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1. 发明专利

GB551439A Device for indicating or controlling the turning of a craft 未知
公开(公告)号：GB551439A
公开(公告)日：1943-02-23
申请号：GB607741
申请日：1941-05-10
申请人： ROBERT HAYES NISBET , WILLIAM GEORGE HARDING , SPERRY GYROSCOPE CO LTD
IPC分类号： G01C19/42
摘要： 551,439. Fluid-pressure servomotor-control systems. NISBET, R. H., HARDING, W. G., and SPERRY GYROSCOPE CO., Ltd. May 10, 1941, No. 6077. [Class 135] [Also in Group XX] A device for indicating or controlling the turning of a craft about an axis comprises an inertia member yieldingly constrained towards a fixed position relative to the craft, the resonant period of the member and its constraint being longer than the period of naturally occurring oscillations of the craft, fluid means fcr damping oscillations of the inertia member and means responsive to the pressure difference developed in the damping means. In the form described, the inertia member consists of a closed cylinder 33 mounted in a liquid-filled casing 39, the reduced ends of its shaft being mounted in ball bearings 34, the outer races of which are mounted in resilient material, adapted to yield in the event of chocks, to allow unreduced portions of the shaft to contact with auxiliary plain bearings. Tension springs 76, 77 act on the cylinder, which is connected by metal tapes secured thereto at 65, 67, 71, 75 to the rods 62, 63 of pistons 58 ... 61 working in cylinders provided in the casing. Diagonally opposite cylinders are connected by pipes 42, 43, and 31, 32 to capsules 27, 28. Leakage past the pistons is permitted, and a bypass with an adjustable constriction 85 is provided between the pipes 31, 32. Turning of the craft sets up a differential pressure in the pipes 31, 32 which moves a member such as 29, which may operate an indicator, or act on a relay valve 10 forming part of a control system as described in Specifications 515,290 and 531,388.

