To study the vibration control of satellite with flexible solar panels under disturbance, the disposable micro impulse thruster array（DMITA） is propose to settle on the solar panels as actuators for active vibration control. The DMITA is characterized by small size, low cost and low energy consumption. The application scheme of disposable micro impulse thruster active vibration control system（DMITAVCS） is introduced and the attitude dynamic equations of flexible satellite with DMITAVCS is derived by hybrid coordinate method. The optimal energy principle for settlement location of DMITA is also analyzed. Numerical simulations demonstrate that the DMITAVCS can suppress the vibration of flexible satellite in a short time, which benefits from the long arm of force produced by the DMITA settled on the solar panels.

In this paper, a new method for maintaining and reconfiguring the solar sail spacecraft formation is proposed, based on the fact that the orbit of the high areatomass ratio spacecraft can be controlled via solar radiation pressure. The difference of solar radiation pressure on the formation members can be adjusted by controlling attitude angles and reflection coefficient of the chief and deputy solar sail spacecraft, and the continuous low thrust can be produced for counteracting the perturbation difference in relative motion of formation constellation members or orbital maneuvers, thus achieving the purpose of formation configuration maintenance and formation reconfiguration. Under the condition that attitude angles and the reflection coefficient of the chief solar sail spacecraft are relatively fixed, the simulation results show that the purpose of longterm formation keeping of solar sail spacecraft formations in Sunsynchronous orbit can be achieved by sliding mode control, which is able to counteract the perturbation difference in relative motion of formation constellation members by controlling attitude angles and reflection coefficient of the deputy solar sail spacecraft. And in the same way, formation reconfiguration can be achieved by using openloop control after long period.

The hazardavoidance control for a liquidfilled lunar lander is considered in this paper. A threedimensional spherical pendulum is used for the mechanical equivalent model of the liquid sloshing. Considering the threedimensional dynamics combined of spherical pendulum and rigid body of spacecraft, the vector dynamics equations are given as well as the projected coordinates of each vector variables. With these equations, a combined position and attitude controller is designed, which can stabilize the position and attitude of the rigid body. Moreover, this controller only depends on the position and attitude of rigid body, and independent of liquid sloshing angle or sloshing dynamics. It thus leads to the convenience for the practical applications. The stability of closedloop system is given via LaSalle invariance principle, and the control parameters are suggested for the asymptotical stability of the system when the reference vertical attitude is chosen. Finally the effectiveness of the proposed control is validated via numerical simulations.

Aiming at the mission of Lunar south pole exploration, a launch window searching method of three stages is proposed, taking illumination conditions, the status quo of Chinese ground based TT&C systems and the constraint conditions of Earth reentry process into consideration. A return trajectory is calculated by an improved multiconic method, which combines the lunar oblateness correction in trajectories propagation. Furthermore, return trajectory simulations from Lunar south pole are carried out based on an assumed site in Shackleton rim in 2020. Results show that this launch window searching method is effective and accurate. Additionally, the improved multiconic method can reduce the terminal boundary errors effectively.

The adaptive control problem of twocraft Coulomb formation configuration keeping at geostationary orbit is investigated. the nonlinear relative kinetic model of the twocraft Coulomb formation at geostationary orbit is established. Based on the nonlinear dynamic model, considering the unmodeled disturbance force in space environment and the model error generated during the nonlinear dynamic model, an adaptive control law is designed. The numerical simulation is carried out, and the results are compared with the traditional PID control. The simulation results show that the proposed adaptive control law has fast response, good stability, and the formation configuration can converge to the expected one. The control performance is also proved to be better than PID control.

The dynamics of spacecraft with root damper of antenna mast is investigated. The system consists of a spacecraft mainbody, several sixfreedom rigid damper platforms and flexible appendages which are connected with the damper platforms. The damper platforms are connected with the mainbody by elasticitydamp mechanisms. Hybrid coordinates are used to describe the system motion. System dynamics which are established via using Kane’s equations have better versatility and are advantageous to controller design. Numerical simulation results show that the damper can efficiently attenuate elastic vibration of the appendages, which is beneficial for spacecraft rapid stabilization after disturbance.

Abstract：Electric propulsion systems have huge power demands. To raise the utilization efficiency of satellite resources, work strategies of electric propulsion systems are proposed based on joint power supply from solar cells and batteries with complex engineering constrains. The impact analysis of different kinds of electric propulsions, different configurations of solar panels and power supply systems are introduced to obtain the optimization strategy during the periods of north south station keeping(NSSK), east west station keeping(EWSK) and momentum unloading(MU). Finally, simulation examples validate that reasonable work strategies can be achieved to meet the high power demands of the electric propulsion under complex engineering constrains and suitable design margin.

Considering the characteristics of closerange rendezvous and docking, an idea of using guidance impulse to determine the safety belt in rendezvous and docking is presented. Four belts, including the uncontrolled belt, the modified belt, the guarded belt and the urgency belt of retreat, are designed near the standard trajectory. The guidance strategy based on safety belt is also designed. The simulation results indicate that the guidance strategy can detect a part of fault immediately, and consume less fuel. It is a guidance strategy which is good at both of fuel consuming and trajectory safety.

Nonlinear factors such as friction and clearance have definite influences on mechanical properties of electric actuator structure. To investigate the impact of nonlinearity on actuator control, typical nonlinear characteristics existing in the transmission device are introduced. A new transmission device is designed, which has low friction and controllable clearance. Experiment and simulation results show that the new transmission device has better performances in friction and clearance condition compared with general transmission structure. With new transmission device, both control accuracy and stability of actuator are achieved, which can provide basis for the analysis of structure properties and the research of control system.

To solve pattern “double lock & unlock” and pattern “misuse of volatile”, a detection method based on coding rules is proposed. Firstly, the failure mechanism is analyzed, and then 3 coding rules are proposed to avoid corresponding defects in development stage. These rules and corresponding checking methods are researched and implemented by extending an existing static analysis tool named SpaceCCH. The evaluation result based on real world onboard software show that, the extended SpaceCCH can find rules violations efficiently with low false positive rate and low false negative rate, by which the data race bugs of pattern “double lock & unlock” and pattern “misuse of volatile” can be avoided effectively. The main contribution of this paper is that the detection of a really complex bug is transformed to corresponding coding rules and their automatic detection.

In order to develop the general construction of the aerospace embedded software testing environment, a general method for the aerospace dynamics software design is proposed. Based on the characteristics of aerospace dynamic simulation, a flexible generic and extensible software framework, interface data structures as well as interface functions are proposed, which are applied to all the simulation requirements of spacecraft under developing. The given method is applied in practical work. The programming progress is significantly increased, and the dynamics software is running stably and with high precision.

With the rapid growth of software complexity, the traditional testing method is gradually difficult to meet the reliability and security requirements of spacecraft operating system. Formal method is gradually becoming an effective guarantee for spacecraft operating system security and reliability. Based on the Rodin platform, using EventB formal language, through the requirements and design rewrite and formulate the refinement strategy and stepwise refinement method, the requirement layer and design layer formal model is established for the interruptmanagement module of the embedded operating system SpaceOS2. Model checking and theorem proving are combined to verify the validity and safety of the model.