US2463119A

US2463119A - Aerial torpedo

Info

Publication number: US2463119A
Application number: US460760A
Authority: US
Inventors: Howard T Pyle; Andrew G Tynan
Original assignee: Motors Liquidation Co
Current assignee: Motors Liquidation Co
Priority date: 1942-10-05
Filing date: 1942-10-05
Publication date: 1949-03-01
Anticipated expiration: 1966-03-01

Description

March i, 3949. H. T. PYLE :E1-Al.

AERIAL TORPEDO 2 Sheets-Sheet l Find oct. 5, 1942 f1 EEN .MMA "n" Huh.

IN VEN -ro/es flown/ea 7'. PYLE ana HND/@sw 6. vv/ymv Tron/ways.

March l, 1949., H.T.PY| E ETAL 463m AERIAL TORPEDO Filed Oct. 5, 1942 2 Sheets-Sheet 2 zag) ' /aof INVENTORS /fowqo ryw /7//0 /yopfw s. www

ATTORN EYS Patented Mar. l, 1949 AERIAL TORIPEDO Howard T. Pyle and Andrew G. Tynan, Kokomo,

Ind., assignors to Detroit, Mich., a

General Motors Corporation, corporation of Delaware Application October 5, 1942, Serial No. 460,760

8 Claims.

This invention relates to control mechanism for a torpedo and particularly an aerial torpedo adapted to be released or launched from an airplane or airship.

The type of control mechanism to which the present invention relates is shown, for example, in the copending companion application of Robert H. Hill and James A. Guyton, Serial No. 461,370, filed Oct. 9, 1942 which discloses a torpedo provided with a control mechanism adapted automatically to maintain the torpedo in a substantially direct path of travel toward a substantially constant light source which illuminates the target. The control mechanism is contained in a unitary housing attached to the torpedo. The housingY hasv ns and steering rudders for guiding purposes and ailerons for stabilizing the torpedo during its flight. The ailerons are controlled by a compass in such manner that rotation of the torpedo is prevented during downward night. The direction of flight is controlled by the steering rudders` which are operated by servo-mechanisms controlled by four spaced photo-electric cells mounted at the. head end of the torpedo.. Deviation from the proper course of flight causes certain cells to become more active than others. Consequently the servomechanism operates to bring the torpedo back into the correct course for landing upon the lluminatedV target.

The housing of the Hill and Guyton application carries four rudders mounted in pairs upon two shafts at right angles. Each shaft may be driven by a constantly operating servo-motor by either of two gear trains connectible with the motor by a magnetic clutch. Therefore there are four clutches and four photo-electric cells individually controlling these clutches. When one cell becomes more active than the others, one of the rudder shafts will beconnected with the electric motor due to the energization of the magnetic clutch associated with the more active cell. The shaft will turn suiiiciently to cause the torpedo to be brought back into the proper course. The control system providesl that the two shafts may operate at the same time to correct for deviation from course; but the magnetic clutches controlling the operation of the same rudder shaft cannot operate at the same time.

The Hill and Guyton system of control isrsuccessful when the intensity of ambient illumination is relatively low. That is, the illuminated target should be clearly distinguished from any general illumination around the target. The present' invention is concerned with the elimination disclosed in the aforementioned of effects upon the control apparatus dueto general illumination regardless of its intensity.

Therefore it is among the objects` of the present invention to provide a torpedo with control mechanism adapted automatically to maintain the torpedo in a substantially direct path of travel toward a source of intermittent light flashes in the direction of which the torpedo Was initially launched. These intermittent light dashes on or near the target may be provided in various manners. A specially designed and constructed flareV may be dropped onv the target previous to the launching of the torpedo, said nare giving oi ashesof predetermined intensity and at predetermined intervals. Another Way to provide the guiding light flashes is to have the airplane which Will launch the torpedo, equipped with ay search light adapted to cast strong rays of light toward and upon the objective, said light flashes occurring at certain intervals so as to be adapted to cooperate with the control device of the present invention to guide the torpedo toward its objective or target.