2. 发明专利

GB546664A Method of and apparatus for controlling searchlights 未知
公开(公告)号：GB546664A
公开(公告)日：1942-07-24
申请号：GB1512940
申请日：1940-10-10
申请人： SPERRY GYROSCOPE CO LTD , ROBERT HAYES NISBET , DAVID GLYNDWR WALTERS
IPC分类号： F21V21/30
摘要： 546,664. Searchlight control systems. SPERRY GYROSCOPE CO., Ltd., NISBET, R. H., and WALTERS, D. G. Oct. 10, 1940, No. 15129. [Class 40 (i)] In a system comprising a number of searchlights individually mounted for rotation in azimuth and elevation under separate control in response to data transmitted from a common control station, the control is effected so that the individual beams move in unison but with relative angular displacement whereby they are caused to move as a composite beam. Basic angular settings are determined at the control station, the relative angular displacements being included in the transmitted data or effected at the individual searchlights. The beams may be fanned in azimuth or elevation or the composite beam may be conical. Arrangements are provided for scanning, for changing the form of the composite beam, and for compensating reduction of azimuthal spread with increase of elevation. In the system shown in Fig. 1, to which the invention is applied as shown in Figs. 2 and 3 and which comprises only azimuth control, the similar elevation control being omitted, the sound detector 1 and one searchlight 3 are interconnected by a selsyn system 7, 9, 10 supplied from mains 8. When the rotors are not in correspondence, the rotor of 10 provides an output to a phase detector 11 which may be as described in Specification 523,539 and which provides an indication at 12 of the direction of searchlight movement required to restore correspondence. This movement is controlled by handle 4 and selsyn systems 5, 6 operating on all the searchlights 3, 3 1 , 3 11 . Movement of the transmitting rotors is reproduced by the receiving rotors which by means of cams 15 and reversing switches 16 control the motors 17 to rotate the searchlights and the "stators" until the rotors open the driving circuits. Introducing relative angular displacements; scanning. Fig 2 shows an arrangement for control of searchlight beams having the same elevation but with beams fanned in azimuth, and for scanning, by synchronously varying the elevation. The azimuthal transmitters 5 have their rotors controlled by handle 4 whereas their "stators" are also given angular displacements by connections to a lever 25 pivoted at a point 25 1 corresponding to the central transmitter 5 and controlled by a zero sliding and rotating cam 28 operated as to its sliding movement by handle 46 to adjust the spread, which may be reduced to zero. By this means, displacements are given to the stators which increase in opposite directions from the central stator to the outer stators. The rotors 29 of the elevation transmitters are controlled by handle 30 which is also geared to the cam 28 to vary the position of lever 25 in accordance with elevation. A common elevation transmitter may be used. The seachlights are given superimposed elevational scanning movement by motor 36, driving a crankshaft 32 which oscillates the "stators" 29 by means of levers 33, links 39 and toothed gearing 37. The motor 36 is started bv switch 36 1 and its speed controlled by variable resistance 40. In order to prevent the indicator 12 from responding to scanning movements, compensation is effected by potentiometer 42 the arm of which is oscillated in synchronism with the stators. The scanning angle is adjusted by slotted connections between links 39 and levers 33. A similar arrangement may be used for beams having the same azimuthal angle but fanned in elevation and with azimuthal scanning which may be applied to the rotor of the azimuth transmitter by a differential gear, but a modified arrangement for this purpose is shown in Fig. 3. The common azimuth transmitter 5 has its rotor adjusted by handwheel 4 and its "stator" oscillated by motor 47 for scanning purposes. The motor also drives disc 50 carrying a pin 51 which oscillates a lever 52 whereby a toggle or like reversing switch 5 is controlled to reverse the drive at intervals depending on the position of the switch lever relatively to a cam slot 63 in lever 52. The switch 57 is moved horizontally to screw 60 rotated by gearing 61, 62 from the elevation control handle so that the angle of scan increases with elevation. Manual adjustment of the setting is effected by screw 64. In a further modification, Fig. 4 (not shown) spread is effected at the receivers by superimposing on the angles transmitted, variable and adjustable angles determined by spring controlled levers and combined with the transmitted angles by differential gearing. The levers may be brought into operation by control from the common station and may also be subject to control by the receivers to compensate variation of azimuthal spread with varying elevation. The levers may also be subject to control from the central station to change the form of the beam.

3. 发明专利

GB506379A Improvements relating to automatic steering systems for aircraft 未知
公开(公告)号：GB506379A
公开(公告)日：1939-05-23
申请号：GB605139
申请日：1937-08-23
申请人： SPERRY GYROSCOPE CO LTD , ROBERT HAYES NISBET , WILLIAM GEORGE HARDING
IPC分类号： G05D1/02
摘要： 506,379. Fluid-pressure servomotorcontrol systems. SPERRY GYROSCOPE CO., Ltd., NISBET, R. H., and HARDING. W. G. Aug. 23, 1937, No. 6051/39. Divided out of 503,317, [Group XXXV]. Drawings to Specification. [Class 135] [Also in Group XXXV] The subject-matter of thO' present Specification is described in Specification 503,317 but the claims differ. Specification 377,262, [Group XX], also is referred to.

4. 发明专利

GB504726A Improvements relating to gyroscopic apparatus, particularly to precision directionalgyroscopes 未知
公开(公告)号：GB504726A
公开(公告)日：1939-04-27
申请号：GB2940637
申请日：1937-10-27
申请人： SPERRY GYROSCOPE CO LTD , WILLIAM GEORGE HARDING , ROBERT HAYES NISBET
IPC分类号： G01C19/34
摘要： 504,726. Knife-edge bearings. SPERRY GYROSCOPE CO., Ltd. HARDING, W. G., and NISBET, R. H. Oct 27, 1937, No. 29406 [Class 12 (i)] [Also in Group XX] A pendulum 73 con trolling the applicatior of correcting torques to a gyroscope is suspended by a knife edge 69 held between two large balls 63, 64, and resting on four smaller balls 66-68. The balls 63- 68 are carried in a diametrical groove in a ring 61.

