, and the question whether homemade Xray detector is able to detect the pulsars is answered.

Trajectory tracking control problems of freefloating space manipulators with uncertainty are considered, and a robust adaptive control method is put forward based on neural network. The dynamics model of uncertain space manipulators is established, and the unknown nonlinear parts of system model are considered. A neural network controller is designed to approach the unknown uncertain parts, by the way the traditional upper bound of conservative is be avoided estimating. Taylor technology is used to linearize the Gaussian function of neural network hidden layer. Then the adaptive learning laws of the network weight parameters, the hidden layer center and width of Gaussian function are designed to guarantee the online realtime adjustment. The robust adaptive controller is designed to compensate the amount of highorder item and the approximation errors for better control accuracy. The uniformly ultimately bounded (UUB) of the closedloop system is proved based on the Lyapunov theory. Simulation results show that the proposed control method can get better control accuracy, and the controller has important engineering value for the space manipulator.

To design the fuel optimal ascent trajectory of space planes under complex and multiconstrained conditions, a strategy is proposed to segment the ascent trajectory according to the thrust characteristics of the engines. When the original optimal control problem is transformed into a multistage optimal control problem, the Gauss pseudospectral method is used for parallel optimization. Numerical result shows that this strategy can easily satisfy the constraints of state variables when the engine switches and generates the fuel optimal trajectory within short computing time. It is verified that the optimization strategy proposed is efficient.

A controller is designed to restrain the inplane libration of a tethered satellite system (TSS). To stabilize the inplane subsystem of TSS, a hierarchical iterative nonlinear sliding mode control is proposed. The stability of the closedloop system is also proved. The validity of the proposed algorithm is demonstrated by numerical simulation results. Moreover, the advantages of the algorithm are presented via comparing with the traditional hierarchical sliding mode control.

Atmospheric turbulence is a key factor that affects the high altitude airship movement in horizontal direction. The turbulence disturbance has a serious impact on the safety and stationkeeping capability of the airship. Overcoming the turbulent disturbance has a direct influence on the payload carrying and flight duration. According to the characteristics of the high altitude turbulence and the effect on the attitude adjustment, firstly, the turbulent flow transfer function model is built. Secondly, the dynamic model of the airship under the disturbance of the wind field is constructed according to the wind velocity triangle relationship. Lastly, an internalmodel control method is introduced to design the attitude control system of the airship. The perturbation signal is fed back to the input of the system and thus can control the perturbation directly. The simulation results indicate that the designed controller can overcome the turbulent disturbance impact effectively.

In order to compensate for the shortcomings of singlesatellite network and combine the advantages of singlesatellite network so as to provide users with a better quality of service, hybrid satellite networks are proposed. Every algorithm has different impact on the quality of service; so many current researches focus on how to design better hybrid satellite networks and satellite access method. After analyzing the characteristics of the GEO, MEO, LEO and HEO satellite networks and comparing their performances and complexities, a double 5 GEO +66 LEO satellite network and a satellite selection algorithm with multiple QoS constraints are designed in this paper. Finally, the correctness of this algorithm is verified via simulation.

The low earth orbit (LEO) spacecraft has high requirement for the stability of navigation system. If the standard Kalman filter is used to the integrated navigation system, large errors might occur and the navigation accuracy of the LEO spacecraft will decrease when abnormal disturbances occur. Hence, an adaptive robust filter is proposed to apply to the navigation system of LEO spacecraft, and then the INS/CNS/GNSS integrated navigation is designed based on it. To verify the effectiveness of the adaptive robust filter, simulation experiments are implemented respectively for the integrated navigations with the standard Kalman filter and adaptive robust filter.

Focusing on the requirement of Los measurement accuracy for the optical satellite observation platform, an error distribution method is studied based on interval analysis theory. Based on the structure of advanced satellite, turntable and camera, the lineofsight vector measurement model and measurement error model between the space camera and the target are established. According to the interval analysis theory, the evaluation method of the error sensitivity is presented. According to the working space of satellite observation platform, the global maximum sensitivity of the error source in threeaxis is get. Setting the global maximum sensitivity as weight coefficient, the error distribution model of the lineofsight measurement of satellite borne observation platform is established. The maximum of 13 error sources is reached by genetic algorithm. Monte Carlo simulation shows that the method is effective, and the method is also applicable to the error distribution of the airborne, vehicle and other observation platforms.

A testing system is proposed towards new conditions for both ground and onorbit test. The system has been implied in a satellite and has done a good job in test. Ground testing system consists of dynamical simulator of satellite & robots, onboard module simulators, ATS and 3D display system. The system can verify logic in onboard computer and behavior of electric interface. Onorbit testing system is supplemented by the threedimensional obstacle avoidance system and the image analysis system, which works in real time with high visualization.

 The principle of rendezvous and docking image (RVD) sensor is introduced. The measure system of onetarget RVD image sensor with image track windows is presented. Without any change in the hardware of the sensor, four improvements of embedded software are brought to multitarget RVD image sensor, such as multitarget calculating track windows, multitarget prediction of image row windows, multitarget image match and multitarget results optimization. The safety level ascends when the measure system becomes multispare mode. The automatic switch within different targets improves the process of RVD. The independence level is greatly improved while the switch of different camera is replaced by different spots in images from one camera. The improvements are already used in many missions of RVD in China.