| 摘要 |
A combination directional gyro and navigation radio indicator instrument for use in aircraft which provides a display of compass card, selected course pointer, course deviation indicator, to-from indicator, and glide slope indicator in a unique presentation. The compass card is directly driven by the directional gyro, and the selected course pointer normally rotates with the compass card when it rotates, but can be de-clutched for selection of a new course. The selected course signal is obtained by attenuating, amplifying, and phase shifting the reference signal from a navigation radio such that it can be sent to the rotor of a control transformer which is geared to the compass card. The resulting stator signal is then amplified and sent to the rotor of a differential resolver which is geared to the course selector pointer. The control transformer and the differential transformer rotors turn in opposite directions such that the reference signal does not change when the compass card and the course selector pointer move together, but does change when the course selector is de-clutched and moves independently of the compass card. The resulting signal from the stator of the differential transformer is therefore an electrical representation of the selected course. This signal is then sent back to the navigation radio where it is compared to the signal representing the actual course of the aircraft that is received from a stationary navigation radio transmitter (VORTAC).
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