The dii'erences between the control circuits copending, application and the one disclosed in the present application are as follows:

The control circuit of the copending application requires a constant source of light at the objective to render it operative for controlling the flight of the torpedo.

On the contrary, the control circuit of the present application is designed and constructed to be responsive only to intermittent flashes of light of predetermined intensity, intervals and duration. A constant source of direct or ambient light has no effect thereon.

For instance, when a torpedo, equipped with .-.ie control device of the copending application, is to be launched upon an objective there must rst be placed upon said objective a light inthe form -of a are, incendiary bomb or any other suitable light source from which a constant light beam of suicient intensity emanates. With a torpedo equipped with the control circuits of the present invention a source of light giving oi intermittent flashes must be used. The light flashes, mustv be of a sufficient intensity and must reoccur at predetermined intervals, dependent upon the characterk and design of the electrical units in the control device. The control circuits of the present application provide for elimination of the eiiiects` of constant illumination.v upon the photonelectric cells and passes to the conof the one shown, the power supply being in common to both control circuits.

Fig. 2 is a diagram showing the circuits of the heater elements of all of the tubes used in the circuit of Fig. 1. l

Fig. 3 is a chart showing the relative timing of the light intervals, duration of light flashes, duration of relay energization and deenergization and the resultant operation of a magnetic clutch.

Fig. 4 is a plan View in outline of a torpedo equipped with the present invention.

Fig. 5 is a side view in outline of the torpedo shown in Fig. 1, the various elements in the casing attachable to the torpedo being shown in their proper relative positions.

Referring to the drawings and particularly to the Figs. 4 and 5 thereof, the torpedo itself is designated by the numeral X having a casing 26X attached thereto by any suitable manner, as for instance bands 28X. Within the casing 26X there is provided the control mechanism for controlling the flight of the torpedo after it is launched from the ying airplane or airship toward the illuminated target.

The front end of the casing 26X is open and in its open end of the casing the optical mechan-4 ism of the control apparatus is secured. This optical mechanism includes four photo-electric tubes, and for purposes of this description two are referred to, being numbered 93IA and. 93|B.

The rear end of the casing is stream-lined and has a group of oppositely disposed

fins

29A and 29B, 29C and 29D. These ns are at 90 one to another.

Elevators

30A and 30B and

rudders

30C and 30D are pivotally secured on the casing so as to be in alignment with the respective iin and capable of being hingedly moved out of alignment with the respective iin in either direction. These fins and their respective aligned steering members form the steering mechanism for the torpedo during its flight.

The casing 23X is also provided with oppositely disposed wings SIX and 32X respectively. Each wing has a hinged aileron, the aileron on the wing 3IX being designated by the numeral 33X, and the one for wing 32 by the numeral 34X.

The steering rudders and elevators are actuated by a servo mechanism 10X which may be of any suitable type of servo mechanism, for instance the type illustrated, described and claimed in the copending application, Serial No. 461,370, filed Oct. 9, 1942, by Robert H. Hill and James H. Guyton. This servo mechanism 10X is controlled in turn by the optical apparatus previously described as being located at the front open end of the casing 26X and comprises a plurality of photo-electric tubes among which are the ones referred to by the numeral 93|A and 931B.

' The

ailerons

33X and 34X on the respective wings 31X and 32X are actuated and controlled by a servo mechanism X of the same type as the servo mechanism 10X, this aileron actually being mechanically controlled by a compass 50X. The source of electric power is shown in the form of a storage battery 60X.

As has been previously mentioned, the guiding rudders and elevators are actuated under the control of an optical system including photoelectric tubes. When the torpedo is launched from the flying plane or airship, the switch 64X is automatically operated to connect the storage battery 60X with the entire electrical system, rendering the system operative immediately upon launching. Preparatory to launching the compass 50X is set so that the photo-electric tubes are directed toward the illuminated target at a predetermined or certain directional relation relatively to said target. Light rays emanating from the target and in this instance, particularly intermittent ashes of light rays strike the optical system, and as long as the intensity of the light rays strike all of the photo-electric cells equally, a balance is maintained and no actuation of the steering mechanism is effected. However, as soon as the torpedo veers in any direction right or left, or at to these directions, then the balance of intensity of the light rays striking on the optical system is upset so that one tube will receive more intensive light rays than another whereby this tube will be rendered efective to set its control mechanism into operation for actuating the proper steering device so that the torpedo is again brought into the proper path.

