Patent GB-635822-A (GB)
Title: Improvements in or relating to gunfire control apparatus
IPC: F41G5/18
Filed: 1943-10-26
Abstract: 635,822. Gun-fire control systems. SPERRY GYROSCOPE CO., Inc. Oct. 26, 1943, No. 17684. Convention date, Oct. 17, 1942. [Class 92 (ii)] [Also in Groups XXXV and XXXVIII] A fire control system for a gun mounted in a fixed position on an aircraft comprises sighting means for tracking the target, means controlled by the sighting means for computing lead angles at which the gun must be positioned in order that projectiles from it will strike the target, and means for steering the aircraft according to the lead angles in order to position the aircraft as well as the gun in accordance with the computed lead angle. Fig. 3 shows diagrammatically successive positions C, C<SP>1</SP>, C" of an aeroplane when tracking a target whose corresponding positions are To, To<SP>1</SP> and To<SP>11</SP>. In each position #A represents the angle between the line of sight and the position at which the guns, and therefore the aeroplane, must be set to hit the target, while Ao represents the present azimuth angle of the target, these angles being measured in the direction of the arrows shown. The sum of the angles in each position represents the angle of error " A error," and when this angle is zero, as at the position C<SP>11</SP>, the aeroplane is correctly positioned in azimuth to fire at and hit the target. The computing mechanism shown in Fig. 4, having calculated the azimuth lead angle #A then solves for the azimuth error angle by the formula " A error " =Ao+ #A and transmits this quantity to an automatic servo control system for the rudder, thus repositioning the aeroplane continually in azimuth until the error angle is zero. Similar mechanism is provided for positioning the aircraft in elevation until the elevation error angle " E error " is zero. One form of mechanism for effecting this result is shown in Fig. 4 and incorporates a scanner as described in Specification 635,821, [Group XL (c)], a receiving and scanning system as described in Specification 621,485, and a computing mechanism. Searching.-When the pilot is searching for a target all the various switches shown in the circuit are in the positions S. As described in Specification 621,485, high-frequency radio pulses from a transmitter 64 are transmitted to a scanner 67 and radiated by antenna 68, the scanner rotating continuously about axis 71 and the antennae nodding about axis 72. The system incorporates, as also in Specification 621,485, telegon transmitters 73, 74, in circuit with a source 78 of alternating current, a demodulator and filter 93 connected to the plates 106, 107 of a cathode-ray tube 105, a range wing circuit 118, and a receiver 109 which is connected to the grid 108 of the cathode-raytube. The arrangement is such that when a target is within the field of the scanner a small line appears on the screen on the tube, the length of the line giving a rough range indication and its position giving the position of the target. The scanner is maintained in alignment with the longitudinal axis of the craft by gyroscopic mechanism in the manner described below. Tracking.-When the screen of the tube indicates the existence of a target, the pilot flies his craft along the line of sight of that target and moves all switches to the position T. Swith 75 then energizes the control coil 77 of a clutch which interrupts the nod motion of the antenna 68 so that the scanner concentrates on a small portion of a hemisphere, while switch 91 cuts out telegon 74 and places telegon 73 in circuit with current source 78, lead 94, demodulator 93, lead 97, and thence to a phasesensitive amplifier 121 via switch 98. The amplifier 121 is also connected through switch 124 with receiver 109, and, as described in Specification 621,485, produces in its leads 128, 129 output voltages representing the elevation and azimuth components of the tracking error, that is the error between the line of sight of the target and the spin axis 71. These two voltages serve to operate respectively two torque motors 144, 147 of a gyroscope mounted on the scanner 67. The gyroscope comprises a rotor spinning about axis 241 in a housing which pivots about an axis perpendicular to 241 in a ring 243, the latter being rotatably mounted about axis 244 in a further ring 246 fixed to the scanner. Pivoted within ring 246 about axis 247 is a ball ring 248 having an opening through which passes,a shaft 240 coaxial with the gyroscope spin axis 241. The two torque motors 144, 147 are connected respectively to the rings 248, 243. In operation, when spin axis 71 of the scanner is not in alignment with the target, current passes through one or both leads 128, 129, thus actuating one or both torque motors and causing the gyroscope to precess. Movements of the shaft 240 thus produced actuate a pick-off 257, the signals from which are amplified by amplifiers 258, 259, connected to servos 261, 262, which, through the gearing shown, move the