The first autonomous non-planar formation flying-around in China was finished successfully by SJ-9A and SJ-9B satellites on November 5, 2012. The collocations and design requirements are introduced. The problems of attitude and orbit coupling and thrust loss are described and analyzed, and the disposals in engineering and numerical simulation results are also given. The results in orbit show that the orbit control time is optimized reasonably and the accuracy of orbit control is guaranteed by amending the orbit control accelerations in uplink via precontrol simulation.

To satisfy the need of outfield tests of star sensors, a method is put forward to construct the reference attitude benchmark. Firstly, its basic principle is introduced. Then, all the separate conversion matrixes are deduced, which include the conversion matrix Cwi responsible for the transformation from the earth centered inertial frame i to the earth-centered earth-fixed frame w according to the time of an atomic clock, the conversion matrix Ctwfrom frame w to the geographic frame t, the conversion matrix Cpt from frame t to the platform frame p, and the matrix Csp from frame p to the star sensors frame s. As a result, the attitude matrix Csi of the star sensor relative to the frame i can be obtained using all the three matrixes as the multiplicative factors. Next, the reference attitude angles for star sensor outfield tests can be calculated from the transformation matrix Csi from frame i to s. Finally, the computer program is given to solve the reference attitudes, and the error curves are drawn about the three axis attitude angles, whose absolute maximum error is less than 0.25″. The simulating results manifest that the method by precise timing to acquire the absolute reference attitude benchmark is feasible for star sensor outfield tests.

Throttling cavitation venturi, which can control the propellant flux and thrust in a wide range, is an important component of throttling rocket engine. Based on the designed model, a numerical simulation of cavitation flow in venturi is performed with a mixture model based on Rayleigh-Plesset equation. The results indicate that the linear throttling cavitation venturi can regulate the propellant flux in a wide range. Furthermore, the flux changes linearly with respect to the movement of actuator. The proposed cavitation venturi can satisfy the need of design.

In the microgravity environment, the position of the ullage bubble is uncertain. It’s hard to vent and control the center of mass for the receiver tank on mission of on-orbit refilling. The test tank of NASA FARE II is taken as reference. According to the theory of surface tension tank, calculation model is established. Under the conditions of different refill flow rates, the gas-liquid distribution in the vane-type surface-tension tank is studied with the method of numerical simulation. The hydrazine is chosen as working liquid. Using the CFD（computational fluid dynamics） software Fluent, the process of vane-type tank on-orbit refilling is simulated. Simulation results show that the greater the inflow rate is, the higher the gas-liquid interface protrudes. When the inflow rate exceeds the critical value, liquid is vented. The results can provide reference for the control of refill flow rate.

Aimed at the problem of choosing appropriate amount and suitable arrangement of thrusters for satellite attitude control, four different configurations of thrusters are summarized. Thruster burn time is given under phase-plane control, and the design criterion is proposed with comparing of control accuracy, fuel consumption and reliability under different configurations. This criterion shows that the reliability and fuel consumption are the primary reference in the design of thruster configuration.

For meeting the general utility of satellite control system testing, a test framework is proposed based on ATS（automated test system） concept and ATML（automatic test markup language） standard. The universal testing platform is composed of three parts: general test station, test adapter, integration development and running environment. The test requirements and test capability are decoupled through the system description scheme using ATML standard and signaloriented method. The general utility is realized via configuring the universal testing platform according to the test capability and requirements.

High credibility ground test of spacecraft control system becomes very important since modern spacecrafts are complex and the performance requirements are higher. Based on engineering applications, this paper introduces the theories and technologies of high credibility ground test of spacecraft control system. In this paper, we present the definition and factors of testing credibility, and introduce the flexible prototype test technique, the methods of spacecraft control system test, high precision sampling, high credibility signal resource technique, etc.

For a swing infrared earth sensor (IRES), the characteristics of the chord information from each single channel are given when only two bolometer detectors work. An attitude determination method is proposed using the chord information of the two bolometer detectors, and the bolometer detector redundancy is also discussed. The simulation and experimental results indicate that the attitude determination method is very simple and practicable in engineering application. Meanwhile，the detector redundancy improves the reliability of the IRES.

In order to achieve precise synchronization among multi-module redundancy embedded electronic system of aerospace，this paper deals with the time synchronizing algorithm of the hot redundancy systems based on IEEE1588 protocol and FPGA（field programmable gate array）/ASIC(application specific integrated circuit), which combines the software with the hardware. This method can achieve the same precision as the hardware synchronizing and owns the fault-tolerant ability. The time synchronization precision of this algorithm is at hundreds of nanoseconds, and the algorithm is validated by system simulation.

Retransmission mechanisms in end-to-end manner and segmentation manner are proposed for reliable data transmission requirement in the satellite network. The performances of retransmission mechanisms are analyzed in all scenarios for single packet and multi-packet reliable transmission respectively. The affection factors are also discussed. The analysis and simulation results show that retransmission mechanism has less influence on single packet transmission, but the segmentation retransmission mechanism is fitter for multi-packet transmission to achieve higher transfer efficiency, especially when the hop number, the packet number, and the packet lost rate are big.

Based on the problems discovered in thirdparty software testing, 6 kinds of programming errors of spacecraft software in C language are listed and analyzed in detail. The code analysis technique is proposed to check the software safety vulnerability, and a new method is also proposed to constitute the safety programming rules and analyze the code by using code analysis method, based on the programming language using errors.By using these methods the above 6 kinds of common programming errors and other serious errors can be effectively checked.

Here we analyze the noise contribution to electron multiplying CCD based on high dynamic range requirements of star tracker, and derive the signal-to-noise ratio computation formula for star detection. We also propose a design method for electronmultiplication voltage and cooling temperature. The attitude measurement error is less than 30″ when angular rate is 10(°)/s, which verifies the correctness of the designed method.