US2911145A - Torpedo director - Google Patents

Description

Nov. 3, 1959' E. ODIN ET AL TORPEDO DIRECTOR 5 Sheets-Sheet 2 Filed Jan. 28, 1939 w M? R.

ERR .QQKEQ Y B Nov. 3, 1959 E. ODIN ET Al. 2,911,145

TORPEDO DIRECTOR Filed Jan. 28, 1939 3 Sheets-Sheet 3 fi/w/us x :05 ANGIE 67 our/=07- 73 7/ .9 9 5010/05 x 671v ANGLE Z 46 6 6'6 our/ 07- 74 77 I 75 I a 0 80"- 619 as J I6 T ANGLE V 040/05 INPUT lA/Fl/I' United States Patent TORPEDO DIRECTOR Eugene Odin, Brooklyn, and Noel Urquhart, Stewart Manor, N.Y., assignors to American Bosch Arma Corporation Application January 28, 1939, Serial No. 253,260

8 Claims. (Cl. 235-615) This invention relates to computing mechanisms, and has particular reference to the provision of factors for the laying of ordnance for directing propelled or selfpropelling projectiles to a target and the like, although the invention is not limited to that use.

In accordance with the invention, certain types of equations are solved, which involve interdependent variable quantities, by supplying the interdependent variable quantities to mechanism including an electrical follow-up head, on which the quantities are set up in such a way that the variable interdependent quantities which form one side of the equation are supplied as an input to one member of the follow-up head, and the variable interdependent quantities which form the other side of the equation are supplied as an input to the other member of the follow-up head. The engagement of the contacts of the follow-up head upon operation eifect energization of a follow-up motor which rotates in the direction which will drive mechanical devices to change the values of the interde pendent quantities simultaneously, so that both members of the follow-up head will be driven into synchronism with each other. When synchronism between the members of the follow-up head exists, it will indicate by suitable means that the correct values of the interdependent variable quantities have been obtained to satisfy and thereby solve the equation.

For a more complete understanding of this invention, reference may be had to the accompanying drawings, in which:

Figure 1 is a diagram which illustrates a typical ordnance problem, such as a submarine torpedo direction problem;

Fig. 2 is a schematic diagram of the computing mechanism of this invention;

Fig. 3 is a perspective illustration of the proportionator; and

Fig. 4 is a perspective illustration of one form of resolver.

Referring to Fig. 1, which illustrates the torpedo direction problem, the range R is the distance from the observation instrument of own ship 0, such as the periscope of a submarine, to the target T at the present instant; target angle A is the angle between the fore and aft axis of the target T and the line of sight to the target T, measured clockwise from target bow; target speed S is the speed of the target T; relative target bearing Br is the angle between the fore and aft axis of own ship 0, and the line of sight to the target T, measured clockwise from own ship bow; gyro angle G is the angle between the fore and aft axis of own ship 0, and the final track of the actual I torpedo, measured clockwise from own ship bow; torpedo run U is the distance traveled by the actual torpedo from the muzzle of the torpedo tube to the point of impact on the target T; impact angle I is the angle between the fore and aft axis of the target T, and the final track of the actual torpedo, measured clockwise from the target bow; target run H is the distance traveled by the target T during the time of actual torpedo run; tube parallax base line P is the parallax base line between mean periscope and torpedo tube; semi-pseudo torpedo run Us is the distance traveled by the semi-pseudo torpedo from the muzzle of the torpedo tube parallel to the final track of the actual torpedo, to a point abreast of the point of impact on the target T; and torpedo advance I is the perpendicular distance between the final track of the actual torpedo and the line from the torpedo tube muzzle parallel to this final track.

The general method of this invention is predicated upon the solution of the torpedo problem equation R sin (G-Br) :H sin I+J+P sin G, where all of the terms of the equation are functions of G.

The apparatus of this invention operates to produce a continuous solution of the impact angle I, predicted torpedo run U, and the corrected gyro angle G, which is the gyro angle G corrected as required, to compensate for the error caused by balancing of a torpedo gyro in one latitude and the firing of the torpedo in another latitude. In the system of this invention, the range R, relative target bearing Br, target angle A, and target speed S, are received mechanically or electrically from the local or remote observation and calculating instruments in accordance with the usual practice, and as the observation and calculating instruments which derive the above quantities may be of any conventional construction and form no part of the present invention, they need not be illustrated or described. The mechanical construction and operation of the component elements of the system will be described first and then their functional operation will be described in connection with a problem.

