The stabilization of the rockets using a control system including a differentiator gyroscope, an accelerometer and a correction subsystem

摘要

The paper presents an angular stabilization system of the rockets in vertical pane using a differentiator gyroscope, an accelerometer and a correction subsystem. One has determined the transfer functions (in closed loop or in open loop) of the system in the complex variable or in discrete variable. All the eigenvalues of the system are placed in the left complex semi-plane (the proof of system's stability). Using three different methods (least square method, instrumental variables' method and neural networks method), one makes the identification of the system, obtaining (using a Matlab program and a Matlab/Simulink model) the frequency characteristics, responses to step or impulse input in the complex and discrete planes and time variations of the rocket's overload and of the pitch angular velocity. With least square method (LSM) the output of the system and the output of the model were plotted. The identification is made very well - the two signals overlap. With the second identification method (instrumental variables method - MVI), one obtained the frequency characteristics for LSM and MVI on the same graphic. The identification may also be made using neural networks. Using this method, one obtained the indicial responses of the control system and of the neural network before and after the training process.