GB610856A - Improvements in and relating to the recovery of zinc from zinciferous material containing iron and apparatus suitable therefor - Google Patents

Abstract

610,856. Electric indicating systems. BRITISH THOMSON-HOUSTON CO., Ltd. March 29, 1946, No. 9738. Convention date, April 3, 1945. [Class 40 (i)] In an aircraft attitude indicator, roll and pitch are detected by a stabilised device, such as a gyroscope, and rolling movements are transmitted to an indicator by an electric remote control device. Pitching movements may be indicated by a mechanical connection. The arrangement enables the indicator to show a representation of the aircraft in flight as viewed from a fixed point, thereby assisting the pilot's natural reactions in correcting. The gyroscoperotor spins on a vertical axis A, A in a casing 11 and is mounted on a transverse axis on pivots 12, 12 in a gimbal ring 13 supported on longitudinal pivots 14, 14. One pivot 12 is extended to carry an arm 18 so as to raise or lower the indicator 5 relative to a window 7, carrying a fixed horizon line 6, to follow pitching movements. One pivot 14 carries a permanent magnet 29 so as to rotate it within a wound annular stator 22 in response to rolling movements. This stator is electrically connected to a wound stator 30 to influence a permanent magnet 35 on a spindle 16 in known manner. This spindle carries the indicator disc 5 to rotate it to show any banking motion. The electrical connections of the system, (see Fig. 5, not shown) are such that the two stator windings are fed in parallel from a common A.C. supply and are also interconnected by three common leads joined to three equally-spaced points on each.