Referring to the schematic diagram of the system, Fig. 2, the received range R is supplied to the input member 11 of resolver 10; relative target bearing Br is supplied to the input member 12 of mechanical differential 13; target angle A is supplied to the input member 14 of differential 15; and target speed S is supplied to the input member 17 of proportionator 16. The proportionator 16 has four input members, 17, 18, 21 and 56, of which the input member 18 is driven by the output member 19 of differential 20, input member 21 is driven by the output member 22 of differential 23, and input member 56 is driven by the output member 62 of differential 63, in a manner to be described.

The proportionator 16 is illustrated in perspective in Fig. 3, and consists essentially of three similar carriagewithin-a-carriage arrangements designated generally as 24, 25 and 26, carriage arrangement 24 being adapted to position arms 27 and 28, so that the position of these arms will thereby determine the proportionality factor for the carriage arrangements 24, 25 and 26. The input member 21 of carriage arrangement 24 is secured to long pinion gear 29 which engages rack 30. The rack 30 is mounted on inner carirage 31, which is supported by four rollers 32 engaging the rails 33 of outer carriage 34, which in turn is supported by four rollers 35 engaging rails 36. The longitudinal axes of the rails 33 are parallel to each other and lie in the same horizontal plane, and the longitudinal axes of the rails 36 are parallel to each other and lie in the same horizontal plane. The longitudinal axes of rails 36 also lie in vertical planes which are at right angles to the vertical planes of the longitudinal axes of rails 33. Outer carriage 34 carries a rack 37 which is engaged by the pinion 38 of the input member 18, so that rotation of input member 18 drives the outer carriage 34 along the rails 36. Similarly, rotation of input member 21 of carriage arrangement 24 drives inner carriage 31 along the rails 33 by means of pinion 29 and rack 30. Rack 30 slides sidewise on pinion 29 as outer carriage 34 moves along rails 36 and the length of pinion 29 is so proportioned that it will remain in engagement with rack 30, within the limits of movement of outer carriage 34.

A vertical stud 39 depending from the underside of inner carriage 31 is journalled in carriage 40 having four rollers 41 which engage opposite edges of arm 27 pivotally mounted on pin 42, which is secured to a part 43 of the stationary frame of the proportionator. Arm 28, located below arm 27, is similarly pivoted to the other end of pin 42, and the arms 27 and 28 are secured to each other at one end by means of end fastener 44, so that both arms will rotate as a unit about the axis of pin 42. The opposite edges of arm 28 are engaged by the four rollers 45 of carriage 46 from which depends the vertical stud 47 having the inner carriage 48 of carriage arrangement 25 journalled on its lower end Carriage arrangement 25 is similar to 24 with the rollers of its inner carriage 48 engaging the parallel side rails of outer carriage 49, and the rollers of the outer carriage 49 engaging their respective parallel rails 50. The input member 17 of carriage arrangement 25 positions the outer carriage 49 by means of pinion 51 and rack 52. The movement of inner carriage 48 Within the outer carriage 49 is transmitted to the output member 53 of the carriage arrangement 25 by means of rack 54 and long pinion gear 55.

The third carriage arrangement 26 is likewise similar to 24 and 25, its latitude correction input member 56 positioning the outer carriage 57, and the movement of inner carriage 58 within the outer carriage 57 being transmitted to the output member 59. The lower end of stud 60 depending from inner carriage 58 is journalled in carriage 61 which rides by means of its rollers on the extension of arm 27.

The longitudinal axes of the rails 36, 50 and 57', of respective carriage arrangements 24, 25 and 26 lie in parallel vertical planes, and these rails are secured to the stationary frame of the proportionator.

In the operation of the proportionator 16, the angular position of the vertical plane which contains the longitudinal axes of arms 27 and 28, with respect to any of the parallel vertical planes which contain the longitudinal axes of the stationary rails 36, 50 and 57', is determined by the angular position of the input members 18 and 21 of carriage arrangement 24. In Fig. 3 these arms 27 and 28 are shown in the zero angle position, where the vertical plane which contains their longitudinal axes is parallel to the vertical planes which contain the longitudinal axes of the stationary rails 36, 50 and 57. The rotation of input member 21 of carriage arrangement 24 rotates pinion gear 29, and thereby causes rack 30, inner carriage 31, stud 39, and carriage 40 to move. The movement of carriage 31 along the rails 33 causes the arms 27 and 28 to pivot about the axis of pin 42, and the angle which is generated in a horizontal plane by the movement of arm 27 about the axis of pin 42 is determined by the position of the inner carriage 31 with respect to both the outer carriage 34 and the stationary rails 36.

