Control and neutralization of acoustic and unwanted vibrations on ADCS subsystem

Mechanical vibrations and acoustic waves are always one of the main causes of malfunction in controllers that use gyroscope data. This data is of particular importance for the control of any aircraft. Accordingly, it is necessary to check the accuracy of gyroscope data. Control errors that usually occur due to vibration sometimes cause irreparable damage. One of the prevalent methods is to detect incorrect data and remove it by statistical methods. But the data removal method is practically inefficient when the data is affected by a continuous vibration element. This paper tries to provide a suitable way to control and handle data that has been affected by vibration. To test the performance of this control method, We implemented it on a UAV simulator. In this simulator, we used the MPU6050 chip to calculate the gyroscope data. In tests, the chip was exposed to vibrations generated by the motor, mechanical vibrations from special vibration motors, And acoustic vibrations up to 90 dB with high and low frequency. This chip is resistant to acoustic vibrations up to 100 dB. The new method uses the integration of chip output data with the time factor and the use of recursive functions, the output of which is acceptable and promising for the control of aircraft and spacecraft. Another utilization of this method is to control self-driving cars.

Keywords:

Nonlinear Vibration , Vibration control , Spacecraft , Structural Dynamics