The compass control during this time will prevent rotation of the torpedo about its longitudinal axis during its flight, a feature which is absolutely necessary for the proper effective operation of the torpedo. It will readily be seen that if the torpedo were permitted to rotate about its longitudinal axis, the optical system would, if such rotation is complete about the axis, rotate in a circle whose radial distance would be equal to the distance between the center of the torpedo 25X and the casing 26X. Traveling in this circle would entirely upset equilibrium, for the various photo-electric cells would at all times be changing their relative positions to the target and would be rendered effective in quick successive intervals which would correspondingly actuate the various guiding rudders and elevators in quick succession, thereby throwing the torpedo into an unimaginable spin and consequently destroying its effect. With the compass -control cooperating with the optical control so that any tendency of the torpedo to rotate is substantially prevented and immediately corrected, the directional relation of the optical system with the target as set at the time of launching, is practically maintained during the entire night of the torpedo toward its illuminated target and consequently complete control is maintained during its entire flight.

This compass control which acts upon the

ailerons

33X and 34X to prevent turning of the torpedo about its longitudinal axis during its falling flight after being launched from an airplane, is identical with the one disclosed in the aforementioned copending application Serial No. 461,370. The compass 50X is cradled in a gimbal ring 51X so that, by gravity, the axis of its operating parts, especially its polar controlled member, is constantly held at substantially right angles to the horizon. Any tendency of the torpedo to rotate about its longitudinal axis while dropping toward its target will rotate the compass and thereby move its polar controlled part relativelyV to the North Pole causing it to rotate due to polar attraction. As the polar controlled part rotates it aiects certain parts in the compass which cause the servo mechanism 80X to become operative to adjust the

ailerons

33X and 34X. Thus when the torpedo starts to rotate in one direction the compass control adjusts the ailerons to cause the torpedo to be rotated in the opposite direction and be returned to normal position. Each turning tendency of the torpedo is therefore counteracted by the adjustment of the ailerons.

Referring particularly to the Figs. l and of the drawings the numerals 93|A and 535B designate the two multiplier photoelectric tubes adapted, under the influence of intermittent light beams on the objective or target, to eiect control of the operation of the servo-mechanism which actuates two of the four rudders on the torpedo for steering the torpedo toward said objective. This intermittent light beam may be provided by intermittent are dropped on or near the objective or by a search light on the airplane giving intermittent illumination of the target. This intermittent illumination is reflected back upon the photo-electric tubes SSlA and 93| B to cause their proper excitation for control purposes.

The photocathodes o of the tubes 53m and 931B are supplied with high voltage unidirectional current through a `circuit which includes wire 232, filter 235, transformer secondary 225 and half-wave rectier tube 2 X 2. Secondary 226 is part of a power supply unit having a D. C. to A. C. converter 225 is connected through a lter 22lA with the l2 volt battery 22! which is the source of electrical power for the entire control device. The tubes SMA- are of the 9 stage multplying type, having nine dynodes numbered from 1 to 9 and having a ring of voltage dividing resistances marked R. The anodes lil of said tubes are connected respectively by

wires

25 and 23 and condensers 2i and 24 with the

grids

22 and 25 of the tubes GSFE. These condensers 2i and 24 are so constructed and arranged that they will pass only pulsating current tol their

respective grids

22 and 25, any direct current being blocked o` and caused to flow to ground G through the respective resistances 3| and 33 connected to

wires

25 and 23 ahead of the condensers 2i and 24. Because they prevent the passage of direct current, these condensers are called blocking condensers; however, they may also be termed coupling condensers inasmuch as they also couple the anodes I5 with the

respective grids

22 and 25 of tubes 5SF5A and B for the passage of pulsating current. The cathodes 26 and 21 of tubes 5SF5A and 6SF5B respectively are connected together through two load resistances 28 and 2S both of which are connected to ground G through wire 30. Between this wire 3% and the grids of tubes GSFSA and B are connected two grid return resistances 32 and 34 respectively.