In effect, the operation of input members 18 and 21 of carriage arrangement 24 will set up a primary right triangle in a horizontal plane, in which the base of the right triangle is determined by the angular position of input member 18, and the altitude is determined by the angular position of input member 21, with the hypotenuse of the triangle being the distance on arm 27 between the vertical axes of stud 39 and pin 42. It therefore follows that the angular departure of arms 27 and 28 from the zero angle position as a result of the operation of carriage arrangement 24 will simultaneously generate equal angles about the axis of pin 42 for the carriage arrangements 25 and 26, so that a secondary right triangle will be set up for each of the carriage arrangements 25 and 26, and the tangents, or slopes, of the equal angles about the axis of pin 42 for the primary and two secondary right triangles, will also be equal to each other, Out- '4 put member 59 of the proportionator drives input member 64 of diflerential 65 in accordance with the value Gm, gyro angle correction in degrees, to be described later, and output member 53 of the proportionator drives input member 66 of resolver 67 in accordance with target run H, also to be described.

The resolver 67, with inputs which are proportional to radius and angle, produces outputs which are proportional to the-product of radius and the sine of the angle, and the product of radius and the cosine of the angle. The resolver 67, illustrated in perspective in Fig. 4, consists essentially of a carriage arrangement 68 which is under the control of the two input members 66 and 69, the movement of the carriage arrangement 68 controlling the movements of sliders 70 and 71. The movements of sliders 70 and 71 drive the respective output members 72 and 73 of resolver 67. The carriage arrangement 68 comprises a large gear 74 having a diametrical slot 97 and the upper surface of the gear supports two parallel rails 75 at the edge of the slot engaged by the rollers 77 of carriage 76. The underside of carriage'76 carries a rack 78 which engages pinion gear 79 secured to the upper end of shaft 80 having gear 81 on its lower end engaging the output gear 82 of differential 83. The radius input member 66 of resolver 67 drives input gear 84 of differential 83 by gear 85, and the other input gear 86 of the differential is driven by large gear 74 whose rotational axis is colinear with the axis of shaft 80 and attached gears 79 and 81. The upper side of carriage 76 carries a stud 88 which extends through the slot 89 in slider 71, and through the slot 90 in slider 70. Carriage 76, slider 70, and slider 71, lie in parallel planes which are perpendicular to the axis of stud 88. The two sliders 70 and 71 are supported by respective rollers 91 and 92 which are journalled to the stationary frame of the resolver.

The radius of the resolver 67 is the perpendicular distance between the axis of stud 88 and the rotational axis of large gear 74, and is under the control of input member 66, whose movement is applied to carriage 76 and attached stud 88 by means of gear 85, gear 84, differential 83, gear 82, gear 81, shaft 80, gear 79 and rack 78. The angle of the resolver 67 is the angular departure of large gear 74 from its zero position, and is under the control of angle input member 69, whose movement is applied to large gear 74 by means of gear 87.

The rollers 91 and 92 restrict the movements of their respective sliders 70 and 71 to linear motion along the paths provided by the rollers, and the sliders and rollers are so positioned that when the angle of the resolver is zero (as is illustrated in Fig. 4), the movement of carriage 76 along the rails 75 will cause stud 88 to move slider 70 an equal distance, while stud 88 slides in slot 89 of slider 71 and transmits no motion to slider 71. When the angle of the resolver is 90, the movement of carriage 76 along the rails 75 will cause stud 88 to move slider 71 an equal distance, while stud 88 slides in slot 90 of slider 70 and transmits no motion to slider 70. It therefore follows that any movement of stud 88, as a result of the movement of either or both input members 66 and 69 of the resolver 67, will be resolved into its component movements which drive the sliders 70 and 71.

In the operation of the resolver 67, slider 70 will be moved to a position where its displacement, from the position it occupies during zero radius on the resolver, will be equal to the product of the resolver radius multi plied by the cosine of the resolver angle, and as slider 70 carries rack 93 which engages pinion gear 94 of output member 72, the angular position of output member 72 of the resolver will be proportional to the product of the resolver radius multiplied by the cosine of the resolver angle; and slider 71 will be moved to a position where its displacement, from the position it occupies during zero radius on the resolver, will 'be equal to the product of the resolver radius multiplied by the sine of the resolver angle, and as the slider 71 carries rack 95 which engages pinion gear 96 of output member 73, the angular position of output member 73 of the resolver will be proportional to the product of the resolver radius multiplied by the sine of the resolver angle.