5. 发明专利

GB500652A Improvements relating to follow-up systems for sensitive indicators 未知
公开(公告)号：GB500652A
公开(公告)日：1939-02-14
申请号：GB1648737
申请日：1937-06-14
申请人： SPERRY GYROSCOPE CO LTD , WILLIAM GEORGE HARDING , ROBERT HAYES NISBET
摘要： 500,652. Electric signalling systems. systems. SPERRY GYROSCOPE CO., Ltd., HARDING, W. G., and NISBET, R. H, June 14, 1937, No. 16487. [Class 40 (i)] A repeater or other object is driven by a servomotor controlled in part by an instrument the position of which is to be reproduced, and in part by a follow-back from the servomotor, corrections for errors in the indications of the instrument being introduced in the follow-back. In Fig. 2, the follow-up member of a gyro - compass operates a selsyn transmitter 2. The signals are applied to the rotor of a selsyn receiver 5 and the voltages induced in the stator control a servomotor 34 which drives the shafts 6 and 6 so that the shaft 6 carrying the rotor of 5 follows the transmitter. A worm on the shaft 6 drives a compass card 12 associated with which is a device for automatically determining the Northsteaming error and moving a rack 20 a vertical distance in proportion to the error. The rack 20 engages a differential 33 connecting the shafts 6 and 6 so that the movements of shaft 6 and rack 20 are added. A reversing gear 85 enables both the shafts 6 and 6 to turn in the same direction. An amplifier 37 suitable for connection between the receiver 5 and the servomotor 34 is described in Specification 417,995. A synchronizing device 38 is also provided to enable the indications of the follow-up member and the uncorrected indications of the compass card 12 to be brought into agreement initially. A fixed pointer 13 and a moving pointer 29 give corrected and uncorrected readings respectively. In the modification shown in Fig. 4, the servomotor is controlled as in Fig. 2, but the correction is introduced in the follow-back by arranging the shafts 6 and 61 on different axes so that compass cards 12 and 12 are eccentric. A lever 57 can be adjusted relative to the card 12 by a screw 58 and carries a pin 56 which engages a radial slot in the compass card 12 . The correction introduced for " damping error " is controlled by the screw 58. Ships' speed and latitude are allowed for by moving the receiver 5 in slides 66 and 67 to vary the eccentricity of the connection between cards 12 and 12 . In a modification, similar to that shown in Fig. 4, the transmitter 2 and receiver 5 are of the step-by-step type and the pin 56 and slot arrangement are replaced by electrical contacts which cause current to pass in one direction or the other through the servomotor 34 according to the direction of rotational displacement of card 12 relative to card 12 . Correction for North-steaming error may be applied as described in Specification 461,424, [Group XX]. Specifications 500,647 and 500,648, also are referred to.

