US3018981A

US3018981A - Guidance control for missile

Info

Publication number: US3018981A
Application number: US97061A
Authority: US
Inventors: Weller Royal
Original assignee: Individual
Current assignee: Individual
Priority date: 1949-06-03
Filing date: 1949-06-03
Publication date: 1962-01-30
Anticipated expiration: 1979-01-30

Description

Jan. 30, 1962 R. WELLER 3,913,931

GUIDANCE CONTROL FOR MISSILE Filed June 3, 1949 2 Sheets-Sheet 1 MECHANISM A/V TENN/1 DEFLECT/NG CHARGE SELEG T/VE TRA NSM/TTER FREQUENCY $0 URGE 23 amen m ROYAL WELLER Jan. 30, 1962 R. WELLER 3,018,981

GUIDANCE CONTROL FOR MISSILE v Filed June 3, 1949 2 Sheets-Sheet 2 W1 A I.

D wm mq E BAND P4 55 F L TERS RECE/ l/ER TRANSMITTER 4 s50 ass: 12556 lasso 20.950

ROYAL WELLE I araasr Patented Jan. 30, 1962 3,018,981 GUmANCE CONTROL FOR MISSILE Royal Weller, Silver Spring, Md. (Rochester, N.Y.) Filed June 3, 1949, Ser. No. 97,061 12 Claims. (Cl. 244-44) (Granted under Title 35, US. Code (1952), sec. 266) The present invention relates to guided missiles and more particularly to a signal transmitting and receiving system for performing a control function thereon such,

for example, as a steering operation effective to change I will be deflected from the original trajectory by a signal 3 l of a selected frequency. In other words, all of the launched missiles will be controllable by a signal of a certain frequency when they have travelled a certain period of time from the time of launching.

An object of the present invention is to provide a new and improved arrangement for changing the direction of flight of a missile to meet a changed target condition.

Another object is to provide apparatus for changing the course of a missile in flight without influencing other missiles launched before or after the launching of the instant missile.

Still another object is to provide apparatus for changing the trajectory of a missile in flight having the qualities of simplicity and ruggedness.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:

FIG. 1 is a diagrammatic side elevation of a missile in accordance with the present invention, parts being broken away;

FIG. 2 is a diagram of the control circuit therefor and associated apparatus;

FIG. 3 is a diagram of a signal transmitting apparatus for use with the present invention;

FIG. 4 is a diagram of a modified form of the control circuit; and

FIG. 5 is a diagram of a transmitter for use with the missile of FIG. 1.

Referring more particularly to the drawings in which like numerals indicate like parts throughout the several views there is illustrated in FIG. 1 a missile 10 having a casing composed of a pair of portions 11 and 12. The portion 11, in the present instance, is employed as a ground for the radio receiver of a control mechanism 13 contained therein, while portion 12 serves as the antenna therefor. The portions 11 and 12 are suitably insulated from each other in any well-known manner as by an insulating band 14. An explosive deflecting charge 15 is mounted in one side of the portion 11 and is arranged to be operated by mechanism 13 under conditions to be hereinafter more fully described.

An indicated in FIG. 2 the mechanism 13- comprises a radio receiver 16 which is grounded to portion 11 of the casing 10 and has its antenna lead connected to portion 12 of the casing. Arranged in the tuning circuit 17 of receiver 16 is a variable condenser 13 driven by a .clock 19, the condenser being arranged to progressively vary its capacity during the flight of the missile. In this manner the receiver 1-6 will be tuned to receive a radio signal comprising any one of several possible, continually changing frequencies at any point in the trajectory of the missile. It is to be understood that the clock 19 is provided with a starter mechanism of any well-known variety which will operate to start the clock at the instant of launching of the missile 10. It will thus be seen that the receiver will be tuned to receive a control signal of a certain frequency at only a small fractional or incremental portion of the trajectory and will be tuned to receive a plurality of progressively different frequencies throughout the flight respectively corresponding to other small fractional portions of the trajectory. The missile, thus may be controlled at any point in its flight by a control signal of a frequency which matches the tuned frequency of the receiver controlled by the instant setting of the variable condenser and corresponding to the instant position of the missile. It is also apparent that other missiles in flight which were launched either before or after the instant missile will not be affected at this time by the signal for controlling the aforedescribed missile, for-the reason that the control signal is of short duration and the receivers of the other missiles are tuned at this instant to different frequencies corresponding respectively to their positions in their trajectories at the time the signal is transmitted.

In order to provide for firing the charge 15 a relay 21 has is operating coil 22 in a circuit 23 arranged to be energized at the instant a signal of the proper frequency is received by the radio receiver 16. When coil 22 is energized make contact 24 is brought into circuit closing position against contact 25 thus closing a control circuit 30 including a source of power BA connected to make contact 24 through contact 25 to an electroresponsive detonator 26 or other means for firing deflecting charge 15 and thence to source of power BA.

The particular missile referred to herein is of the spinning type and in altering the trajectory thereof it is possible to improve the target impact probability of the missile whereas no such possibility would exist if the target should change course and the missile were restricted to its initial trajectory.

