Design and Implementation of a Rocket Launcher with Improved High Speed & Accuracy

De Ying Li

doi:10.4028/www.scientific.net/AMR.466-467.1334

Paper Titles

Flaw Detection by Using Hardware-in-Loop Based on Proteus
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Intelligent Car Direction Control Based on Fuzzy PID
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Design of Semi-Physical Simulation System of UAV Based on Computer Control
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Iterated Cubature Kalman Filter for State Estimation of Maneuver Reentry Vehicle
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Design and Implementation of a Rocket Launcher with Improved High Speed & Accuracy
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Modeling and Simulation of Brushless DC Motor Adaptive Fuzzy PID Control System for Pure Electric Vehicle
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Modeling and Simulation of Permanent Magnet Synchronous Motor for Pure Electric Vehicle Based on Space Vector Pulse Width Modulation
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Study of Precise Measurement Algorithm Based on Machine Vision
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Research on ANN Dynamic Inversion Control of UAV
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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 466-467Design and Implementation of a Rocket Launcher...

Design and Implementation of a Rocket Launcher with Improved High Speed & Accuracy

Abstract:

Aiming at high speed and accuracy position control, this paper introduces design of an optimal internal mode control and sliding mode control for rocket launcher servo systems which have large varied moment of inertia, strong impact moment and load moment. Internal mode control designed by LQR theory can satisfy system requirement of the position loop in PMSM system. Sliding mode control can restrain effects that caused by model parameter perturbation and external disturbance and realize high performance position control. Simulation results show that the control method is simple and has better performances compared with PID controller.

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Periodical:

Advanced Materials Research (Volumes 466-467)

Pages:

1334-1338

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.466-467.1334

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Online since:

February 2012

Authors:

De Ying Li

Keywords:

Internal Mode Control (IMC), Optimal Control, Rocket Launcher, Servo-System, Sliding Mode Control (SMC)

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