scanner about its axis 130, 131. Thus the scanner is maintained constantly in line with the target during the tracking operation. Upon the axis 130, 131, are mounted the arms 152, 157, of two potentiometers connected to batteries 154, 159, the leads 155, 162 from which are connected to the potentiometer arms and to a centre tapping. The magnitude and polarity of the voltages across the conductors thereby correspond to the angular displacement of the scanner axis 71 with respect to the craft. When searching, these voltages are applied, through switches 163, 166 to actuate the torque motors of the gyroscope and thus ensure that the axis 71 is maintained in alignment with the aircraft, but when tracking they are applied to the computor to indicate the angles Ao, Eo. During tracking, the voltages applied to the torque motors are proportional to the angular rates Er, Ar, of the target, and these voltages are maintained by time-constant circuits 142, 145- illustrated diagrammatically in more detail in Fig. 7 (not shown)-even when the target is being accurately tracked and there is in consequence no voltages in the leads 128, 129. The voltages corresponding to Ar and Er are fed by leads 173, 172 to the computing mechanism. Computing mechanism.-The input data for this mechanism comprises present range data Do which is supplied through lead 188 from an automatic range circuit as described in Specification 582,279, [Group XXXV], altitude data H supplied by a manual control 212 and indicated air speed (I.A.S.) data introduced by a manual control 216. The computer solves the equation for the time of flight to based on the formula to=f(Do) xf(H) Î f(I.A.S.) and for this purpose the mechanism includes a logarithmic cam 223 which, through rack-and-pinion mechanism 225, 229, gearing 227, and differentials 215, 219, combine with the logarithmic settings of controls 212, 216 to rotate a logarithmic cam 232. The latter, through follower 233 and rack-and-pinion mechanism 234, 235, produces an angular rotation of a shaft 269 proportional to to, the shaft in turn moving the arms of two potentiometers 272, 273, which are supplied respectively with the elevation and azimuth rate voltages Er, Ar. The voltage drop across the taps 276, 281 and the conductors 198, 196 from the arms is therefore proportional to the product of (a) Er and to and (b)ÀAr and to, which products are respectively equal to #E and #A -see Fig. 3. The azimuth lead angle (#A) voltage 198, 276, is placed in series with the present azimuth (Ao) voltage 187 as shown, and the two voltages added algebraically together produce the azimuth error angle (" A error ") according to the formula " A error " = Ao+ #A. In the case of the other potentiometer 272 a battery 280 is arranged in its circuit to provide a correction for super-elevation. The voltages across the pairs of leads 196, 197 and 198, 199 serve to (a) provide an indication of " A error " and " E error" on the cathode-ray tube, (b) energize two relays 283, 284, thereby breaking a circuit 23, 24 for the firing mechanism for the guns, whereby firing can take place only when the two voltages are reduced to zero, and (c) actuate, through amplifiers 200, 202, two servomotors 201, 203 for moving the ailerons and rudder of the craft whereby the craft is automatically controlled until the errors are reduced to zero. The servos 201, 203 may be identical with the aileron servo shown in Fig. 2, referred to below. Rudder and aileron mechanism.-Figs. 1 and 2 show diagrammatically the mechanism for actuating the rudder and ailerons, Fig. 1 showing a computor 1, of the type in Specification 606,957, having output shafts 11, 12, the rotations of which correspond to E " error " and A "error," These shafts actuate racks which are connected to a piston-rod similar to the rod 52 of the aileron servo, Fig. 2. The rod carries three pistons working in a cylinder 55 to which fluid is supplied through conduit 54; the cylinder has an outlet 56 and also has conduits 57, 58 leading to opposite sides of a piston 59 in cylinder 61. This movement of rod 52 produces a differential pressure to actuate piston 59, the latter carrying a rack 16 serving to rotate a pinion 17, Fig. 1, which actuates the rudder or the aileron. Figs. 1 and 2 also show means for ensuring that the aircraft banks correctly, such means comprising a pendulum 35 fitted with a magnetic element 37 located adjacent the legs of a pick-off 40 as shown. The centre leg is wound with a coil 31 excited constantly by a source 32 of alternating current, and the two outer legs are wound oppositely with coils which are connected in series. When the pendulum is correctly positioned (i.e. centrally) no voltage exists across the coil leads 38, 39, but when it moves to one side or the other voltages are induced in the coils which are unequal and the voltage across the leads is passed to an amplifier 41. As shown in Fig. 2, the output leads 42, 43 of the amplifier actuate a torque motor which is connected as shown to a servomotor which act