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A method based on particle swarm optimizer is presented for the optimization the pre-impact configuration of a dual-arm space robot to minimize the changes of robot's attitude. The dynamic equations of pre- and post-impact phases are firstly given, then the impact dynamic model is derived based on impulse-momentum equation, the objective function is the change of robot's angular momentum caused by impacts. By use of the particle swarm optimizer, the pre-impact configure is calculated to minimize the effects of impacts on the robot's angular momentum. An ideal pre-impact configuration is found. Numerical results show that the proposed method is useful and effective. [ABSTRACT FROM AUTHOR]

In order to reduce the complexity of the multistage system and improve the system immediacy, a new cascaded approach is proposed. Taking a three-coefficient finite impulse response (FIR) model for the continuous wave interference (CWI), a nonlinear Kalman-type adaptive filter is formulated to suppress narrow band interferences. Subsequently, pre-processing results are transmitted to a space-time adaptive processor to suppress wide band interferences. Simulation results show that the new approach outperforms ordinary space-time adaptive processor and space-frequency adaptive processor under the condition of matched-spectrum interferences, especially when the narrow band interferences NBIs are incomming from the direction of the satellite. [ABSTRACT FROM AUTHOR]

Focusing on increasing space manipulating demands and orbital life extension application background for a spacecraft in HEO, the flight process is analysed firstly, and followed by the process of relative attitude and orbit coupled dynamics modeling in super-close distance. In addition, the attitude-orbit coupling control law design is derived in details. Meanwhile, concerning the HEO spacecraft featuring apogee engine fixed in its sky-facing surface, the image-based non-cooperative target feature recognition, extraction and relative measurement algorithm are researched. Finally, by means of distributed simulation system construction and small capturing-docking facility, ground simulation test for super-close relative navigation and relative motion control is executed in order to validate the feasibility of this orbital life extension scheme achieved via capturing the apogee engine nozzle of HEO spacecraft. [ABSTRACT FROM AUTHOR]