| 摘要 |
<p>The method involves automatically controlling a flying vehicle (1) when using a longitudinal pitch rate gyro (2), by an automatic controlling unit (8) to rotate the pitch rate gyro around a longitudinal axis (3) by alternating a rotation direction, for eliminating effects of a scaling factor of the pitch rate gyro. Correction of drifts is obtained by rotation of the flying vehicle. An independent claim is also included for a pitch rate gyro.</p> |
