Patent GB-427422-A (GB)
Title: Improvements in or relating to gyroscopic apparatus for example for air and other craft
IPC: G05D1/02
Filed: 1933-10-24
Abstract: 427,422. Controlling aircraft. BROWN, J. P., Waldronhyrst Hotel, South Croydon. Oct. 24, 1933, Nos. 29473 and 30904. [Class 4] [See also Group XX] In gyroscopic apparatus having the rotor mounted on and frictionally driven by a rotating spindle by means of a ball joint between the surfaces of which slip is caused to occur, servo means actuated by movement of the rotor axis relative to the spindle axis cause the latter to follow up the rotor axis. In the form shown, the driving spindle follows up the rotor about vertical and horizontal axes and the fluid pressure servomotors for effecting the follow up are adapted to control automatically the rudder and elevators of an aircraft. The gyro casing C is carried by horizontal bearings B<1> in a cradle B carried so as to be rotatable about a vertical axis by pillar A<2> which is fixed to a base plate A. The driving spindle (not shown), is mounted in the casing C and has a spherical end of which the centre of curvature lies at the inter - section of the axis of the spindle and the two axes of rotation of the casing C. The rotor D, which may be built up from a heavy rim, a hub, and a flat annulus, is mounted on and driven by the spherical end as described in Specification 341,519 or 410,839, [both in Group XX]. A pin E extending along the axis of the rotor and carrying an axially adjustable balancing weight E<1> is adapted to extend between the arms of a horizontally extending fork J and a vertically extending fork H. The fork J is mounted to swivel about an axis parallel to its length in one arm J<4>, Fig. 7, of a parallelogram linkage counterweighted at J<8> and pivoted to a valve casing S fixed to the gyro casing C. Upon relative movement of the rotor D and casing C about a horizontal axis, the pin E acting through the fork J rocks the parallelogram linkage whereupon the arm J<3> causes movement of the piston valves S<1>, S<2> in their cylinders so that the pipe M supplying oil under pressure and the return pipe N are appropriately connected to the pipes L<3>, L<4>, The latter communicate with spaces on opposite sides of the piston of a servomotor L which through link L<2> is caused to rock the double lever Q, Q<8> about its pivot Q<1>. The shorter arm Q<8> is adapted through Bowden wire C<3> to cause the casing C to rotate in bearings B<1> and follow up the movement of the rotor. The pivot Ql carries an arm Q<5> adapted through link Q<6> to control automatically the joy stick Q<7> and an arm Q<3> adapted to be connected to a fan-shaped extension of the lever Q by a pin controlled by Bowden wire Q<4> when it is desired that the lever Q should automatically control the joy stick. The amount of control applied for a given deviation of the rotor axis may be varied by adjusting the connection between wire C<3> and arm Q<8> towards or away from the pivot Q<1> by means of slot Q<2>. The fork H, upon relative movement of the rotor axis and driving spindle about a vertical axis, moves the valves F<6>, F<2> controlling the servomotor K which is adapted through link K<2> to rock the lever P pivoted at P<1>. A yoke P' for engaging the rudder bar P<6> and an arm P<3> are fixed to the pivot P<1>. A pin controlled by Bowden wire P<4> enables the arm P<3> to be coupled to a fan-shaped extension of the lever P when desired. The follow up is effected by an adjustable pin and slot connection P<2> between an arm B<2> fixed to the cradle B and a lateral arm of the lever P. When it is desired to alter the course, valves K<6>, L<6> are opened by Bowden wires K', L<7>, so that the two ends of each cylinder K, L are put in communication through pipes K<5>, L<5> and the rotor is brought into and kept in line with its spindle by a locking device controlled by Bowden wire C<5>. The Bowden wires C<5>, K<7>, L<7> may be connected to a single operating lever. For effecting slight corrections of the course the valve casings S, F may be adjustable relatively to the supporting cradle B. Alternatively the rotor may be caused to precess about a vertical axis by pressing upwardly or downwardly on the pin J<7> which is an extension of one of the arms of the parallelogram linkage to which the fork J is connected. The pressure may be applied by a lever which bears on the pin J' under the action of gravity on a weight on one end, the direction of the pressure being reversed by turning the lever through 180 and the amount of the pressure and therefore the rate of precession of the rotor being varied by adjusting the position of the lever pivot by means of a Bowden wire. The course correcting means may be operated by a compass, electric, electro-magnetic or radio-electric means or by a manometric pressure device. To eliminate friction the valves F<1>, F<2>, S<1>, S<2> may be continuously rotated through gear teeth S<3>, S<4>, Fig. 7, engaging a driving pinion S<5>. Alternatively the pin E may be slightly eccentric so as to keep the servo valves continuously shivering. The apparatus may be arranged to control elevators and ailerons or rudder and ailerons. In a modification the control is about one axis only e.g. the rudder. In this case the rotor is precessed so that it follows the driving spindle if the latter tilts about a horizontal axis, the horizontal fork J being adapted to operate a piston valve controlling a servomotor arranged to press resiliently on the parallelogram linkage supporting the fork H and the valves S<1>, S<2>, motor L, lever Q, and bearings B<1> being eliminated. The apparatus may be used for maintaining constant the orientation of guns searchlights, bombing sights, or directional wireless aerials or for controlling gun fire or as an indicating instrument.