Tube 6SF5A has a plate 35 connected toone side of a D. C. blocking and A. C. coupling condenser 37 the other side of which is connected with the grid 39 of the tube 2550A which may be termed a trigger tube. Likewise tube BSFSB has its plate 3S connected to the D. C. blocking and A. C. coupling condenser 38 which is also connected to the grid 45 the trigger tube 255GB.

Plates

35 and 35 are connected through

respective loadv resistances

95 and 95 with a lter 233 of standard design said filter being connected 6. with afull wave rectifier 6X5B fed by the secondary winging 227 of the transformer. The grids 39 and 4D of the trigger tubes 2550A and 235GB respectively are connected through

grid return resistances

45 and 45 connected with adjustable resistances 4'! and 48 connected between the negative pole of the battery 22! and ground G. These adjustable resistances 4l and 4B form what is termed a balancer for equalizing the action of trigger tubes 2050A and 2055B respectively. Adjustment of the grid balancer resistances 47 and 48 determines the grid bias on the tubes 2550A and B respectively and hence determines their triggering point, or in other words determines the amount of plus potential which must be impressed upon the

grids

39 or 45 before the tubes 2050A or 2il5B pass current.

The control relay designated as a whole by the numeral 55 has two electromagnets 53 and 54 adapted to actuate a walking beam armature 65. One end of each winding of electromagnets 53 and 54 is connected to the other as at 55. The other ends of said windings are connected respectively to plates 5l and 52 of the tubes 2050A and 28MB. A wire 5l leading from the juncture point 55 of one end of said electromagnet, windings, connects with one end of the magnet winding 55 of an overload relay 60; A condenser 5| and resistance 52 connected in shunt with winding of magnet 53 provides a timing device adapted to control the action of this electromagnet while a similar condenser 53 and resistance 64 perform the same function for the electromagnet 5,4.

The relay armature 55, grounded at G, has one end normally engaging contact 68 and its other end contact 1l. Contact 65 is connected with cathode 42 of tube 255GB through wire SS. Contact 'Il is connected with the cathode 4! of tube 2550A. A contact 5l is adapted to be engaged by the grounded armature 55 when it is attracted by the energized electromagnet 53. While contact 61 is engaged by the armature 55, said armature is disengaged from contact 'Il while remaining connected with contact $6. Another contact 'lll of the relay is engaged by the armature 65 when it is attracted by energized electromagnet 54 at the same time remaining connected with contact li but severing connection with contact 66.

Normally the clutch magnet coils l5 and 'i6 are disconnected from battery 22l. The movement of armature 55 toward magnet 53 when energized, causes clutch magnet coil i5 to be connected with the battery 22! through contacts 'F2 and 13 of limit switch unit lla. When armature 65 moves toward magnet coil 54, the clutch magnet coil 'I6 is connected with the battery 22l through the contacts 'l1 and 'I8 of limit Switch unit 7l The limit switch unit lla is operated by a rudder operating shaft 'i9 which is caused to rotate in either direction by a servomctor (not shown) depending upon which of the two clutch magnet coils 15, 'IG is energized. The limit switch Ha comprises an actuator cam 32 mounted on the rudder shaft "l5 which shaft when rotated in one direction by said servo-mechanism rotates two of the rudders in one direction; and when rotated in the other direction, the shaft rotates said two rudders in the opposite direction. The two sets of normally engaging contacts l2-l3 and 'll- '58 are arranged on diametrically opposite sides of the rudder shaft 79. Contact i3 is connected to one end of the winding of electromagnetic clutch 'l5 the other end being connected to the negative side of the battery 22|. Likewise contact 18 is connected to one end of the winding of electromagnetic clutch 16 which is also connected to the battery as shown. A flexible arm 10 carries contact 12 and a similar flexible arm 80 carries contact 11. These two

arms

10 and 80 are engaged by the cam 82 at a predetermined point in the counterclockwise or clockwise rotation respectively of the said cam and its shaft 19 whereby the rotation of the two rudders connected to said shaft is limited in either of said directions. Flexible arm 10 of the limit switch 1Ia is connected to contact 61 -while arm 80 is connected to contact 10 of the control relay.