6. 发明专利

GB498738A Improvements relating to electrical transmission systems 未知
公开(公告)号：GB498738A
公开(公告)日：1939-01-09
申请号：GB1312437
申请日：1937-05-07
申请人： SPERRY GYROSCOPE CO LTD , WILLIAM GEORGE HARDING , ROBERT HAYES NISBET
摘要： 498,738. Electric signalling systems. SPERRY GYROSCOPE CO., Ltd., HARDING, W. G., and NISBET, R. H. May 7, 1937, No. 13124. [Class 40 (i)] In an electrical signal transmission system, the signals from a step-by-step transmitter are amplified by means of gas discharge tubes. In Fig. 1, 1, 2, and 3 are gas discharge tubes, the cathodes of which are connected to a tapping point 16 on a resistance bridged across the positive and negative lines 28 and 18 respectively of the D.C. supply. The grids of the discharge tubes are connected to tapping points 19, 20, and 21 on resistances 22, 23 and 24 respectively. The resistances are connected across the D.C. supply through contacts A, B, C so that when each contact is open, the grid of the corresponding tube is negative with respect to the cathode. When a contact, say A, is closed, the grid of tube 1 becomes more positive and the tube becomes conductive, sending a current through the corresponding winding A of the receiver. The secondary of a transformer 8 is connected to the anodes and cathodes of the tubes, to provide the necessary anode potential. The tubes act as rectifiers. The tubes may be arranged in pairs so as to give full wave rectification. The contacts A, B, C may be operated in the transmitter by the follow-up element of a gyro-compass in a ship. Fig. 3 is a circuit diagram of a three-line step-by-step system in which 30 is a receiver and A1 A2, B1 B2, C1 C2 each represent a gas discharge tube arranged to drive current in the direction shown when excited by the transmitter. Fig. 4 shows one way of arranging the discharge tubes A1 and A2. Anode potential for both tubes is supplied by the windings 41, 42 of a transformer 40, the join of the two windings being connected to the point 33 (see also Fig. 3). The point 34 is connected directly to the anode of A2 and to the cathode of A1. A transformer 38 has a cathode winding 37 which is tapped and connected to the centretap of a winding 44, 45. Winding 45 is connected to the grid of A, through an impedance 46 so as to apply a grid voltage in opposite phase to the anode voltage and to render the tube nonconductive. When the transmitter contact 47 is closed, however, the grid is directly connected to the winding 44 applying a voltage in phase with the anode voltage and rendering the tube conductive. The tube A2 is similarly operated. In a modification, the contact for each valve is in the primary circuit of the associated transformer. The pairs of tubes A1 A2, B1 B2, and C1 C2 may be arranged in star instead of delta formation.

