9786134966863 - Optimized Controller for Attitude and Orbit Determination and Control von Fakhari Mehrjardi, Mohamad; Sanusi, Hilmi; Abdullah, Mardina (5 Ergebnisse)

Paperback. Zustand: Brand New. 108 pages. 8.66x5.91x0.25 inches. In Stock.

Taschenbuch. Zustand: Neu. This item is printed on demand - it takes 3-4 days longer - Neuware -In this textbook, investigation and modeling of enhanced attitude and orbit determination and control systems is conducted which consists of sensors and control actuators in an effort to design an optimized controller. A three-axis star tracker and three reaction wheels are used in order to solve the spacecraft three-axis attitude and control estimation. In the case of sensor malfunction, three-axis attitude estimation is obtained using only two-axis star tracker sensor that utilizes a flexible and mathematically effective Discrete Kalman Filter (DKF). Development of an optimized Proportional-Integral-Derivative (PID) control law is desired mainly due to its simplicity and robustness. Control parameters of the PID controller are selected optimally by comparing the results from Gravitational Search Algorithm (GSA), Backtracking Search Optimization Algorithm (BSA) and Particle Swarm Optimization (PSO) methods to minimize the error. In all optimization methods, the objective function was considered the mean absolute error (MAE) of the controller error. 108 pp. Englisch.

Zustand: New. Dieser Artikel ist ein Print on Demand Artikel und wird nach Ihrer Bestellung fuer Sie gedruckt. Autor/Autorin: Fakhari Mehrjardi MohamadMohamad Fakhari Mehrjardi received the B.S. degree in mechanical engineering from the Yazd University, Iran, in 2006, the M.S. degree in aerospace engineering from the K.N.Toosi University of Technology, Iran.

Taschenbuch. Zustand: Neu. This item is printed on demand - Print on Demand Titel. Neuware -In this textbook, investigation and modeling of enhanced attitude and orbit determination and control systems is conducted which consists of sensors and control actuators in an effort to design an optimized controller. A three-axis star tracker and three reaction wheels are used in order to solve the spacecraft three-axis attitude and control estimation. In the case of sensor malfunction, three-axis attitude estimation is obtained using only two-axis star tracker sensor that utilizes a flexible and mathematically effective Discrete Kalman Filter (DKF). Development of an optimized Proportional-Integral-Derivative (PID) control law is desired mainly due to its simplicity and robustness. Control parameters of the PID controller are selected optimally by comparing the results from Gravitational Search Algorithm (GSA), Backtracking Search Optimization Algorithm (BSA) and Particle Swarm Optimization (PSO) methods to minimize the error. In all optimization methods, the objective function was considered the mean absolute error (MAE) of the controller error.VDM Verlag, Dudweiler Landstraße 99, 66123 Saarbrücken 108 pp. Englisch.

Taschenbuch. Zustand: Neu. nach der Bestellung gedruckt Neuware - Printed after ordering - In this textbook, investigation and modeling of enhanced attitude and orbit determination and control systems is conducted which consists of sensors and control actuators in an effort to design an optimized controller. A three-axis star tracker and three reaction wheels are used in order to solve the spacecraft three-axis attitude and control estimation. In the case of sensor malfunction, three-axis attitude estimation is obtained using only two-axis star tracker sensor that utilizes a flexible and mathematically effective Discrete Kalman Filter (DKF). Development of an optimized Proportional-Integral-Derivative (PID) control law is desired mainly due to its simplicity and robustness. Control parameters of the PID controller are selected optimally by comparing the results from Gravitational Search Algorithm (GSA), Backtracking Search Optimization Algorithm (BSA) and Particle Swarm Optimization (PSO) methods to minimize the error. In all optimization methods, the objective function was considered the mean absolute error (MAE) of the controller error.