Patent GB-748455-A (GB)
Title: Gyro controlled servomotor
IPC: G01C19/00
Filed: 1953-04-20
Abstract: 748,455. Controlling aircraft. SUMMERS, T. O. April 20, 1953, No. 10820/53. Class 4. A rate gyroscope device for actuating movement controlling surfaces in aircraft includes a casing mounted for precessional movement and operatively connected with a variableoutput friction clutch releasably connecting a movable power output member with a source of kinetic for obtaining from said clutch an output proportional to the precessional force of said casing, said releasable connection between the power output member and the source of energy including a reversing mechanism and a rotor journalled in said casing, which is mounted on the aircraft for freedom of movement about a predetermined axis of said aircraft perpendicular to said rotor's axis of rotation, whereby said gyroscope is caused to precess about said predetermined axis, when said craft develops rotational movement about an axis perpendicular to said predetermined axis, said controlling surfaces being connected with an actuating mechanism, which includes said movable power output member and is connectible with said source of energy through said variable output friction clutch by precessional movement of said casing. A housing 11, comprising a base member 12 and a detachable cap 13, is formed with trunnions 18 for a gyro casing 16 which carries bearings 28, 36 for the rotor 26, foimed as a shell 31 to enclose a winding 32 which serves as an armature operating within the field of a stationary permanent magnet 33. The casing 31 carries a shaft 27 formed on its outer extremity as a pinion 41 and this is drivingly connected, through reduction gears 42, 47, 48, with a rotatable shaft 49 connected by a universal joint 64 to an aligned shaft 61. A bevel pinion 66, keyed to shaft 61 meshes with opposed bevel gears 102, 103 freely mounted on a shaft 71 so that when the gyro rotor is driven the gears 102, 103 are rotated continuously in opposite directions. The inner faces of the bevel gears 102, 103 respectively carry friction linings 111 and 112 and clutch discs 118, 119 are interposed between these linings and further linings 116 and 117 mounted on opposite faces of a central collar 113 mounted for free axial movement on the shaft 71. The collar 113 is formed with an annular groove 142 to receive anti-friction bearings 141 mounted on the ends of opposed arms 136 mounted on a rockshaft 131, one arm 136 being extended to carry a further bearing 137 which is engaged within an arcuate slot 127 in a plate 126 integral with the rotor casing 16. The shaft 71 carries a pinion 81 meshing with a sector 82 fast with a shaft 83, the outer end of which is secured to an arm 96 coupled by a rod 152 and arm 153 to a rudder 151 of an aircraft. Should the aircraft yaw, resulting precessional movement of the casing 16 and plate 126 would cause pivotal movement of the arms 136 about the rock-shaft 131 and axial movement in one direction of the collar 113 to engage one clutch whereby the shaft 71, and finally the rudder 151, is moved in the appropriate direction to correct the yawing tendency. In order that the rudder may be moved in response to electrical signals from within or outside the aircraft, discs 166, 167 carrying electromagnetic coils 163 are mounted adjacent the gears 102, 103 and when the coils are energized the discs are rotated by the gears which act as armatures. The discs 166, 167 are provided with pins 171, 172 which engage fingers 173, 174 fast with the casing 16 so that the casing is caused to rotate and operate the clutches as described previously.