| 摘要 |
1,076,116. Automatic control of aircraft. BODENSEEWERK PERKIN-ELMER & CO. G. m. b. H. Oct. 23, 1964 [Oct. 26, 1963], No.43360/64. Heading G3R. In an aircraft automatic pilot, an integrating, restrained gyro controlling roll stabilization is torqued about its precession axis by differentiated signals from a turn controller and by signals from an apparent vertical detector. As shown, gyros 1, 1' respectively responsive to roll and yaw of an aircraft are restrained about their precession axes by pneumatic cylinders 2, 2' having throttled outlets so that bridge-connected pick-offs 3, 3' produce electrical outputs, each dependent on both deflection and integral of deflection about the roll and yaw axes, to respectively control servoactuated ailerons and rudder (not shown) and thus maintain the aircraft in a desired altitude. A similar gyro may also stabilize the aircraft about its pitch axis. Turns may be produced by a manual controller 7, signals from the electrical pick-off 6 of which are applied through an amplifier 5' to torque the yaw gyro. A pendulum QU develops an electrical signal, corresponding to the error between the true and apparent vertical during turn, which is applied through an amplifier 5 to torque the roll gyro so that the aircraft is banked to produce a properly co-ordinated turn. To reduce the initial signal from the pendulum, the signal from manual controller 7 is differentiated by a transformer 10 and applied through amplifier 5 to torque the yaw gyro. The signal thus applied is limited by saturation of transformer 10 and is varied in dependence on aircraft velocity by causing the latter to vary a potentiometer 9. In the case of radar or localizer radio control the appropriate receiver output may be substituted for that of pickoff 6. |
