Abstract：Spacecraft control technology is one of the key techniques dominating the spacecraft development level. According to special requirements for spacecraft control raised by different space activities, the state of the art of the spacecraft control in highperformance satellites, manned spacecraft, lunar and deep space exploration is analyzed. Academician Yang Jiachi pointed out that spacecraft control was bound to walk towards intelligent autonomous control. It is further proposed in this paper that spacecraft intelligent autonomous control ought to inherit the idea and methodology of “synchronous research of theoretical approach, system architecture and components”. The characteristicmodelbased intelligent adaptive control is presently proposed at Beijing Institute of Control Engineering, being shown to be a promising method from the view point of the current application.

Spacecraft control systems are typical CPSs (cyberphysical systems). The application of CPS techniques will be an important way of improving the correctness and efficiency of the design of spacecraft control systems. Based on the studies on the characteristics of CPSs and the progress of the researches of CPS techniques, and the discussion of the features of spacecraft control systems, the practicability of applying CPS techniques to spacecraft control systems is analyzed, and an idea that introduces CPS techniques into the design, verification and validation processes of spacecraft control systems is proposed, to deal with the problems raised in these processes. At last, several technical challenges are discussed about the application of CPS to spacecraft control systems.

The stability of a gradient algorithm for timevarying parameter identification is studied in this paper. The stability of the timevarying parameter identification gradient algorithm is analyzed by using the stochastic process boundedness criterion. The sufficient conditions to ensure the stability of the gradient algorithm are demonstrated. It is shown that if the rate of variation of the parameter to be identified is bounded, and the measurement noise is zeromean white noise, under the persistent excitation condition, the identification error given by the properly designed gradient algorithm is bounded in the sence of mean square. This analysis is different from prior works in that it is not necessary to assume that the parameter variation is the zeromean white noise in the proof of the theory.

The transfer trajectory of libration point mission varies considerably due to the high sensitivity of error sources and perturbation forces. So, the midcourse correction of transfer trajectory must be considered. For the Halo perigee insertion transfer trajectory, the sensitivity to initial launch errors is firstly analyzed in this paper, and two correction schemes of three impulses and four impulses are put forward. And then the influence of the factors such as initial errors, navigation errors, maneuver performance errors, and earth gravitational perturbation, moon gravitational perturbation, and sunlight pressure perturbation on transfer trajectory correction cost and effect is discussed. The relation between correction times and maneuvers and the relation between errors and maneuvers are achieved by numerical simulation. The Monte Carlo simulation results show the feasibility of proposed two schemes.

The explosion of scale and complexity of SoC is currently becoming a challenge for the SoC verification. The methodology illustrated in this paper is established based on the practice of DW8051 SoC verification and  its suitability and validity has been proved. This methodology includes verification flow, verification level and verification technique.

This paper introduces some international advanced testing technologies of spacecraft control system based on open system architecture (OSA), and analyzes stateoftheart of Chinese spacecraft control system testing technology. The existing problems are also analyzed. An implemental plan of OSAbased testing system for spacecraft control system is presented, and the key technologies are summarized. Moreover, an idea about future work is put forward.  

Software testing occupies a very important position in space embedded software development process, and the alldigital simulation testing platform is considered as an effective method for software testing. This paper studies hiberarchy component decomposition and design for simulation testing platform, and componentbased development method for space software simulation testing platform. Finally, an application example is given to verify these methods.  

An automatic test method is introduced for spacecraft space rendezvous and docking (RVD) GNC software. The introduced approach is realized based on the management of test cases and scripts, automatic execution of the testing process, test data interpretation and test defect management. Practice shows that the automatic test method plays an important role in GNC software development.  

Classification of software defects is the basis of software defect management． The concept of software defects, is presented in this paper,and some kinds of software defect classification methods and their merit and flaw are analyzed in detail. According to analysis of spacecraft embedded software development process and its defective types, a classification method is proposed for spacecraft embedded software defects, particular for defects types and its subclass of “implementation and coding errors”.  

To meet requirement of longevity for manmade satellite, a “H” type hydrodynamic air bearing is used in gyroscopes. The deep going cognition is got in the application process. The fundamental structure and principle of hydrodynamic air bearing are simply presented in this paper. Starting characteristics of “H”type hydrodynamic air bearing are analyzed at different attitudes in detail and ends of the paper gives some results and valuable suggestions.

According to the analytic results of the paper, the operating characters of the forward converter based on LC series resonance magnetic recycle (without magnetic recycle winding) are totally and perfectly showed with both of family of the equivalent curves of the parameters (Vm/E and Toff/LC) in the plane of taking T/LC as horizontal axis and D as vertical axis. The figure has importantly theoretic significance and practical value, because it can make the designer estimate intuitively the operating characters according to the values of the parameters T, L, C and D, and can be used to determine the values of the parameters T, L, C and D based on the operating characters requested beforehand.