The overload relay has an armature 9D yieldg ably urged to engage a contact 9| connected to the end of the relay winding 58 opposite that to vwhich the control relay windings 53 and 54 are connected by wire 51. A timing device comprising a condenser 60a and a resistance 60h is connected in shunt with magnet winding 58 this device automatically timing the operation of this relay. The armature 90 is connected through a resistance 92 with a full wave rectifier 6X5A fed from the secondary 93 of the transformer.

In order to simplify the circuit diagram Fig. 1, all of the heating units of all of the tubes used are shown with their circuit connections in Fig. 2.

Fig. 3 is a timing chart, the spaces b-b representing the frequency of the light flashes to effect control. For the sake of comparable values these spaces b will represent .l second denoting that the time between successive, intermittent flashes is .l of a second. The letter c designates the time length ing devices, would be excited for a period of .08 of a second iwhich is designated by the letter d, the difference between intervals b and d denoting the time during which the relay light flashes energizing one or the other tube 93 IA or 931B to render it predominating will cause clutch magnet energization over the constant period denoted by the letter e, the clutch magnet, however, becoming inoperative when tubes 93|A and 93|B are again brought into balance by equal excitation or equal exposure to the light rays.

As long as the torpedo, after launching, approaches the objective so that the periodic light rays emanating therefrom fall substantially equally upon tubes 93 |A and 93 IB, both amplifying tubes SFSA and EFSB will be concurrently energized sufliciently to cause trigger tubes 2050A and 20.59B to pass current through the magnet coils 53 and 5A simultaneously. If the relay magnet windings 53 and 54 are simultaneously energized, the armature would continue in normal position and the plate circuits of the tubes 2050A and B would never be broken. However the instant both tubes 2050A and B pass current, the current passed is suflicient to cause overload relay 60 to separate contacts 9|) and 9| and thus to break the plate circuits of both tubes 2959A and B. So long as the cells 93|A and B are both excited simultaneously to a degree sufficient to cause tubes 2950A and B to become simultaneously con ducting, this cycle of operation will be repeated and the relay 66 will operate as a buzzer. Therefore the control relay 55 remains in neutral so long as the excitation of the photo cells is substantially equal.

If, for any reason. the torpedo should veer from its directed course toward the objective then the intermittent light flashes would not strike of the iiash which would be approximately .00001 second. The control relay, due to its timis inoperative. AniT the two photoelectric tubes 93IA and93IB with equal intensity and consequently one of said tubes would be excited to a greater degree than'the other. For instance, let it be assumed that the torpedo has veered from its directed course toward the objective so that the tube 93|A receives a greater intensity of said intermittent light rays than the tube 93 IB. At the same time tube 93 IA might receive ambient light rays which are of a constant value. Tube 93|A will immediately be excited to a greater degree than tube 93IB. In fact under some circumstances tube 93IB would receive no controlling light rays whatsoever. Now, with tube 93|A being excited by light rays some of which are of an ambient, constant nature while the others, actual controlling rays occur periodically, a current will be produced in the wire 20 leading from the anode I0 of tube 93IA said current being of a constant and pulsating character. The constant or D. C. component of this current is blocked by the condenser 2| and caused to return to ground via the resistance winding 3|. The pusating or A. C. component of t-he current in wire 20 passes through the condenser 2|, now acting as a coupling condenser, to the grid 22 of the tube 6SF5A. Excitation of this grid by pulses causes pulses of current to ow from the full wave rectifier tube 6X5B and its iilter 233 through the resistance 95 to plate 35 and across the tube to its cathode 26, cathode resistance 28 back to ground G. Excitation of the tube BSF5A as just described provides an amplification of the pulsating voltage received at grid 22 and impressed amplied pulsating voltage upon the grid 39 of the trigger tube through the coupling condenser 31 which serves also tol prevent passage therethrough of the D. C. current from filter 233, but allowing passage of the amplified A. C. voltage from tube IiSFSA to the grid 39 of the trigger tube 2050A which renders the tube 2050A conductive or what may be termed triggerable. This grid 39 is connected to the grid return resistance 45 which adjustably engages the balancer resistance 41. Adjustment of the resistance 45 along the balancer resistance 41 determines the grid bias on tube 2050A and hence determines its triggering point, in other words, the amount of plus potential which must be impressed upon the grid 39 before the tube 2050A will be conductive or pass current.

