The explicit guidance method can be used in the research of the midcourse correction of MoonEarth return trajectory, as the algorithm is simple, computationally fast and the thought is widely employed in practice. On the premise that the aim point is predicted, the velocity increment needed from the correction point to aim point is computed using the twobody model to replace the one needed from correction point to nominal location point under the multibody model. According to this method, the explicit guidance correction scheme of MoonEarth return trajectory based on subsection aim point prediction is presented, while the midcourse correction strategy is divided into moonsection and earthsection. Finally, the adaptability of the scheme is validated by example simulation and MonteCarlo simulation and the advantages of thd scheme are stuted.

The infrared detector is a kind of indispensable detectors in satellite attitude control systems. The international research progress of thermistor wafer electrode is summarized, especially its design and preparation process. The internal stress caused by various thin film metal electrodes is also analyzed. It is found that, in order to get a low stress solder joint and high reliability infrared detector, the process parameters such as electrode structure, materials, the thickness of the film, preparation method and heat treatment should be considered. A Ti/Au double-layer structure electrode is employed to the thermistor wafer to achieve an ideal noise coefficient and a good bonding strength of the joint.

A sliding mode rate damping controller is designed for underactuated spacecraft with one of the three axes actuators invalid. The stabilization problem of the system is addressed, and the disturbance rejection performance is analyzed. The guideline of tuning parameters for the controller is presented. By regarding product of inertia as external disturbance, the problem of designing a controller for underactuated spacecraft with non-diagonal inertia matrix is resolved. The application aspects are considered, such as the switching feature of thrusters, the saturation characteristics of rate gyroscope, the existence of external disturbance and the non-diagonal property of the inertia matrix. Numerical simulation results demonstrate the effectiveness and practicability of the designed controller.

A time synchronization method for regional constellation satellites via estimating the relative clock errors is presented in this paper. The realization principle of this method is introduced, and the system state and measurement equations of clocks are established. Finally, a Kalman filtering algorithm applicable to time synchronization of constellation is designed. Simulation results show that this method is feasible.

Based on the results of no-load experiment on solenoid valve and its model，factors which influence solenoid valve’s response time are analyzed. Two models are set up by using of FEM (finite element method) and magnetic circuit simulation. Using the two models, the characteristics of the response are calculated by changing the values of spring rate, the predeformation of spring, the mass of armature, the resistance of discharge circuit, the amount of windings and void air gap. Moreover, how these factors influence the characteristics of the response is obtained. The results of simulation are basically consistent with the experiments. And the advantage and disadvantage of the two models are analyzed. Finally what should be paid attention to in the progress of solenoid valve’s design and manufacture is partially summarized, which can give a good help to the work of solenoid valve design in the future.

The control capability of gimbal servo system is one of the key characteristics of the single gimbal control moment gyro (SGCMG). This paper introduces a control system based on Fuzzy PI controller. Considering the drawbacks of the traditional PI controller, we design a fuzzy control algorithm with parameter self-tuning capability based on fuzzy control technology. Simulation results show that the proposed control strategy has faster response than the traditional ones. Meanwhile, the overshoot is smaller and it has no parameter tuning requirement. Besides, the proposed controller is robust and has excellent tracking capability.

Hysteresis gyro motor is one of the significant parts of gyro in an inertial sensor. Meanwhile, the lifespan of hysteresis gyro motor determines the lifespan of the inertial sensor. Focused on the main failure mode, lubrication system is improved to prolong the lifespan of hysteresis gyro motor. The lifespan test demonstrates that the MTTF（mean time to failure）is longer than thirty thousand hours.

Considering the demand of the hardware-in-loop simulation for manual control rendezvous and docking, a simulation scheme is provided to validate the performance of sensors and the control law of manual control rendezvous and docking, named as 9-degree freedom hardwareinloop simulation system for manual control rendezvous and docking. The scheme is applied to the design of the manual rendezvous and docking of ShenZhou-9 spaceship and the simulation results of the control system are provided. The results of the manual rendezvous and docking of ShenZhou-9 spaceship and Tiangong-1 on-orbit confirm the validity of this simulation system design.

For solving the problem of large-angle maneuver control for satellites subject to input saturation, a low gain feedback control law based on characteristic model is designed. The characteristic model is established in the form of a secondorder timevariable difference equation based on the dynamic model of the initial system, and the range of characteristic model parameters is calculated. The low-gain feedback law is instructed and is designed based on the characteristic model to deal with the performance deterioration or instability caused by input saturation. Characteristic model extends the application range of low-gain feedback law to some complex systems. By simulating single axes attitude maneuvering process of satellites subject to input saturation, availability of the lowgain control law based on this characteristic model is validated.

In order to reduce the cost and improve the efficiency of regression testing, this paper presents a repression testing method based on the analysis of the change of domain. The change types are described in detail. And the corresponding domain analysis strategy is put forward for each type. The results show that the method has good technical guidance and is easy to use, which improves the adequacy of the regression testing and further ensures the quality of the test.

In combination with the results of the failure mechanism, which was based upon the previous life test of critical components of LIPS-200 ion thruster, this paper synthesizes the academic progress with respect to the lifetime of ion propulsion system by numerical simulation and theoretical analysis. The progress comprises several segments, such as the analysis of electron backstreaming of ion optics, structure failure of accelerator grid and the absolute depletion failure mode of hollow cathode emitter. A credible life range of critical components is derived. The result shows that the ion thruster can satisfy the design configuration. Furthermore, it can provide reference for the lifetime evaluation and performance optimization of ion thruster.

By means of putting permanent-magnet into solenoid valve’s magnetic circuit, a pre-bias magnetic field can be produced in the circuit to get a faster response speed，which is helpful for reducing effective permeability and induction. This design is validated by finite element simulation. With simple structure and fast response speed，the high speed solenoid valve based on magnet prebias can improve the impulse performance of bipropellant thruster，and meet the challenge of accurate control for the satellite in future.