The correlation matrix of gyros is built firstly based on analysis of gyro’s fault model and the correlation between different gyro modules. Then a preliminary result of gyro model diagnosis is obtained using the detectability and separability theorems. Then the ambiguity group of correlation matrix is separated further via improved BHStree. Finally the diagnosability is evaluated by the proposed method. Some suggestions are presented to improve the diagnosability. Moreover, some approaches are given to resolve the key problems in programming for diagnosability analysis and validation.

A lightweight software bus is devised in the article. It attempts to introduce software bus notion into customization and integration of standalone system. Software bus technology is proposed to resolve construction of distributed heterogeneous environment. It is applied broadly in the distributed system. The lightweight software bus reforms structure of traditional software bus by applies dualbus framework and discards unneeded burdensome distributed elements. Therefore, it is qualified as effective software architecture in standalone environment. By means of giving a demonstrated implementation of lightweight software bus architecturebased bank service simulative application, it testifies lightweight software bus effectual as a truss of standalone application’s establishment.

Considering that attack angle, sideslip angle and roll angle have obvious coupled feature, a dynamics model of “X20like”hypersonic vehicle is established in this paper firstly, then an allchannelcoupled characteristic model considering coupled states and coupled inputs be proposed. After that, a controller combined with multiinput multioutput (MIMO) golden section adaptive control law, derivative control law and integral control law is designed for the system. At last, tracking ability and robustness of the controller are approved by simulations of both accurate model and interference model. Simulations also show that the all channelcoupled characteristic model controller is better for attitude control of hypersonic vehicles than the single channel one.

GNC system of rendezvous and docking in space involves two attitude and orbit control systems of both the Chaser satellite and Target satellite. The simulation of this system is more complicated. A standard method about several simulation models, such as orbit dynamics, attitude dynamics, relative dynamics, sensor models etc. is proposed in this paper. Based on these standard models and an automatic coding method, a GNC simulation system for rendezvous and docking in space is built. This system achieves  high degree of modularization and automatization, and has high expansibility and generality. This system achieves a standard simulation of the two satellites, and helps researchers improve efficiency and provides support for design and simulation of RVD control system greatly.

A satellite attitude determination method using magnetometer is expounded in this paper. Based on the telemetering data provided by a satellite in the orbit, an attitude determination experiment on the ground is conducted, and the high accuracy attitude determination is also gotten. This experiment result shows the feasibility of the proposed attitude determination scheme.

The fault safety design is one of the key factors to ensure the GEO satellite in service with long life and high reliability. Firstly, the investigation the fault safety design of the international topranking GEO satellite is done in detail. Then the features of the fault safety design of domestic GEO satellite are described briefly, and the author’s opinions are mentioned. Finally, the suggestion and idea are proposed to improve the fault safety design of the domestic GEO satellite in future according to synthesis of the investigation and study. The suggestion and idea are expected to use for helpful reference to the fault safety design of the domestic GEO satellite, and be useful for the improvement of the reliability of the domestic GEO satellite.

We introduce an image acquisition and processing method of miniature sun sensor in this paper. The miniature sun sensor is designed using aerospace CMOS APS image sensor units and the field programmable gate array(FPGA). Utilizing FPGA, we realize the control of the image sensor units and image data detection, acquisition, storage, transmission, and preprocessing. The calibration and experimental results illustrate that the performance of the designed miniature sun sensor almost reaches the level of other similar international aerospace products.

How to use μVision extend programming interface and the steps to build a software test environment are described in this paper. It is a low cost and short development cycle method to build a software running environment without any hardware.The software developer and tester can use it quickly to test software in time.

A design scheme of the faulttolerant multiprocessor is proposed to improve the reliability of the MPSOC processor based on voting by software and arbitrating by hardware in this paper. The feasibility of the scheme is validated through experiments.

For overproof in high frequency region in 200N·m·s CMG Random Vibration real situation test，the primary factors for the overproof are analyzed，the solution of overproof in high frequency region Random Vibration test through improving the performance of vibration test fixture,and adding viscoelastic damper between vibration test fixture and shaker panel is proposed, which is confirmed by Random Vibration qualification test.

A gimbal drive assembly (GDA) for intersatellite link antenna (ILA) is required with long life, huge drive torque, high pointing accuracy, and adaptability to complex and atrocious space environments. Harmonic drive with many advantages such as high reduction ratio, high loading capacity, and high transmission accuracy is applied widely in aeronautics and astronautics fields. Design constraints are briefly analyzed, advantages and disadvantages among three different types of dualaxis structures are campared, a type of structure layout for the single axis actuator is proposed, motor, harmonic drive and angle sensor as well as of points thermal interface design are analyzed, critical techniques including compact and lightweight structure, long life lubrication and high pointing accuracy are pointed,and finally test methods for verifing long life and high pointing accuracy are presented in this paper.