The application of the angle input to the resolver 67 by shaft 69 rotates rack 78 of carriage 76 around pinion gear 79, and thereby tends to change the radius of the resolver by moving the carriage 76 along the rails 75. The differential 83 is provided to prevent the angle input from affecting the radius of the resolver. The rotation of large gear 74, in response to the movement of angle input member 69, will drive the input gear 86 of the differential, and the resulting rotation of the output gear 82 of the differential will drive gear 81, shaft 80 and pinion 79. Therefore, the application of the angle input to the resolver will simultaneously cause pinion 79 and rack 78 to rotate in the same direction and through the same angle about the axis of rotation of pinion 79, so that the radius of the resolver will not be affected by the operation of the angle input. Output member 72 of resolver 67 drives input member 98 of differential 99, and output member 73 of resolver 67 drives input member 100 of differential 101, as shown in Fig. 2. r

The construction of resolver is similar to that of resolver 67, and therefore does not require detailed description, In resolver 10, the radius input member 11 is driven in accordance with the range R, and the angle input member 102 is driven by follow-up motor 103. Radius multiplied by the cosine of the angle output member 104 of resolver 10 drives the input member 105 of differential 99, and radius multiplied by the sine of the angle output member 106 drives the outer member 107 of follow-up head 108. The contacts of follow-up head 108 control the operation of reversible type follow-up motor 103, in the manner disclosed in copending application Serial No. 141,189, filed May 6, 1937, now Patent No. 2,406,323 by Arthur P. Davis and George Agins, for example. The trolley member 109 of the follow-up head 108 is driven by the output member 110 of differential 101.

Follow-up motor 103 also drives the input member 111 of differential 13, and the input member 112 of differential 15. The output member 113 of differential drives the input member 69 of resolver 67, and the dial 145, which is calibrated to indicate the impact angle I. The output member 114 of differential 13 drives the input member 115 of differential 65, and the cams 116 and 117. The cam follower 122 is actuated by cam 116 so as to rotate the input member 123 of differential 101 in proportion to the value of the cam function at the point of contact of follower 122 with cam 116. The cam follower 124 of cam 117 similarly drives the input member 125 of differential 121, and the output member 126 thereof drives the input member 127 of differential 23, cam 128 and dial 119. The cam follower 129 of cam 128 drives the input member 130 of differential 23. The output member 131 of differential 65 drives dial 132. The output member 118 of differential 99 drives the contact trolley 146 of follow-up head 147. The contacts of follow-up head 147 control the operation of reversible follow-up motor 148, and the motor 148 drives the outer member 149 of follow-up head 147 and the input member 120 of differential 121.

A Latitude Proof adjusting knob 133 is provided to apply the sine of the latitude in which the torpedo gyro was balanced to the input member 134 of differential 63. Dial 135, which is calibrated to indicate latitude, is also driven by adjusting knob 133, so that the operation of the adjusting knob will apply the sine of the desired indicated proof latitude to the input member 134 of differential 63. A Latitude In adjusting knob 136 is provided to apply the sine of the latitude in which the torpedo is to be fired to the input member 137 of difierential 63. Dial 138, which is calibrated to indicate latitude, is also driven by adjusting knob 136, so that the operation of the adjusting knob will apply the sine of the desired indicated latitude to the input member 137 of differential 63. The output of differential 63 is proportional to the algebraic difference between the sines of the Proof Latitude and the Firing Latitude, and the gearing between the output member 62 of differential 63 and the input member 56 of proportionator 16 is so proportioned that the input to input member 56 of proportionator 16 is proportional to A2 [sin (Proof Latitude) sin (Firing Latitude) An Individual Speed Variation adjusting knob 139 is provided to apply the difference between the tested average speed of an individual torpedo for a measured run, and the standard torpedo speed, to the input member 140 of differential dial 20. Dial 141, which is calibrated to indicate knots, is also driven by adjusting knob 139, so that the operation of the adjusting knob will apply the desired knots correction, as indicated on dial 141, to the input member 140 of differential 20. A similar Depth Set adjusting knob 142 is provided to apply the depth speed reduction to the input member 143 of differential 20. Dial 144, which is calibrated to indicate depth in feet, is also driven by adjusting knob 142, so that the operation of the adjusting knob will apply the depth speed reduction in knots for the desired depth of torpedo travel, that is indicated on dial 144, to the input member 143 of differential 20. The output of differential 20 is the standard speed correction which is proportional to the algebraic sum of the individual speed variation and the depth speed reduction. Input member 18 of proportionator 16 is initially positioned for the standard torpedo speed by the setting of adjustable clutch 153, and the position of input member 18 is modified by the standard speed correction of output member 19 of differential 20.

