Patent GB-694850-A (GB)
Title: Improvements relating to aiming equipment for projectile despatching apparatus
IPC: G01S13/42
Filed: 1943-10-20
Abstract: 694,850. Electric control systems. SPERRY GYROSCOPE CO., Inc. Oct. 20, 1943 [May 22, 1942], No. 17314/43. Class 40 (i) [Also in Group XXI] Gun sighting apparatus particularly for use on aircraft comprises means for setting up a reference direction which is independent of the angular movements of the aircraft, and means, including a computer, adapted to set up a line of aim to the target, such line of aim being also substantially independent of the angular displacements of the platform, such as the aircraft, upon which the apparatus is mounted. In the construction shown in Fig. 1 the computer 1 actuates elevation and azimuth transmitters 12, 13, whose output voltages serve to control the orientation of remotely actuated guns as in Specification 630,064, or to indicate the correct firing angles to the gunners. The necessary data is set into the computer by eight shafts 2, 3, 4, 6, 7, 8, 9 and 11 which respectively impart data corresponding to target dimension, indicated air speed, altitude, elevation of the target, azimuth position of the target, slant range, rate of change of azimuth of the target, and rate of change of elevation. The shafts 6, 7, which set in the data corresponding to the elevation and azimuth positions of the target as determined by a sight 10 are controlled in part by the manual operation of a control member 18 which is actuated to maintain the line of sight on the target, and in part by a pair of gyroscopes 70, 90 whose spin axes remain fixed in space whereby any pitching, rolling or yawing of the aircraft on which the sighting device is mounted results in relative movements between the aircraft and the gyroscopes, such motion being suitably transmitted to the shafts 6, 7. As shown in Fig. 2, the control 18 is movable about two axes 19, 21, and serves, through circular rack and pinion devices 23, 27, and gears 34, 36 to move the arms 28, 37, of two potentiometers 29, 38. The potentiometer 29 is energized by a battery 31 and has a centre tap 33. When therefore, the control 18 is moved about axis 19 to maintain the line of sight on the target the voltage in the output wires 32 of the potentiometer 29 corresponds in magnitude and sense to the angle and direction of such movement. In a similar manner a voltage is applied to wires 42 when the control is moved about axis 21. The voltage in the wires 42 is amplified by an amplifier 44, see also Fig. 3, the output of which actuates a torque motor 48 of a servo 46, the arrangement being such that the angular displacement of the member 49 of the motor corresponds in direction and magnitude to the movement of the control 18. Member 49 is centralized by springs 51 and is connected to the piston 52 of a control valve 53, which is supplied with hydraulic or pneumatic pressure by a duct 54. When the piston is moved in either direction a pressure is applied to one side or the other of the fixed piston 59 of a servo 60, thus producing a movement of the cylinder 65 in which piston 59 is mounted. Cylinder 65 is connected to the housing 55 of valve 53 and thus repositions the housing to its neutral position. Cylinder 65 is also connected to the input 61 of a hydraulic variable transmission device, the output 64 of which serves to drive a shaft 47 which is geared to the shaft 7 of the computer. Since the displacement of the cylinder 65 represents the rate at which the shaft 47 is rotating it is geared as shown to a shaft 67 which transmits such motion to the shaft 9 of the computer. In a similar manner the shafts 6, 11 of the computer are actuated when the control 18 is moved about its other axis. Shaft 7 is also actuated by the gyroscope 70 when the aircraft carrying the sighting device and guns changes its attitude in azimuth. Such changes result in a relative movement of the gyro ring 74 with respect to a pick-off 77, the resultant signal being fed to an amplifier 78 controlling a motor 79. The latter repositions the pick-off by worm and worm wheel 81 and link 82, and also drives the shaft 7 via a differential 68. Shaft 7 is :geared as shown to a frame 97 carrying a second gyro 90, which actuates the shaft 6 in a similar manner, the frame being so moved that the axis 93 between the gyrohousing and frame 94 is maintained in a vertical plane containing the target. Slant range data is set into the computer by operating a pedal 109 which through a potentiometer 111 and servo 113 actuates the shaft 8. In a modification Fig. 6 (not shown) the servo 46 is coupled directly to the shaft 7 and the shaft is geared to a turntable carrying a gyro. When the shaft rotates the gyro precesses, and the precessional movement is used to produce the required movement of shaft 9. The other gyro similarly actuates shaft 11. In another modification Fig. 4 (not shown) the gyro in frame 97 spins about a horizontal axis and means, including a pick-off and torque motor, are provided to maintain this axis in the vertical plane containing the target. According to a further modification the mechanism shown in Fig. 1 is actuated by a remote sighting device, such as a telescope, movements of which about vertical and horizontal axes produce signals in self-synchronous transmitters. Such signals are received by generators 133, 134, which are connected as shown, upon actuation of switches 84, 43 with the amplifiers 44, 86. The generators are geared as shown to shafts 88, 47 and their output control signals thereby represent the relative elevation and azimuth displacements between the orientation of the sighting device and the data setting of the shafts 6, 7. Fig. 8 (not shown) illustrates schematically a system whereby the shafts 47, 83, 88 and 107 of Fig 1 are coupled to transmitters which are connected to generators having follow-up devices adapted to actuate the remote sight. By this arrangement the line of sight is stabilized and corrections, applied by the manual control, become necessary only when the target is moving with respect to the earth. In the modification shown in Fig. 9 a single gyro 170 is employed, the gyro consisting of a rotor 171 spinning about axis 172 gimballed in a ring 173 which pivots about axis 174 in a ring 176. The latter pivots about axis 177 in a followup ring 178 which pivots about the same axis in a bracket 179 pivoting about a vertical axis. When control member 18 is moved to follow the target in elevation a control signal passes, as described with reference to Fig. 1, through cable 32 via switch 84 to amplifier 86 the output signal of which actuates a torque motor 48' which in turn actuates a servo 60<SP>1</SP> serving to rotate a pulley 182. The pulley is connected by springs to arms 183 on axis 174 and thereby applies a torque to ring 173. The gyro therefore precesses about axis 177 at a rate proportional to the torque and hence proportional to the signal in cable 42, such precessional movement being sensed by a pick-off 189 the signal from which is amplified at 191. The amplified signal actuates a follow-up motor 193 which serves to drive the follow-up ring 178 via shafts 199, 202, and gearing as shown, and also to drive the input shaft 6 of the computer. The shaft 11 representing the angular rate of the target in elevation is driven by a flexible shaft driven by gearing 213 connected to the pulley 182. Shaft 6 is connected to the sighting device as in the case of Fig. 1. A similar arrangement of devices are employed to follow the target in azimuth, the drive to the torque applying pulley in this instance however, incorporating a solid cam 214 rotationally set by gearing on shaft 6 and vertically set by means controlled by servo 60. The cam applies the necessary corrections arising from the deviations of axis 174 of the gyro from the vertical position. By such means the axis of the gyro is maintained parallel with the line of sight and hence oriented towards the target. Changes in the altitude of the craft on which the sight and gyro are mounted result in the actuation of the follow-up motors which change the orientation of the sighting device with respect to the craft and also actuate the computing mechanism. In a further modification the sighting device incorporates a radio-scanna on which is mounted a gyro to which torques are applied as in Fig. 9, the precessional movements of the gyro being sensed by pick-offs and the amplified signals being used to reposition the scanner to align it with the target. Movements of the scanner are transmitted by electrical transmitters to receivers associated with the computer. The main features of the system are substantially the same as the sighting system described in Specification 714,670. Specification 360,428, [Group XX], also is referred to.