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Binzhou, China

Li D.,Civil Aviation University of China | Shi Z.,Binzhou Vocation College
2011 2nd International Conference on Artificial Intelligence, Management Science and Electronic Commerce, AIMSEC 2011 - Proceedings | Year: 2011

The modeling and control problem of networked control systems(NCSs) with bounded time-delay and data packet dropout are discussed. Using a full-order observer to compensate networked-induced delay, the system is modeled as an asynchronous dynamical system(ADS) with rate constraints on events by defining an augmented state vector. The criterion for the exponential stability of the networked control systems is presented. Finally, the simulation results are given to show the effectiveness of the presented method. © 2011 IEEE.

Shi Z.,Civil Aviation University of China | Shi Z.,Binzhou Vocation College | Zhang H.,Civil Aviation University of China | Ha D.,Civil Aviation University of China | Gao Q.,Civil Aviation University of China
IET Conference Publications | Year: 2012

According to the problem that the traditional map-building method has high complexity, a map-matching method based on the combination of normal distribution transform (NDT) and environment feature extraction is proposed. The real-time environment information is obtained by two dimension laser sensors, from which the geometric feature is extracted and it will be transformed into normal distribution using NDT method, then the map is matched the by Newton' s algorithm. The method can reduce the complexity of the traditional NDT process, improving the efficiency of the map-matching. The experiment results demonstrate the effectiveness and superiority of the method.

Wang H.,Civil Aviation University of China | Hu Q.,Beihang University | Shi Z.,Civil Aviation University of China | Shi Z.,Binzhou Vocation College | Gao Q.,Civil Aviation University of China
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2015

Backstepping-based finite-time control strategies are investigated for spacecraft attitude tracking subject to external disturbances, control saturation and actuator faults. A finite-time fault-tolerant attitude tracking controller is developed by introducing a novel integral-type sliding mode with finite-time convergence, and it is further shown that the controller is independent from a prior knowledge of spacecraft inertia or bound of external disturbances with parameter adaptations. It is important to note that the designed fault-tolerant controller does not require any fault information detection, isolation online even controller reconstruction, and saturation magnitude of actuator output is explicitly taken into account. The stability analysis shows that the finite-time convergence of spacecraft attitude tracking can be ensured by the designed controller with superior fault tolerant capability for actuator faults, even with respect to the multi-constraints such as control saturation and even faults. The control performance of the proposed controller is further evaluated through the numerical simulation analysis, with the robustness to external disturbances and system uncertainties. ©, 2015, AAAS Press of Chinese Society of Aeronautics and Astronautics. All right reserved.

Sri Z.,Civil Aviation University of China | Sri Z.,Binzhou Vocation College | Jiang B.-Y.,Civil Aviation University of China | Hu Q.-L.,Harbin Institute of Technology
2013 25th Chinese Control and Decision Conference, CCDC 2013 | Year: 2013

In this paper, an adaptive control approach combined with time-varying sliding mode technique is developed for attitude maneuver of a rigid spacecraft, in which multi constraints are simultaneous considered, such as thruster uncertainties including thrust misalignment and magnitude error, external disturbances, uncertainty of the inertia of the spacecraft, and even the control saturation. By explicitly considering the saturation magnitude of the available control input to the thruster, the maximum value of thrust is used in the designed control law. Finally Lyapunov stability analysis shows that the closed-loop system is stable and numerical examples illustrate that the effectiveness and robustness of using the proposed controller. © 2013 IEEE.

Li B.,Civil Aviation University of China | Li B.,Harbin Institute of Technology | Hu Q.-L.,Harbin Institute of Technology | Shi Z.,Civil Aviation University of China | And 2 more authors.
Yuhang Xuebao/Journal of Astronautics | Year: 2013

A backstepping design based adaptive control algorithm is developed for attitude stabilization of a rigid spacecraft, in which the uncertainties of actuators misalignment and external disturbances are considered. Lyapunov stability analysis shows that the attitude and angular velocity converge to zero, and an novel updating law is employed to implement attitude control law as well, in which the possible singularity problem caused by the estimation of uncertainties due to actuator misalignment is avoided effectively. In addition, a dynamic control allocation is investigated to distribute the desired control command among redundant actuators. This method extends the conventional quadratic-programming control allocation by penalizing the previous step before sampling intervals and minimize the energy consume. Finally, a numerical simulation example for a spacecraft attitude control system is included to illustrate effectiveness and feasibility of the proposed control scheme.

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