Ma Guangfu

Robust stability analysis for a cruise missile

Abstract A global controller design methodology for a flight stage of the cruise missile is proposed. This methodology is based on the method of least squares. To prove robust stability in the full airspace with parameter disturbances, the concepts of convex polytopic models and quadratic stability are introduced. The effect of aerodynamic parameters on system performance is analyzed. The designed controller is applied to track the over-loading signal of the cruise segment of the cruise missile, avoiding system disturbance owing to controller switching. Simulation results demonstrate the validity of the proposed method.

The node selection of satellite attitude control system based on sensitivity function in Bayesian network

In order to improve efficiency and save limited storage space for on-orbit fault diagnosis system, the node selection problem of satellite attitude control system based on the sensitivity function in Bayesian Network is investigated. First, the Bayesian Network model of the satellite attitude control system is established based on expert experience and historical fault data, so that to reduce the complexity and uncertainty of the system. Then, through analyzing the importance of each node, a node selection algorithm is proposed through using Bayesian sensitivity function, which can greatly improve the reliability and fault diagnosis performance of the whole system. Finally, numerical computation results show that the proposed algorithm is efficient and has the potential to be used in practice.

A novel central difference Kalman filter with application to spacecraft control

Spacecraft tracking is a very important issue in the domain of spacecraft control. Traditional EKF method can not work well when the system noise is large and initial estimation is less accurate. In order to solve this, a novel central difference Kalman filter based on maximum likehood posterior function is proposed in this paper. The second step of Kalman filter was modified in order to achieve better performance and a typical spacecraft tracking problem is given to show the advances the proposed method.