'In operation, and considering the torpedo problem of Fig. 1, the apparatus of this invention continuously receives known inputs of R (range), Br (relative target bearing), A (target angle), S (target speed), from the observation and computing mechanisms which are not shown, and the operation of the apparatus of this invention produces a continuous solution of G (corrected gyro angle), I (impact angle), and U (predicted torpedo run). The R (range) input is applied directly to the radius input member 11 of resolver 10, so that the radius of the resolver will be proportional to R (range). The angle of resolver 10 is proportional to GBr, and this angle may be any value at the start, usually and probably the last value of G-Br left on the apparatus from the previous problem. A value which is proportional to G-Br is also applied to differential 15, where it combines with A (target angle), so that the output of the differential 15 is proportional to I (impact angle), since I =A+ (GBr) as determined geometrically for the angles indicated in Fig. 1. The output of differential 15 is applied to the angle input member 69 of resolver 67.

The value of H (target run), which may be any value at the start, is applied by output member 53 of proportionator 16 to the radius input member 66 of resolver 67, so that the radius of resolver 67 is proportional to H. From the radius and angle inputs to the resolvers 10 and 67, the resolvers continuously produce the since and cosine functions, as described. Thus, the output of output member 72 of resolver 67 is proportional to H cos I, and the output of output member 104 of resolver 10 is proportional to R cos (GBr), and these outputs are applied to differential 99 which algebraically subtracts H cos I from R cos (GBr) so that the output of differential 99 is proportional to Us+P cos G. The relationship (R cos [G-Br] (H cos I )=Us+'P cos G is determined geometrically from the problem diagram. The output of differential 99 is applied to the contact trolley 146 of follow-up head 147, and the resulting operation of follow-up motor 148 will drive the outer member 149 of the follow-up head 147 into angular correspondence with its contact trolley, and in so doing the follow-up motor 148 also supplies an input which is proportional to Us-l-P cos G to the input member 120 of differential 121.

Br (relative target bearing) is applied directly to the input member 12 of differential 13, and the other input member 111 of the differential receives a value which is proportional to GBr from follow-up motor 103. Differential 13 combines the two inputs so that the output of output member 114 is proportional to G, and this value of G is applied to the input member 115 of differential 65, and to the cams 116 and 117. Cam 117 is so proportioned that with an input which is proportional to G, the output of the cam follower 124 is proportional to Ug-P cos G, where Ug is an added distance a torpedo must travel in addition to the semi-pseudo torpedo run (Us), during the time interval between the instant of firing the torpedo and the instant when the torpedo arrives at the point of impact. The output of cam follower 124 is applied to the input member 125 of diiferential 121 which combines Us-l-P cos G with Ug-P cos G so that the output of output member 126 will be proportional to Us+ Ug. The value of Us+ Ug is applied to the input member 127 of differential 23, dial 119, and to cam 128. Cam 128 is so proportioned that with an input which is proportional to Us+Ug, the output of the cam. follower 129 is proportional to Uz, which is a correction to a given torpedo run, of which it is a function, due to the difference between the inherent speed characteristics (average speed) and the assigned speed characteristics (standard speed) of a torpedo. The output of cam follower 129 is applied to the input member 130 of differential 23 which combines Us+ Ug with Uz so that the output of output member 22 will be proportional to Us+ Ug+ Uz.

As previously explained, the input member 18 of proportionator 16 is initially positioned for the Standard Torpedo Speed, and the output of differential 20 modifies the position of input member 18 so that the base of the primary right triangle of proportionator 16 will be proportional to Sd, which is standard torpedo speed corrected for individual speed variation and depth speed reduction. Output member 22 of differential 23 applies Us-l-Ug-l-Uz to input member 21 of proportionator 16, so that the altitude of the primary right triangle of proportionator 16 will be proportional to Us+ Ug-l-Uz. It therefore follows that the slope of the primary right triangle (Us Ug+ U2) Sd will be proportional to Ta (corrected time of torpedo run).

