| 摘要 |
1,172,441. Aircraft instruments. ELECTRONIC COMMUNICATIONS Inc. 11 April, 1967 [11 April, 1966], No. 16451/67. Heading B7W. [Also in Division G1] A roll stabilized gimbal 10, forming the mounting for a gyroscope in an aircraft &c. instrument, is supported in a frame 14 by a shaft 19, the gyroscope consisting of inertial masses 12, 13 and a motor 11 the speed of rotation of which is varied by a system 68-70, 75 in accordance with the speed of the aircraft. A toothed ferromagnetic wheel 73 rotates with the gyroscope and causes fluctuations in the reluctance of the air gap between it and a magnetic member 72 fixed to the gimbal 10, these fluctuations being detected by a coil 74 connected to the gyroscope speed sensor 75. The shaft 19 is mounted on the roll axis 17 and sudden roll displacements are resisted by a dashpot and lever arrangement 21-24. A yoke 26 is secured to one end of the shaft 19 and supports a horizon ball 31 on an axis 28. A pendulum 32, pivoted about an axis 33 and having a weight 34, correctly positions the ball in accordance with pitch of the aircraft by engagement of a pin 36 in a slot 37 of the ball. The device is used in conjunction with an indicator panel including a horizon window 43 and a horizon reference marker 45 carried by a vertical rod 46. A knob 49 enables vertical adjustment of the marker 45 and a further pendulum 53 indicates the direction of the resultant of the gravitational and centrifugal forces acting on the aircraft. The pendulum 53, which is pivoted at 55, is ring shaped and carries an indication 54 observable in a window 57. A third window 58 permits viewing of a pointer 38 attached to the yoke 26. During a turning manoeuvre of the aircraft, the gyroscope will tend to precess about the roll axis in the opposite sense to the roll. This tendency is counteracted by the restoring torque supplied by springs 65, 66. In a modification, the device is adapted to give an indication of the rate of change of altitude, i.e. of ascent or descent. |
