Active Disturbance Rejection Control for Position Servo System of Rocket Launcher

doi:10.3969/j.issn.1000-1093.2014.05.004

Abstract

Abstract: The strong disturbance of combustion gas flow and the large change of system parameters for rocket launcher are analyzed. The system model is based on real servo system with speed closed loop using frequency domain analysis. The approximate low frequency and middle frequency models are established to construct the second-order and third-order linear extended state observers for position servo system. And the active disturbance rejection control methods are designed to estimate the uncertain dynamics compensating the input control. The control effects of proposed control laws and traditional PID are compared both in the servo tracking and the disturbance of combustion gas flow. The simulation results indicate that the proposed methods can effectively improve the output tracking accuracy, and restrain the vibration of launching platform resulted from the disturbance of combustion gas flow to maintain hit precision of projectile.

Key words: ordnance science and technology, rocket launcher, position servo system, linear extended state observer, velocity loop, model approximation

CLC Number:

TJ393

ZHENG Ying， MA Da-wei， YAO Jian-yong， HU Jian. Active Disturbance Rejection Control for Position Servo System of Rocket Launcher[J]. Acta Armamentarii, 2014, 35(5): 597-603.

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