7. 发明专利

GB549105A Automatic control systems for aircraft 未知
公开(公告)号：GB549105A
公开(公告)日：1942-11-06
申请号：GB1681940
申请日：1940-11-22
申请人： SPERRY GYROSCOPE CO LTD , ROBERT HAYES NISBET , ARTHUR PHILIP GLENNY
IPC分类号： G05D1/00
摘要： 549,105. Fiuid-pressure servomotors controlsystems. SPERRY GYROSCOPE CO., Ltd., NISBET, R. H., and GLENNY, A. P. Nov. 22, 1940, No. 16819. [Class 135] [Also in Group XX] For the control of aircraft during flight, an alternative manual and automatic pilot control system is combined with an emergency automatic control system, and includes continuously-acting means urging automatic change-over from manual to automatic control and being positively held out of operation by the pilot during . manual control, the automatic controlling mechanism set into action during emergency automatic control being wholly or in part that embodied in the automatic pilot, but the control initiating means for emergency automatic control about at least one axis of the craft including a primary controlling device other than the primary control instrument of the automatic pilot. As shown, the manual control column 1 is connected by cables 2, 3 to the elevator 4. Cable 2 includes a hydraulic servo-motor piston 6 actuated from a relay valve 32 controlled by a diaphragm 27 in a chamber 28. Opposite ends of the latter have restricted air inlets 29, 30, and are connected by pipes 23, 13 and 24, 14 to ports 11, 12 in a casing 10 subjected to suction pressure. Ports 11, 12 are controlled by a plate 8 connected to a gyroscope. Both plate 8 and casing 10 are pivoted at 9. With normal automatic pilot operation the parts are in the position shown, variation in the attitude of the aircraft causing the gyroscope to act on the plate 8 and thus vary the air pressure on opposite sides of the diaphragm 27 which results in movement of the relay valve pistons 33, 34, servomotor piston 6 and elevator 4. Movements of the latter gives a follow-up action on the casing 10 through cables 44, 45, pulley 46, differential gearing 48 and gear 49. The casing 10 may also be under the control of a rate of turn gyroscope (described below) mounted in a casing 54, the movement of this gyroscope being transmitted to the casing 10 through bellows 73, 74, rack 77 and pinions to the differential 48. Alternative means for controlling the servomotor 32, for use in an emergency, consists of a pendulum 103 carried in a casing 105 which is connected to the relay valve 32 and to the rate of turn gyroscope 54 in a similar manner as in the casing 10. The pendulum device 103 may replace the device 10 by operating a handle 107 to rotate valves 17, 18. Pipes 37, 38 leading from the relay valve 32 to the servomotor 7 have a manual byepass valve 80 and an automatic byepass valve 80 1 . The latter is connected to the shaft of a rotary electric magnet 90 the windings of which are connected through a switch 98 and battery 97 to contacts 95, 96. Contacts 95 are on a slidable ring 93 under the pilot's control wheel 92 to which the contacts 96 are fixed, the contacts 95, 96 being normally held apart by springs 94. A spring 91 holds the byepass valve 801 closed when the magnet windings are de-energized. For normal manual control a byepass valve 801 is opened to enable the control surface 4 to be operated by the handwheel 92. Should the pilot desire to set the apparatus for alternative automatic control the handle 101 is rotated to close the switch 98 so that when the pilot grasps the handwheel 92 he moves the ring 93 to close the contacts 95, 96 to complete the circuit through the rotary magnet 90, whereupon the valve 801 moves to interconnect the pipes 37, 38. Should the handwheel 92 be released the automatic control again takes charge. If the pilot wishes to make the emergency automatic control possible he not only actuates the handle 101 to close the switch 98 but also actuates a handle 107 to interconnect pipes 110, 111 with the pipes 23, 24. Thus when he releases the grasp of the handwheel 92, the control of the servomotor 32 is initiated by the pendulum device 103 instead of by the gyroscopic valve device 8. A warning signal, such as by a lamp 102 is given to the rest of the crew when the emergency automatic control takes over. The handles 101, 107 may be interconnected for simultaneous rotation. In a modification, the handle 107 is replaced by automatic means for actuating the valves 17, 18 if the gyroscope of the normal automatic control system should be disturbed. The means for controlling the ailerons are generally similar to that shown in Fig. 1. In the case of the rudder, however, preferably the system operates to bring the rudder to a central position during the emergency control. The byepass valves 801 for all the . servomotors may be interconnected so as to be operated by a single magnet 90, and all the valves 17, 18 may be ganged together for operation by a single handle 107. The rate of turn gyroscope employed in Fig. 1, comprises a rotor 50 in a gimbal ring 51 oscillatable about a vertical axis. A vacuum is maintained within the casing. Air is admitted to the casing through passages 55, 56 controlled by semicircular plates 57, 58 secured to the gimbal ring shaft 53. Thus, if the gimbal ring 51 turns, one of the passages 55, 56 is open to atmospheric pressure and the other to suction pressure according to the direction of rotation. The pressures in the passages 55, 56 are led by pipes 65, 66 to a pair of bellows (one of which 67 is shown), connected by a rod 69 engaging a rod 70 connected to the gimbal ring shaft 53. If the gimbal ring precesses about its axis the difference of pressure set up in the bellows acts on the shaft 53 to check such movement A modified form of control pendulum comprises an inverted rigid pendulum 125, Figs. 2 and 3, pivoted at 128 in a casing 129 which is journalled co-axially with the pivot 128 in a fixed outer casing 130. The bob 137 of the pendulum has very small freedom of movement between walls 138, 139 of a recess 136 in the casing 129 so that if inclined slightly from the vertical position it engages one of the walls 138, 139 and closes a port 140 or 141 in these walls. The ports 140, 141 are connected by channels in a shaft portion 134 of casing 129 with channels 148, 149 which, if the device is used instead of the pendulum 103 of Fig. 1 are connected to the pipes 110, 111, the casing 129 having gears 150, 151 connected to cables 115, 116 for follow-up purposes. Alternatively the pendulum may control electric contacts instead of air ports. Specifications 416,813, [Group XX], 515,290, 531,388, 538,526; 539,058, 543,455, [both in Group XX], and 545,187 are referred to.