S (target speed) is applied directly to the input member 17 of the proportionator 16 sot hat the base of the lower secondary right triangle of the proportionator will be proportional to S. The altitude of the lower secondary right triangle is equal to the base times the slope, so that the output of output member 53 of the proportionator 16 will be proportional to the product of S and Ta, which is H (target run).

The output member 62 of differential 63 applies ,4,, [sin (Proof Latitude)- sin (Firing Latitude)] to the input member 56 of the proportionator, so that the base of the upper secondary right triangle of the proportionator 16 will be proportional to this value. The altitude of the upper secondary right triangle is equal to the base times the slope, so that the output of output member 59 of the proportionator will be proportional to A3 [sin (Proof Latitude)- sin (Firing Latitude)] times Ta, which is Gm (gyro angle correction) in degrees. Gm is algebraically added to G in differential 65, so that the output of the differential will be proportional to G (corrected gyro angle), and G' will be indicated on dial 132.

The value of H thus obtained by means of proportionator 16, changes the initial input to input member 66 of resolver 67, and thereby changes the H sin I, and the H cos 1, output values of the resolver 67. The change in the H cos I value of resolver 67 will be transmitted through differential 99 to differential 121 by means of follow-up head 147 and follow-up motor 148, and on to cam 128 and differential 23, and then from differential 23 to the input member 21 of the proportionator, which thereby changes the altitude of the primary right triangle, so that this sequence of operation continuously will change the H output value of the proportionator until the system becomes synchronized.

The G output value of differential 13 also drives cam 116 which is so proportioned that the output of cam follower 122 is an angular displacement which is proportional to J+P sin G, and this relationship is made possible by utilizing the tactical data in which I is plotted as a function of G. Differential 101 combines H sin I from resolver 67 with J+P sin G from cam follower 122, so that the output of differential 101, which positions contact trolley 109 of follow-up head 108, will be proportional to H sin I-i-J-l-P sin G.

H sin 1+] +P sin G is matched on follow-up head 108 against the R sin (GBr) output of resolver 10, and the physical significance of the values which are matched is illustrated in Fig. 1. If the two inputs to the follow-up head 108 are not matched, the contact trolley 109 will be in engagement with a contact of the outer member 107 of the follow-up head, so that the follow-up motor 103 will thereby be energized to rotate in the direction which will change the G-Br input to resolver 10, the G input to cams 116 and 117, and the I input to resolver 67, until matching does occur. At the same time, for every instantaneous value of G, or GBr, the circuit through resolver 67, differential 99, differential 121, cam 128 and differential 23, proportionator 16, and back to resolver 67, is continuously brought into synchronism, so that when the matching of follow-up head 108 is accomplished, the entire system will be in synchronism. The apparatus will then remain continuously in synchronism for changing values of R, Br, A, and S.

The system will be in its synchronized condition during operation when both of the contact trolleys 109 and 146 of follow-up heads 108 and 147 engage their respective short segments 150 and 151. This characteristic of follow-up head operation is utilized to control the operation of lamp 152, which when lighted will indicate that the system is in synchronism. The circuit for the control of lamp 152 is illustrated in Fig. 2, and may be traced from one side of the electric supply to contact trolley 146 of follow-up head 147, short segment 151, lamp 152, short segment 150 of follow-up head 108, contact trolley 109, and then to the other side of the electric supply. The movement of contact trolley 109 or 146 out of engagement with respective short segment 150 and 151, will break the electrical circuit through the lamp, so that when lamp 152 is not lighted it will indicate that the system is operating to restore itself to the synchronized condition. The Torpedo Problem will be solved when lamp 152 is lighted, so that the indications of dial 132 (corrected gyro angle, G), dial 119 (torpedo run, U= Us+Ug), and dial 145 (impact angle 1) will then be the solution values.

A graphical representation of the relative positions of own ship and target is provided by means of dials 154 and 155. Thus, own ship dial 154 has an outline of own ship engraved on it, and the dial is positioned in response to Br (relative target bearing). Target dial "155 has an outline of target engraved on it, and the dial is positioned in response to A (target angle). The index line 156 between own ship dial 154 and target dial 155 represents the line of sight. Own ship dial 154 as read against index line 156 will indicate Br. Target dial 155 as read against index line 156 will indicate A. A pointer 157 is coaxially journalled with own ship dial 154 so as to be rotated independently of the dial, and the pointer is positioned in response to G-Br, so that from the relationship Br-j-(G-Br) :G, the pointer as read on dial 154 will indicate gyro angle G. A pointer 158 is coaxially journalled with target dial 155 so as to be rotated independently of the dial, and the pointer is positioned in response to G-Br, so that from the relationship A+(GBr) :1, the pointer as read on dial 155 will indicate impact angle I.

