A selforganizing architecture for the control system of spacecraft is proposed to solve the problem that the computing efficiency is insufficient for many redundant computing units. Based on cloud computing and high speed interconnected net, the redundant backup of the single node is cancelled in the proposed architecture. The computing capability of whole system is the staunch supporter for every single node. If one node shuts down, its program code and data will be transferred to other working nodes dynamically to continue its functions. This selforganizing manner realizes the reconstruction of computing architecture for system with faults.

In relative navigation model, there are linear model and nonlinear model. And the navigation algorithm based on Kalman filtering has high computational complexity in multisensor information fusion. Aiming at these problems, the hybrid information filtering is proposed. To overcome the influence of inaccuracy of noise statistic characteristic, the relative navigation based on adaptive hybrid information filtering is also proposed. Theoretical analysis and numerical simulation show that the hybrid information filtering has lower computational complexity in multisensor information fusion than the navigation algorithm based on Kalman filtering. And the navigation task with linear and nonlinear hybrid models also can be completed with the hybrid information filtering. Besides the above characteristics, via adaptive adjusting the measurement covariance matrix, the effect of inaccurate noise statistic characteristic can be reduced.

An adaptive discretetime variable structure control algorithm is proposed for large angle attitude maneuver of rigid spacecraft in the presence of parametric uncertainty and external disturbances. The affine system including attitude kinematics and dynamics equations is modeled and decoupled by inputoutput feedback linearization. Then the linear dynamic equations are discretized and the discretetime variable structure control law is obtained via the exponential approach law. Finally, the parametric adaptation law is designed based on Lyapunov stability theory to overcome multiple timevarying and disturbance terms in models. The simulation results indicate that the proposed algorithm can decrease the attitude tracking deviations caused by the parametric perturbations and external disturbances effectively. In addition, the system ensures the accuracy and robustness of the large angle attitude maneuver and eliminates the conventional control chattering.

The usual orbit computation methods include the analytical and numerical approaches. For satellites in high eccentricity orbit, numerical method brings more computation, and a perturbation analysis solution is inapplicable. A new method of prediction for high eccentricity orbit is developed, which adopts the position bias between the precise trajectory and twobody dynamic orbit to fit the Chebyshev polynomial coefficients. This method can improve the precision of fitting orbit, and the positions and velocities of the high eccentricity orbit satellites can be calculated more precisely, easily and quickly.

Based on the magneticfieldoriented vector control principle, a microstep drive control strategy for the permanentmagnet synchronous motor (PMSM) is proposed in this paper. By maintaining a constant statorcurrent vector and evenly varying vector position, the amplitude of the stator MMF is unchanged while its position moves smoothly, so as to orient the solar array toward the sun. The results show that the proposed microstep drive control method achieves the drive performance when the solar array drive mechanism drives the simulated solar array load. The given torque current is suggested to be selected according to the power efficiency and solar array driving speed stability in the design and implementation process. The effectiveness of the control method is further confirmed. The control method can be used in engineering practice.

The principles of laser coherent beam combination that can enhance the output power and improve the beam quality are introduced. The developments of coherent beam combining technique are reviewed and discussed. Two beam combining approaches that respectively based on active phase control and passive phase control are compared. Based on the master oscillator power amplifier (MOPA), the active phase control can obtain a neardiffraction limited, stable and high brightness farfield laser beam. As a result, the active phase control is considered to be a technical support for a long distance, high rate data space optical communication system. It provides valuable information on the trends of laser coherent beam combination technology and has some important significance for space optical communication.

To solve the key problem in the design of miniature integrative encoded sun sensor, FPGA is used instead of the 80C31 microprocessor system. To calculate the angle in FPGA, CORDIC algorithm of fine code is studied. Almost all the functions of signal processing of sun sensor are realized in FPGA, including multiplexer and AD controlling, data collecting, angle calculating and UART. Flexibility board is also used to connect the analog board and digital board so as to realize the miniature assembling. The performance of the miniature integrative coded sun sensor is listed as the following: mass 0.5 kg, power consumption 0.5 W,accuracy 0.05°(3σ), resolution 14″, update rate 40 Hz.

In order to diagnose whether or not tiny air leak from flywheel housing before its delivery, based on linear regression analysis of correlation of flywheel rotating speed and work time, a construction method of flywheel sealing leak prediction model is developed. For the purpose of insuring the accuracy of model and practicability in engineering, the variance, statistical test and correlation of the model are analyzed. This construction method is suitable for all kinds of flywheels or other performance parameters to construct the corresponding prediction models, and a high reliability of flywheel sealing can be insured before they are delivered to customers.

During developing the software for spacecraft, there are many tools to use. This paper designs and implements an integrated development environment, which is composed of various components, including project management, editor, syntax checker, compiler, linker and debugger. Now, the IDE is applied to develop the software of spacecraft. As a result, it not only shortens the development cycle, but also improves the software quality. Meanwhile, the result of this paper can be a reference for the development of integrated development environment.

One kind of pseudorate modulator designed with digital integrated FPGA and its application are introduced. Only one integrated digital chip is needed to integrate threechannel modulator. This modulator is designed with digital circuit, and is different from that designed with analog circuits or software. The exponent operation of the oneorder feedback logic is substituted by digital shift. It has the same characteristics of high real time, high precision compared with that implemented by analog circuits, and has the same characteristics of convenience and flexibility compared with that implemented by software. This modulator can overcome the shortcoming of that implemented by analog circuits or software. It is applicable to the satellite control system with incorporated information and integrated electronic technology.

Considering the precision losing and error propagation of floatingpoint arithmetic operation in space embedded software, the paper introduces the floatingpoint database, the precision losing causation, and the error sources and error measure. Then, with several examples, the typical floatingpoint arithmetic operations in space embedded software are analyzed, which supply a reference for space software error control.

Three interrupt resource conflict instances of spacecraft software in C51 language are summarized. The existing methods of software resource conflict analysis are summarized and analyzed. Based on static analysis technique, a new resource conflict analysis method is advanced on C51 language software, and the solutions for above 3 instances are given.