When tube 2050A becomes conductive or reaches its triggering point, current will flow from the full wave rectifier tube 6X5A to the armature of the overload relay 60 thence through the contact 9|, normally engaged by the armature, magnet winding 58 to the junction point 56, control relay magnet 53 to the plate 5| of trigger tube 2050A and after passing through said tube to contact 1I, armature 65 and back through ground G. This energizes the control relay magnet 53 to attract and move the armature 65 counterclockwise regarding Fig. 1, thus causing the armature to engage contact 61 and break its engagement with contact 1|, thereby interrupting the plate circuit of tube 2050A and causing it to become nonconducting until again triggered as the result of a succeeding flash of light. When the armature 65 engages contact 61 the circuit across limit switch contacts 12--13 and the electromagnet clutch 15 is completed which renders the rudder operating servo-mechanism operative to move the rudders in the direction necessary to again return the torpedo to its directed course toward the target when the two tubes 93|A and 931B will again receive the intermittent light rays equally. Operation of .the servo-mechanism rotates the shaft 'i9 and the cam 82 counterclockwise, the cam-82 when reaching a predetermined point engaging blade 'i9 and moving it to separate its contact I2 from Contact 13 to break the clutch magnet circuit .and render the servo-mechanism inoperative to continue rudder adjustment.

As the armature 65 of the control relay 55 disengages contact 'il due to energization of relay magnet 53, the circuit through the ytube 2050A is broken rendering said tube inoperative and :at the same time interrupting the :ow or energizing current through the relai/magnet 53. This, if no other means were provided, would quickly render the relay magnet ineffective to hold the armature in attracted position resulting ina substantially immediate discontinuation of clutch energization and servo-mechanism operation. However, in the present arrangement'there is provided a circuit in shunt withthe relay magnet winding 53, this circuit including -a resistance 82 anda 'condenser 6l. The action of these upon the relay magnet is analogous to -the vaction of a dash-pot, that is, this shunt circuit retardsthe deenergization of the relay magnet 53 so `that the armature is retained in its attracted position over a longer period even though the tube current is completely cut oi. This is clearly indicated in the Fig. 3 where c designates the length of the light flash and thus the substantial length of energization while d denotes the extended time of magnet excitation and armature attraction or in other words the duration of closing of contacts 61 and S5.

When armature S5 is returned to its normal position vwhere vit engages contact 'l'l and has disengaged contact-S, then the tube '2050A is again ready to respond to a light flash received Yby the tube 931A. Successive flashes-occur at the rate b, Fig. 3, their time 'length is c and the relay magnet is eiTective over the period d. The intervals between lashes `being short, the time length of flashes exceedingly shorter and the action of the electromagnet relay and electromagnetic clutch on the contrary relatively slow, the operation of cluch magnet and the servo-mechanism controlled by it is substantially sustained during effective recurrent light indicated at e in Fig. 3.

As long as one or the other of tubes 93IA or 93IB is effective to cause operation of relay 55, the vibrating relay is not 7depended upon to render the active trigger tube inactive. However, when both trigger tubes 2055A and ZlB are equally excited and consequently endeavor simultaneously to energize both -electromagnets 53 and 54 of relay 55 then the relay 5D, active as a buzzer, tends to render both trigger tubes 2050A and 2il5B inoperative. Attempted equal 'energization of the relay magnets 53 and 5@ renders the relay inactive; and thus, under this condition, contacts 6l and H are not engaged by the relay armature to render the electromagnetic clutches 'i5 and 'i5 effective.

