| Gas executing agency is an important part of the guided munitions flight control system,which components that emerge control force, change the flight path and the attitude of guidedmunitions. Guided munitions can be obtained by changing the aerodynamic force, it isaerodynamic control; also, it can be guided by load direct control force, it is direct control.Traditional guided missiles generally use hydraulic or pneumatic servo system, these servosystems have excellent dynamic characteristics and structural adaptation, but they have thefailures of complex structure, quality, high price, great technical difficulty.In order to overcome the disadvantages of liquid, pneumatic servo system and simulationof electric steering gear controller, improve the performance of the rocket control system, sothat it can be applied to the design of a model rocket digitize the gas actuator control system.The thesis will design a digitize control system that can accurately, quickly for the real-timecontrol of the munitions gas actuator, and realize to control the trajectory of rocket projectile.The servo system will fundamentally remove the shortcomings of large volume of modernanalog electric servo system, big impacts of system characteristics by the change of circuitparameters, poor reliability, hard to debug and maintain. It can greatly improve the reliability,maintenance and promotion.For this study, the controlled object is a brushless DC motor, based on the transform ofattitude information of the geomagnetic measurement to a given speed command, Aftermicroprocessor substituting into the control algorithm, the pulse-width modulation (PWM)signal derived. After power amplify, it can drive the motor spin follow the command, so as tocontrol the gas executing agency to change the flight attitude of the munitions. The design canimprove the dynamic and steady-state performance of the gas executing agency controlsystem in the munitions, increase the torque response speed of system and control precision. |
PDF Full Text Request