8. 发明专利

GB538346A Means for controlling the direction of the axis of a gyroscope 未知
公开(公告)号：GB538346A
公开(公告)日：1941-07-30
申请号：GB149440
申请日：1940-01-25
申请人： ROBERT HAYES NISBET , WILLIAM GEORGE HARDING , SPERRY GYROSCOPE CO LTD
IPC分类号： G01C19/36
摘要： 538,346. Gyroscopic apparatus. NISBET, R. H., HARDING, W. G., and SPERRY GYROSCOPE CO., Ltd. Jan. 25, 1940, Nos. 1494 and 17447. [Class 97 (iii)] In a gyroscopic apparatus employed as an indicating instrument or as a control instrument for an automatic pilot, baffle means are provided on the rotor bearing frame to intercept continuous air jets for applying a torque in one direction or the other, and thereby precessing the gyroscope so as to follow a controlling member mounted for rotation through at least 90 degrees relative to the gyroscope about the secondary (vertical) axis of sensitivity. The axis of the gyroscope may, for example, be caused to follow a controlling member positioned by a direction-giving instrument such as the repeater of a magnetic compass, the slower precessional movements of the gyroscope avoiding intrinsic wandering. In the directional gyroscope shown in Fig. 1, the rotor 1 is driven by air jets as described in Specification 394,412 and deviations in direction of the craft to which the gyroscope is applied are detected by observing a compass card 17 attached to the vertical ring 9. If extraneous torques change the direction of the gyroscope, inclined air jets issuing from holes 44, 45 in a U-shaped controlling member 31 act differentially on a partial hemispherical baffle 37 attached to the rotor-bearing frame 4 and cause the gyroscope to precess about the vertical axis A, A 1 until restored to its normal position relative to the controlling member 31. If the craft banks so that the axis A, A 1 becomes inclined, the spherical form of the baffle 37 prevents the air jets from affecting the resultant torque. The controlling member 31 may be turned about the vertical axis A, A 1 by gearing operated by a shaft 34. In Fig. 3 the invention is shown applied to a directional gyroscope of wellknown type and provided with means for controlling the steering of aircraft. The gyroscope is shown in its locked or " caged " position resulting from the inward operation of the push-pull knob 46 as described in Specification 419,816. In the operative position of the gyroscope, the knob is pulled out to free the parts. If the aircraft yaws, air ports 68, 69 adjustably mounted on the casing move relative to the diametrical edge of a semi-circular plate 70 secured to the vertical gyroscope ring 9 and differentially affect the flow of air through the ports to two pipes 56 (one pipe only shown). An external relay device (not shown) connected to the two pipes controls the aircraft's rudder, for example as described in Specification 416,813 and causes the aircraft to turn to restore the original alignment of the ports 68, 69 with the diametrical base of the plate 70. The air-jet nozzles 74, 75 (and two similar nozzles at the opposite side of the vertical ring 9) for applying torque to the gyroscope are carried by two hollow U-shaped structures 70 1 secured to opposite sides of the vertical ring 9. The nozzles direct air on to two turbine wheels 80, 81 attached to the rotor-bearing frame 4. The air jets are partially interrupted by a controlling baffle 82 comprising two semi-circular strips attached to a spindle 83. In the normal position of the baffle the torques are balanced, but when the baffle is rotated, the interception of the air jets is varied and a torque is applied to cause the gyroscope to precess around the vertical axis A, A 1 towards the normal position relative to the baffle. The controlling baffle 82 (or the controlling member 31, Fig. 1) may itself be governed by the movements of a magnetic compass 90 connected to the baffle 82 by a transmitter 91, receiver 92 and gearing 93 ; or alternatively the baffle 82 may be governed through the agency of a servo-motor operated for example as described in Specification 513,624. In a further modification, Fig. 5, an air jet from a nozzle 97 carried by the vertical ring 9 is normally divided into upward and downward streams by the vertical abutting edges of two oppositely-directed conical surfaces or baffles 99, 100 supported by rollers 102, 103 for rotation by the repeater shaft 111. The divided streams impinge equally on a serrated segment 94 carried by the rotorbearing frame 4 and the torques are balanced. If the conical surfaces are displaced so that one or other of them pre-dominates, a corresponding torque is produced by the jets acting on the segment 94, and the gyroscope is caused to precess about the vertical axis until the normal position is again reached. In a modification, Fig. 8 (not shown), the nozzle 97 is replaced by two nozzles. In a further modification, Fig. 9, air jets issuing from nozzles 113, 114 in the vertical ring 9 are normally each bisected by the ends of a semi-circular baffle wall 115, and no resultant torque is then applied to the gyroscope. If the baffle is rotated about its vertical axis, for example by a magnetic compass repeater connected to the shaft 119, one or other of the air nozzles 113, 114 is fully opened and the other is closed by the baffle. The full jet is directed through one or other of two tubes 135, 136 to play upon a turbine 139 fixed to the rotor-bearing frame 4 thus applying a torque to the gyroscope and causing it to precess until the neutral position relative to the baffle is again reached. Specification 549,042 and U.S.A. Specification 2,003,270 also are referred to.