Resist-ancres i3 and 44 are sufficiently high to limit the plate current to avery 'low value when armature 55 separates from contacts 66 or 'il so that the tubes 2559A and B will become non conducting by said Contact separation, Resistances 43 and i4 serve to reduce sparking at these contacts.

It will be understood that the other two of the four multiplier photoelectric tubes 93! series are provided with the identical arrangement of tubes, relays, condensers, resistances and their circuits 10 as has just been described and that they all work together in the same manner to eiect operation of the servo-mechanism for purposes of adjusting the other cooperating rudderson the torpedo for controlling its ilight in other directions.

In the foregoing the use of the term light is not to be construed as limiting the device to the use of visible light. Any electromagnetic radiation which will actuate photo tubes may be used, including infra red light, visible light, or ultraviolet light. By providing the light source and the lens system of the servo unit with vsuitable light lters the light source may be made invisible to the eye yet still capable of operating the servo control unit. The photo tube may also be of a type specially sensitiveto :the type of light to be used.

The tubes Tubes 93! of which there are four in thecomplete system of control are referred to by their catalogue number and are obtainable 0n the open market. The same is true of the tubes 6SF5 and 2050.

The various electrical units:

Experiments have proven that the electrical dimensions of the various electrical units as given below provide for satisfactory results:

The resistances marked R in tubes f93|A and B are each 100 M ohms Resistances 3l and 33 are each 100 M ohms Condensers 2l-24-'31 and 38 are yeach 120 m. m. f.

Resistances 32--34-45-46 are each 470 M' ohms Resistances -95 are each 270 M ohms Resistances 47-48 are each 25 M ohms Resistances i3- 44 are each 1.2 megohms Resistances {i2- 64 are each 330 ohms Condensers 6 I-f63 are each 10 mid.

Condensers 50a is 50 mfd.

Resistance 60h is 600 ohms The two condensers in filter 233 .are 20 mfd.

The resistance of lter 233 is 5600 ohms Resistance 92 is 150 ohms Secondary winding 226 1350 v. 5 ma.

While the embodiment of the present invention as herein disclosed, constitutes a vpreferred form, it is to be understood that other forms might be adopted, all coming Within the scopevof the claims which follow.

Whatis claimed is as follows:

1. In a control device for an aerial torpedo, the combination with steering rudders on said torpedo; of a source of electric power; a servomechanism adapted to actuate vthe rudders; a multiplier photo-electric tube adapted in response to a constant ambient light and also in response to intermittent light rays impinging thereon, to provide constant and pulsating currents respectively; a condenser for blocking the .current having a constant component .and for passing the current having a pulsating component.; and a voltage amplifying tube, fed by the said pulsating current for passing current to render effective the rudder operating servo-mechanism whereby it Will aotuate certain of said rudders in one direction.

2. In a control device for an aerial torpedo, the combination with steering rudders on said torpedo; of a source of electric power; a servomechanism adapted to actuate the rudders; a multiplier photo-electric tube adapted in response to a constant ambient light and also in response to intermittent light rays impinging thereon, to

provide constant and pulsating currents respectively; a condenser for blocking the current having a constant component and for passing the current having a pulsating component; an amplifying tube excited by the pulsating current for rendering it conductive to current from the source of power whereby said tube provides an amplification of the pulsating voltage received by it from the multiplier photo-electric tube; a condenser for passing only the pulsating component of the current from the amplifying tube; a trigger tube upon which said amplined voltage is impressed; and means for rendering said trigger tube 'effective periodically to eiect energzation of the servo-mechanism to actuate certain of said rudders in one direction.

