Composite control of simultaneous maneuvers of a spacecraft platform and its appendages is potential research direction. Requirements and research contents are analyzed in this paper. Then, complete dynamics equation of a two-rigid-body system as a simplest object of the composite control is derived. Many topics are discussed, such as complexity of the problem, description of attitudes of the spacecraft platform, model simplifying for its composite controller and coupling characteristics of the system. The composite controller are designed for the system and numerical simulation done. Some principle advises about modeling, feedforward and bandwidth band choice strategies are given.

In this paper, we have proposed an adaptive control scheme for the capture of a tumbling spacecraft using free-floating space manipulators. Capturing tumbling target spacecraft requires the free-floating space manipulator to have high tracking performance. However, uncertainties always exist in both the free-floating space manipulator and the target spacecraft. In the presence of parameter uncertainties, model based controllers tend to give deteriorated performance or even become unstable. Thus, we employ parameter adaptations to improve the performance of model based controllers, and we have also proposed a novel joint-space adaptive controller for free-floating space manipulators. Simulation results are presented to show the performance of the proposed adaptive control scheme.

A fuzzy discrete adaptive control method via back-stepping design is proposed for the hypersonic aircraft by using its Euler approximation discrete model. By combining the fuzzy adaptive control and feedback linearization, the mismatched uncertainties can be well compensated by designing a corresponding virtual/actual control input in each back-stepping design procedure. Stability analysis shows that the proposed scheme can guarantee the uniform ultimate boundness of the system tracking errors and fuzzy weight estimation errors. The longitudinal model of a hypersonic aircraft is used to demonstrate the effectiveness of the proposed strategy.

This paper proposes an accurate orbit determination technique to accurately determine orbit elements of a spacecraft equipped with a GPS receiver according to navigation messages from the receiver. Accurate coordinate system and time system transformations necessary to guarantee the orbit determination accuracy of the order of 10m are presented. A combined navigation method using navigation messages from receiver and the recursive formula of the perturbation motion equation is adopted, and the navigation can still operate normally even if antennas of the receiver is obscured in a short duration.

A generalized total least squares method is adopted to in-orbit identification of the inertial matrix of a zero momentum satellite. A prior minimum distance solution is defined: this solution closest to the prior estimate in solution space as if measurement information is not enough to determine a unique solution. An algorithm of the prior minimum distance solution is proposed, and applied to in-orbit identification of an inertial matrix. Simulation results validate feasibility of the identification method and advantage of the prior minimum distance solution over the minimum norm solution.

When the moon and the sun light enters into the field of view of the conical scanning earth sensor (CES)，the real attitude of the spacecraft will be affected because of wrong CES measurements．To solve this problem，a new method based on the CES software can discriminate the interference effect．A series of ground are designed to verify this method effectiveness，and results indicate that this method can not only give a indication of the moon，but also can eliminate effect of the moon and the sun light on the CES’s measurements．Finally，the on-orbit flight data is presented to confirm this method validity．

Based on conquering the shortcomings of conventional qualitative or quantitative fault diagnosis methods for the satellites control system and seeking the new mechanism of combining the qualitative and quantitative method，a new mixed modeling method with the qualitative simulation (QSIM) and the parity space method is proposed. The method achieves the organic combination of the qualitative and quantitative information based on the fuzzy logic. The qualitative/quantitative hybrid model can integrate the system information comprehensively ，and then realize the efficient, accurate and rapid fault diagnosis for the satellite control system. Simulation experiments show that the method is efficient and feasible.

A new feature point extraction algorithm based on prior knowledge of navigation systems for lunar rover is presented in this paper .The key-points was extracted by SIFT(Scale Invariant Feature Transform) from image as feature points at first. Then use these feature points for binocular matching thus getting distance information of the scene by the calculation of differences between match points in two images. This algorithm could improve the robust to lightness change for images of lunar region and accuracy in the later matching phase. This algorithm make good results in simulative environment experiments.

Based on error analysis of the C-W guidance, the article shows that the main perturbation sources of C-W impulse guidance are linearization error, relative J2 term perturbation, and impulse assumption error of thrusters . When obtaining the analytic solution of perturbed relative motion equation, an aiming point modification technique is induced to improve guidance accuracy at limited increase of computational effort, and the actual rendezvous trajectory and the fuel consumption are close to optimal ones.

To solve the problem of low reusability in a satellite ground application system, this paper gives a design scheme extensible universal framework for equipment monitoring software. Combining modularized software with abstract modeling technique, the design method has advantages of simply development and higher reusability. A inversion of control technique is used to give the benefit of loose coupling and higher extensibility in application.

Two Star-tracker-based attitude determination algorithms, the Least-Square algorithm (LS) and the quaternion estimator (QUEST) algorithm, are presented. This paper contains an accuracy comparison of the two algorithms under different number of the observation vectors and any bore sight direction of the star tracker in the global area. The results show that the QUEST algorithm is more accurate than the LS one, even under the adverse constellation configuration.