While a preferred embodiment of the invention is illustrated and described herein, it is to be understood that the invention is not limited thereby, but is susceptible of changes in form and detail within the scope of the appended claims. For example, the apparatus of this invention may be employed in the laying of guns and other ordnance, as well as the submarine torpedo tube illustrated and described herein by way of example.

We claim:

1. In ordnance laying apparatus, the combination of calculating mechanism adjustable in accordance with predetermined values, an electrical contact device having two relatively movable elements, one of said elements having two separate contacts, operative connections between one of said elements and said mechanism, whereby the latter drives the former, a follow-up apparatus energized by contact between one of said contacts and said other element, operative connections between said follow-up apparatus and said other element for driving the latter from said one contact to the other, a second similar calculating mechanism adjustable in accordance with certain other predetermined values, a second electrical contact device having two relatively movable elements, one of said elements having two separate contacts, operative connections between one of said last-named elements and said second mechanism whereby the latter drives the former, a second follow-up apparatus energized by contact between one of said last-named contacts and said other corresponding element, operative connections between said second follow-up apparatus and said other corresponding element for driving the latter from said last-named one contact to the other, and an electrical indicator having a circuit containing said other contacts of said first and second one element, whereby engagement between them and the corresponding said other element energizes said indicator for indicating equality of the outputs of said first and second mechanisms.

2. In ordnance laying apparatus, the combination of mechanism adjustable in accordance with certain predetermined values, mechanism adjustable in accordance with certain other predetermined values, members actuated by each of said mechanisms, means for combining the movements of a plurality of said members severally actuated by said mechanisms, second means for combining the movements of one of said members and a member movable in accordance with the quantity J+P sin G defined in the annexed specification, and a comparing device actuated jointly by said means only in response to synchronism between them, said device including two sets of electrical contacts and an electrical indicator in circuit with said sets of contacts for energization upon simultaneous engagement of the contacts of both sets.

3. In ordnance laying apparatus, the combination of mechanism adjustable in accordance with the distance to the target and the angle between a relatively fixed base line and a line to the target for developing a value in accordance with the product of the range and a function of said angle, a member actuated by said mechanism in accordance with said value, second mechanism adjustable in accordance with the distance of travel of the projectile to the target, projectile speed and target speed for developing a value in accordance with the distance traveled by the target during projectile flight, a second member actuated by said second mechanism in accordance with said last-named value, a third mechanism adjustable jointly by said second member and in accordance with the angle of impact of the projectile with the target for developing a value in accordance with the product of the distance traveled by the target to the point of impact of the projectile with the target and a function of said angle of impact a third member actuated by said third mechanism in accordance with said last-named value, a first pair of electrical contacts actuated by said first and third mechanisms and in accordance with the quantity J-j-P sin G defined in the annexed specification, a second pair of electrical contacts actuated by said first and third mechanisms, and an electrical indicating means energized upon simultaneous engagement of the contacts of said first and second pairs of contacts for indicating a predetermined relative position of said elements as data for use in laying the ordnance.

4. In ordnance laying apparatus, the combination of mechanism adjustable in accordance with target range and the difference between target bearing angle and gyro angle for developing a value in accordance with the product of range and a function of the said difference angle, mechanism adjustable in accordance with the distance traveled by the target during projectile flight and the angle of impact of the projectile with the target for developing a value in accordance with the product of the predicted distance of travel of the target to the point of projectile impact with the target and a function of said angle of projectile impact with the target, members actuated by each of said mechanisms, means for modifying the movement of at least one of said members in accordance with the quantity J+P sin G defined in the annexed specification, means for comparing the movement of said members severally actuated by said mechanisms, and an indicator actuated by said means only in response to synchronism between said members, said comparing means including two sets of electrical contacts in circuit with said indicator for energizing the same upon simultaneous engagement of contacts of both sets.