3. In a control device for an aerial torpedo, combination with steering rudders on said torpedo; of a source of electrical power; a servomechanism for operating said rudders in one direction or the other; a tube adapted to be excited by intermittent light rays impinging thereon to provide pulsating current; a second tube adapted to amplify said pulsating current; a trigger tube excited by said amplified pulsating cur-- rent to render said tube conductive to current -from the power source; and means rendered effective by said current iiow from the power source through the trigger tube to render the servomechanism active to operate certain rudders in one direction and to deenergize the trigger tube.

4. In a control device for an aerial torpedo, the combination with steering rudders on said torpedo; of a source of electrical power; a servomechanism for operating said rudders in one direction or the other; a tube adapted to be excited .by intermittent light rays impinging thereon to provide pulsating current; a second tube adapted to amplify said pulsating current; a trigger tube excited by said amplied pulsating current to render said tube conductive to current from the power source; and an electromagnet relay energized by the flow of current from the power source through the trigger tube for concurrently closing a circ-uit through the servo-mechanism to render it active for moving certain of said rudders in one direction only and for opening a circuit through the trigger tube to render said tube inactive.

5. Ina control device for an aerial torpedo, the combination with four rudders arranged in cooperating pairs; a source of electrical power; a multiplier photoelectric tube for controlling each pair of rudders, each tube being adapted in response to intermittent light rays impinging thereon to provide a pulsating current, an amplifier tube connected to each multiplier tube and excited by said pulsating current to provide an amplified pulsating voltage; a trigger tube connected to each amplifying tube and excited by said amplifled current to be rendered conductive to current from the source of power; a double relay adapted to be energized by the action of one or the other trigger tubes to render servo-mechanism eective to actuate a pair of rudders in one direction or the other and then deenergize the active trigger tube; and means for gradually retarding the deenergization and resultant return to normal of the active relay whereby said tube is reconditioned for another triggering cycle.

6. The invention as defined by claim 5 in which, however, a second relay is provided which is adapted successively to break the trigger tube circuit to render said tube ineffective when both ltrigger tubes equally energize the relay and thus neutralize its effect in response to equal excitation of the two multiplier photoelectric cells.

7. A device in accordance with claim 4 in which, however, the torpedo is provided with stabilizing wings and adjustable ailerons; a servo-mechanismnormally maintaining said ailerons in neutral alignment with their respective wings; and a compass on the torpedo operative in response to turning of the torpedo about its longitudinal axis during its descent flight to cause the last mentioned servo-mechanism to become operative for adjusting the ailerons to counteract said turning of the torpedo whereby the rst mentioned tube is substantially held in constant receiving position relative to said intermittent light rays.

8. A device in accordance with claim 3 in which, however, the torpedo is provided with wings each having an adjustable aileron; a servo-mechanism normally holding said ailerons in normal alignment with their respective wings, but operative to adjust said ailerons for causing the torpedo to rotate about its lonigtudinal axis during downward flight toward the target against which the torpedo was released; a compass on the torpedo, having a polar controlled rotor; and means rendered effective by relative rotation between the compass and its rotor in response to rotation of the torpedo about its longitudinal axis during downward flight for causing the last mentioned servo-mechanism to operate the ailerons whereby the torpedo is returned to its norw mal flight position, thereby substantially maintaining the rst mentioned tube in constant light ray receiving position.

HOWARD T. PYLE. ANDREW G. TYNAN.

REFERENCES CITED The following references are of record in the le of this patent:

UNITED STATES PATENTS Number Name Date 1,376,192 Dye Apr. 26, 1921 1,384,868 Sperry et al July 19, 1921 1,388,932 Centervall Aug. 30, 1921 1,418,605 Sperry June 6, 1922 1,792,937 Sperry Feb. 17, 1931 1,818,708 Hammond Aug. 11, 1931 2,100,934 Berges Nov. 30, 1937 2,123,598 Vos Nov. 22, 1938 2,165,800 Koch July 11, 1939 2,190,390 Thiry Feb. 13, 1940 FOREIGN PATENTS Number Country Date V 305,571 Italy Feb. 9, 1933 339,479 Italy Apr. 22, 1936 797,933 France Feb. 24, 1936