9. 发明专利

GB500715A Improvements relating to electrical transmission systems 未知
公开(公告)号：GB500715A
公开(公告)日：1939-02-07
申请号：GB3710138
申请日：1937-05-07
申请人： SPERRY GYROSCOPE CO LTD , WILLIAM GEORGE HARDING , ROBERT HAYES NISBET

10. 发明专利

GB500648A Improvements relating to systems for transmitting indications 未知
公开(公告)号：GB500648A
公开(公告)日：1939-02-07
申请号：GB1312737
申请日：1937-05-07
申请人： SPERRY GYROSCOPE CO LTD , WILLIAM GEORGE HARDING , ROBERT HAYES NISBET
IPC分类号： G05D3/12
摘要： 500,648. Electric signalling Systems. SPERRY GYROSCOPE CO., Ltd., HARDING, W. G., and NISBET, R. H. May 7, 1937, No. 13127. Divided out of 500,647 and 500,652. [Class 40 (i)] In a system for transmitting indications from a member which follows up a sensitive indicator (such as a gyroscopic or magnetic compass) the signals transmitted are corrected in respect of the lag in the following-up. In Fig. 3, a member 1 is controlled by means, not shown, to follow up a directional element 88. The lag is measured by means of a variable air-gap balanced transformer having a core member 96 on the element 1 and a soft-iron armature 95 on the element 88. A "selsyn" transmitter 2 is geared to the member 1 and two distributed field windings 98 and 99 are energized by the A.C. supply that supplies transformer 96 and by the output of an amplifier 97 respectively. The amplifier produces an amplified version of the output of transformer 96. The signals transmitted depend therefore on both the movement of the member 1 and the lag. In the modification shown in Fig. 4, the correction is not applied in the transmitter 2 but is applied in an auxiliary transmitter, the three windings 101, 102, and 103 of the stator being energized by signals from the transmitter 2 and the rotor 100 being energized by amplified signals from the transformer used to measure the lag. The transmission lines 3 are connected to the windings 101, 102 and 103. This correction may be applied to the transmission system shown in Fig. 3 of Specification 500,647 and in this case the transformer used to measure the lag also controls the follow-up motor as described in Specifications 417,995 and 480,115. Specification 500,652 also is referred to. Specifications 360,428, [Group XXXVII], 405,251, and 489,271, also are referred to in the Provisional Specification.

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