Patent GB-468487-A (GB)
Title: Improvements in and relating to aileron control systems for aircraft
IPC: B64C1/00
Filed: 1936-09-14
Abstract: 468,487. Automatic control systems. SIEMENS APPARATE UND MASCHINEN GES. Sept. 14, 1936, Nos. 25073 and 25074. Convention dates, Sept. 13, 1935 and Aug. 26, 1936. [Class 38 (iv)] Body in motion.-Means for controlling aircraft comprise an aileron control-system, the measurement or control value for which produced at any time by a gyroscopic artificial-horizon responsive to inclinations of the aircraft about its longitudinal axis but inherently non-responsive to lateral movements of the aircraft is supplemented by a measurement or control value produced at the same time by a turn indicator. In one form, relative movement between the aircraft and a gyroscopic artificial-horizon indicator 6 actuates through a link 9 and a lever 10 a contact 12 to close a circuit through one or other of contacts 14, 15 to set in motion an electric motor 19 which through a worm 24 and wormsector 25 operates the ailerons 4, 5. The contacts 14, 15 are separated by an insulator 16 and are connected to one end of a lever 36 which is centralized by springs 33, 34. The lever 36 and the arm 26 carrying the sector 25 are connected by a dashpot 32. The contact 12 is carried on a sliding bar 11 connected to the lever 10. The fulcrum 37 of the lever 10 is adjusted, to supplement control by the indicator 6, through an arm 40 and a link 41 from a gyroscopic banking-indicator 38. The control by the indicators 6, 38 is further supplemented by an air-speed indicator comprising a wind vane 48. The vane 48 actuates a contact 51 against the action of a spring 49. The contact 51 moves over a rheostat 47 to vary the current passing through an electromagnet 45 which through an armature 44 carried by a lever 43 adjusts the tension of a spring 42 acting on the arm 40. In a modification, a capsule 59 responsive to air-speed controls, against the action of a spring 55, through a lever 57 and a cord 56 the position of a link 53, replacing the link 41, in an arcuate slot 52 which replaces the lever 40. The slot 52 is centralized by springs 63, 64. In a further modification, a gyroscopic turn indicator 65 is provided with a contact lever 65 which moves over a coil-winding 67 forming one phase of a three-phase system, the other phases of which are S and T. A contact arm 69 is actuated by an air-speed indicator 68. The potentials of the phases 67 and T are supplied to a two-phase rotating field motor 70, the constants of which are selected such that a torque is produced which is proportional to the product of the speed of flight and the speed of rotation of the aircraft about a vertical axis. The motor 70 is anchored by springs and actuates a bolometer amplifier acting as the basis of the artificial-horizon. The bolometer current is controlled by means of a shutter 73 operated by a gyroscope 74. The bolometer operates a rotary magnet 75 in which the armature is provided with two windings capable of exciting it in opposite directions. The armature of the magnet is connected to a spring lever 78 pivotally connected to the piston rod of a servomotor 77 and to a control valve 76.