Patent ID: 6227482
Filing Date: 2001-05-08
Classification: A63H,G01C,G01P,G05D

Abstract:
A gyroscope for a remote-controlled helicopter, wherein a yaw-axis of the remote-controlled helicopter is subjected to PID control, comprising:a yaw-axis control angular velocity detection sensor;a PID controller; anda correct-pitch to yaw-axis mixing unit; andsaid PID controller inputting an error between a yaw-axis angular velocity reference value and a yaw-axis control signal and an error between the yaw-axis angular velocity reference value and an output signal from said yaw-axis angular velocity detection sensor;wherein a counter torque to said yaw-axis due to said correct pitch is prevented by outputting an output signal from said PID controller, an output signal from said correct-pitch to yaw-axis control mixing unit, and said yaw-axis control signal to a yaw-axis driving system.