5. In ordnance laying apparatus, the combination of mechanism adjustable in accordance with the distance to the target and the angle between a relatively fixed base line and a line to the target for developing a value in accordance with the product of the range and a function of said angle, a member actuated by said mechanism in accordance with said value, second mechanism adjustable in accordance with the distance of travel of the projectile to the target, projectile speed and target speed for developing a value in accordance with the distance traveled by the target during projectile flight, a second member actuated by said second mechanism in accordance with said last-named value, and a third mechanism adjustable jointly by said second member and in accordance with the angle of impact of the projectile with the target for de veloping a value in accordance with the product of the dis tance traveled by the target to the point of impact of the projectile with the target and a function of said angle of impact, a third member actuated by said third mechanism, a fourth member actuated by said third member and in accordance with the quantity J+P sin G defined in the annexed specification, an indicator, and means for comparing the movement of said first and fourth members, including a pair of electrical contact elements actuated by said first and fourth members for making a connection to said indicator.

6. In ordnance laying apparatus, the combination of mechanism adjustable in accordance with the distance to the target and the angle between a relatively fixed base line and a line to the target for developing a value in accordance with the product of the range and a function of said angle, a member actuated by said mechanism in accordance with said value, second mechanism adjustable in accordance with the distance of travel of the projectile to the target, projectile speed and target speed for developing a value in accordance with the distance traveled by the target during projectile flight, a second member actuated by said second mechanism in accordance with said last-named value, and a third mechanism adjustable jointly by said second member and in accordance with the angle of impact of the projectile with the target for developing a value in accordance with the product of the distance traveled by the target to the point of impact of the projectile with the target and a function of said angle of impact, a third member actuated by said third mechanism, means for modifying the movement of at least one of said members in accordance with certain corrections, an indicator, and means for comparing the movement of said first and third members, including a pair of electrical contact elements actuated by said first and third members for making a connection to said indicator.

7. In ordinance laying apparatus, the combination of mechanism adjustable in accordance with the distance to the target and the angle between a relatively fixed base line and a line to the target for developing values in accordance with the product of the range and difierent functions of said angle, respectively, members actuated by said mechanism in accordance with said values, second mechanism adjustable in accordance with the distance of travel of the projectile to the target, projectile speed and target speed for developing a value in accordance with the distance traveled by the target during projectile flight, a second member actuated by said second mechanism in accordance with said last-named value, and a third mechanism adjustable jointly by said second member and in accordance with the angle of impact of the projectile with the target for developing two values each in accordance with the product of the distance traveled by the target to the point of impact of the projectile with the target and a function of said angle of impact, two members actuated by said third mechanism in accordance with said corresponding values, a fourth member actuated by one of said last-named members and in accordance with the quantity J +P sin G defined in the annexed specification a follow-up head actuated jointly by one of said first members and fourth member, a second follow-up head actuated jointly by another of said first members and the other of the two members actuated by said third mechanism and, said follow-up heads each having contacts engageable at a predetermined position of the corresponding actuating members, and an electrical signal having said contacts in its circuit for energization only upon simultaneous engagement of said contacts of the corresponding follow-up devices for indicating synchronism of movement of the said two sets of members.

8. In ordnance laying apparatus, the combination of mechanism adjustable in accordance with the distance to the target and the angle between a relatively fixed base line and a line to the target for developing values in accordance with the product of the range and functions of said angle, respectively, members actuated by said mechanism in accordance with said values, second mechanism adjustable in accordance with the distance of travel of the projectile to the target, projectile speed and target speed for developing a value in accordance with the distance traveled by the target during projectile flight, a second member actuated by said second mechanism in accordance with said last-named value, and a third mechanism adjustable jointly by said second member and in accordance with the angle of impact of the projectile with the target for developing two values each in accordance with the product of the distance traveled by the target to the point of impact of the projectile with the target and a function of said angle of impact, two members actuated by said third mechanism in accordance with said corresponding values, means for modifying the movement of at least one of said last named members in accordance with certain predetermined corrections, a follow up head actuated jointly by one set of said first and third members, a second followup head actuated jointly by another set of said first and third members, said follow-up heads each having contacts engageable at a predetermined position of the corresponding actuating members, and an electrical signal having said contacts in its circuit for energization only upon simultaneous engagement of said contacts of the corresponding follow-up devices for indicating synchronism of movement of the said two sets of members.

References Cited in the file of this patent UNITED STATES PATENTS 706,554 Hall Aug. 12, 1902 923,511 Greenbaum June 1, 1909 1,943,403 Watson Jan. 16, 1934 2,065,303 Chafiee et al Dec. 22, 1936

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