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To investigate the dynamics and the potential of the control mechanism of a fixed-trim re-entry vehicle with a moving-mass roll control system and provide the theoretical references for engineering practices, the 7 -DOF dynamic model is generated in this paper. Then, the kinetic characteristics and the dynamic coupling between the moving mass and the carrier are studied with the frequency domain analysis to reveal the control m echanism of the flight vehicle control system. M eanw hile, according to the analysis results of the coupling between three channels and the im pact of the actuator param eters on the control au thority, some suggestions on the structure and control system design have been made in this p ap er, which provide the theoretical references for a flight vehicle with a moving-mass roll control system in engineering practices. [ABSTRACT FROM AUTHOR]

In order to deal with the complicated problem of orbit and attitude control of a flexible spacecraft，a study of dynamic modeling and control of flexible spacecraft is conducted. A new dynamic model which can describe the orbit and attitude dynamics of flexible spacecraft at the same time is proposed, using the method of dual quaternions. The new dynamic model is able to describe the orbit and attitude of the spacecraft integrally, and to consider the coupling effect between the vibration of the flexible parts of the spacecraft and its translation and rotation automatically. An adaptive position and attitude-tracking controller which requires no information of the spacecraft's inertial parameters is designed based on the model. The coupling effect of the flexible parts can be estimated using the adaptive controller, and thus the stability of the whole system during orbit and attitude maneuver process is improved. The simulation result demonstrates that the adaptive controller fits the problem of orbit and attitude control for flexible spacecraft well and thus is applicable. [ABSTRACT FROM AUTHOR]

An intercept guidance law based on motion camouflage strategy is proposed in this paper. According to the relative position between a missile and a target, the dual second order dynamics model is derived, and the missile interception conditions are given based on this model and the characteristics of the motion camouflage strategy. Then, the three-dimensional guidance law is derived by using the interception conditions and the motion relation of the missile and the target. In the process of derivation，the three-dimensional guidance law can be designed in a two-dimensional plane and the difficulty of guidance law design is reduced. A two-dimensional guidance law for three-dimensional space is derived by introducing the estimation for target maneuver. Finally, the interception simulation for the proposed guidance law is taken and compared with pure proportional guidance. The simulation results demonstrate the accuracy and the effectiveness of the proposed guidance law. [ABSTRACT FROM AUTHOR]