Abstract：The spacecraft intelligent autonomous control (SIAC) is a complex and difficult problem. At first, the international recent advances in SIAC are reviewed. Beijing Institute of Control Engineering has obtained a series of results in this field during the past thirty years. However, there still exist many matters in SIAC needed to be studied further, including spacecraft autonomous navigation, the theory and method of SIAC, fault autonomous diagnosis and reconstruction, information autonomous management, and so on. At last, the development objective and the general planning of SIAC are presented.

Abstract：In space missions, such as rendezvous and docking, onorbit servicing, closerange surveillance as well as formation flying, neighboring spacecraft are needed to operate by using relative navigation and control technology. Specific missions in such field are reviewed, and their mission purpose and major features are particularly focused on with respect to relative control methods, the measuring devices and propulsion systems. The tendency of such technology is also summarized.

Abstract：Solid propellant microthruster array (SPMTA) has the advantages of high accuracy, low impulse, high density and rapid assembling. It is quite suitable for micro/nanosatellite in special mission, micro/nanosatellite formation flight and rapid response satellite. In this paper, the structure principle, features and applications of micro electro mechanical systems (MEMS) SPMTA are introduced. The international development status of MEMS SPMTA is investigated. Based on the investigation, the key techniques of MEMS SPMTA and some future development suggestions are presented.

Abstract：The configuration and deployment of noncoplanar solar arrays are introduced briefly. Because of dynamic coupling effects, the deployment process of the noncoplanar solar arrays affects the attitude of the spacecraft. The angular momentum equation is analyzed and the joint path is parameterized by a cosine function. Then, the objective function is defined according to the variation of the spacecraft attitude. At last, genetic algorithm is adopted to search the optimal parameters which are used to obtain a path that when the noncoplanar configuration solar arrays deploy according to this path, its affect to the spacecraft will reduce to a relatively very small range. At last, one kind of noncoplanar configuration solar arrays is given, and the effectiveness of above method is verified by simulation results.

Abstract：A tracking control with prescribed performance is investigated for a class of uncertain oneorder fast timevarying systems. Such control problem is firstly transformed into one without constraints by introducing a state transformation. Then, a robust adaptive controller is proposed. Our scheme can ensure not only that the systems satisfy the given performance constraints, but also the ultimate bound of the new state variable only depends on some control parameters. As the control parameters are known, this scheme can provide a good estimation of this bound. Finally, numerical simulations verify the validity of the proposed approach.

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Abstract：Manual teleoperation rendezvous and docking (RVD) is referred to as the concept that the chaser spacecraft is controlled remotely through teleoperation approach. It can be used as a backup for autonomous RVD for the unmanned spacecraft. The concept of manual teleoperation RVD was introduced briefly. Three manual teleoperation RVD schemes is presented, and a teleoperation RVD system is designed that is easy to realize in engineering project. The key technologies of teleoperation RVD, such as control, time delay and video compressing, is analyzed and the corresponding resolution is given. The teleoperation RVD experiments are carried out for verifying the design. The results show that the design is feasible.

Abstract：Based on a 4quadrant silicon cell, the sun incident angle in two axes can be measured by a dualaxial analog sun sensor simultaneously. Aiming at measurement errors introduced by assembly deviation, the main error sources are analyzed quantificationally, such as the center offset, rotation and tilt between the aperture and silicon cell, and the incline of the optoelectronic component. Based on the presented analyses, the calibration can be realized with high precision.

Abstract：The multianalog signals acquisition circuit being used in satellite is introduced. Then three key factors in design, including anticurrent collude, amplify consistency and signal sample time are introduced. The conclusion can be used as a reference for the design of multianalog acquisition circuit.

Abstract：DragFree technology is a key technology for future space exploration, which put forward higher requirements for thrusters. The development and application of micro thrusters for dragfree satellites are introduced based on the investigation of dragfree technology space application. According to the development requirement for Chinese dragfree propulsion, the dynamic model of the mass flow control of proportional valve for dragfree cold gas micro thruster is built. A fuzzy adaptive PID controller is then proposed to improve the dynamic characteristics.

Abstract：A new kind of method for constructing the rational function approximations for transcendental functions is provided. Differing from Pad′e method, the new method utilizes the conditions which the values of the transcendental function and its approximation approximate each other, less depending the Taylor expansion of the transcendental function. Taking both of transcendental functions for examples, the differences between the approximations derived with the method and Pad′e approximations are discussed. Using the method, we construct a series of approximations suitable to operate on microcontroller.