FIG. 3 illustrates in diagrammatic form a transmitter suitable for use with the present invention which comprises a transmitter 27 having associated therewith a selective frequency source 28 whereby signals of any desired frequency may be selected and transmitted to the missile at any time during the flight thereof.

A modification of the arrangement for progressively selecting the receivable signal frequencies during the flight of the missile is illustrated in diagrammatic form in FIG. 4. A clock 29 is provided which is started as the missile is launched. The clock 29 drives a rotatable brush contact arm 31 having an elongated brush 32. A plurality of ex-tendable contact rods 33 are arranged in radially spaced relation around the path of travel of the contact arm 31 and normally spaced therefrom. The contact rods 33- are yieldably held in their normal position preferably by means of springs 34. Extensions 35 of contact rods are employed as movable cores for the solenoid coils 36. A band-pass filter circuit is indicated at 37, it being understood that there is included therein a plurality of filters each of which is tuned to a different frequency to control a selected one of the solenoid coils 36. A receiver 38 as illustrated in FIG. 4 is provided for the re- 'ception of signals as in the preferred form of the invention.

In operation a signal of a selected frequency is received by the receiver 38. The signal is passed from the "receiver to the band-pass filters 37 wherein the filter tuned .to pass ,the' particular frequency of the instant signal energizes the solenoid coil connected thereto which moves the contact rod associated therewith into contact with the brush 32 of a selected missile. It will thus be seen that brush 32 will be driven by the clock during the entire time of flight and will be progressively adjacent each of the different contact rods at certain intervals of time after the launching of the missile and only those missiles which are within the incremental portion of their I'GSPCC. tive trajectories correspondingto the particular frequency transmitted from the transmitting station will have their brushes 32 in position to be contacted by the selected contact rods and their steering charges fired'thereby. The corresponding contact rodsof other missiles which were fired from a gun at ditferent'times, operate. in response to this signal but without effect as their brushes are not in position to be contacted thereby. i When the signal ceases the brushes are restoredto-their initial positions by their springs 34.

As illustrated in FIG. 5 a transmitter 39 arranged for use with the control mechanism. of FIG. 2 or the modified form of FIG. 4 and includes .a plurality of signal sources 41, 42., 43, 44 and 45, each .of which istuned to produce a different frequency such, for example, as

20, 30, 40, 50 and 60 kilocycles,.respectively. It is, of course, understood that any number of signal sources and any number of solenoid coils may;b ejemployed depending on the length of time, of the flight of the mis- In the illustrative embodimentof FIG. 5. a plurality of

switches

46, 47, 48, 49, and 51 respectively are employed to select the desired frequency, the switches being marked 4, 8, 12, l6 and 20 seconds, respectively,. ifidesired, in

sile and the amount of changes; in frequencydesired.

Ofdl t0 assist the operator-in;selectingthe properswitch a for operation of the correcting apparatus ofaat given missile, such markings indicating the,.-numb.er. -ofelapsed seconds of time after thelaunching Ofi theymissilec at which time the switches are to be operated-,5 '5 z When one of the solenoidco'ils is:energized and the contact rod 33 associatedtherewith;moves into engage.- ment with brush 32 it will bev seen that a trajectory correcting circuit 52 comprising one ofthe contact rods 33, battery 3A1, detonator 26, contact ann 31, .and brush 32 will be energized while the brush is in contact with the extended rod 33, thus firing the correcting charge. It will be understood that if theinstant missile'receives a signal for a certain frequency before or after the brush 32 is in the corresponding position the circuit '52 will not be energized, thus only the missile or missiles launched at a certain time will be affected by any one signal.

As indicated in FIG. 4 the contact assemblies are generally indicated by the letters A, B, C, D and E which in the present instance are influenced or operated by signals of 20, 30, 40, 50 and .60 kilocycles respectively, to correspond with the signals of the transmitter 39.

It will be apparent from the-foregoing description that there has been provided apparatus whereby missiles may be controlled by an operator selectively at will While the missiles are in flight course thereof to meet changing positions of the target or for other reasons.

While the invention has been described-with particularity with respect to a projectile, it is not solimited as the term missile as employed herein is intended to include other missile weapons'such, for example, as rockets and bombs and the invention, therefore, is also suitable for use with spin type rockets, bombs and the like or any other type of missile in which it is desired to change the course thereof during flight. 7

Obviously many modifications and variations of the present invention are possible in the light ofithe above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

What is claimed as new and desired to be secured by Letters Patent of the United States is:

1. Apparatus for altering the trajectory of a missile comprising, a clock arranged to be started as the missile is launched, a selector mechanism having a brush rotated by said clock and a plurality of normally and yieldably retracted radially arranged contact members, said contact members being arranged to be contacted when in an extended position by the brush member as it rotates, a plurality of actuating coils individual to said contact members for moving .the contact members from the retractedto the extended position, a plurality of band-pass filters of different valuesvforvcontrolling the operating frequency of the actuating, coils and operatively connectedthereto for energizing a selected coil when a matching frequency is received, anda radio receiver in the missile for receiving said frequencies.

2.. Apparatus for changing the trajectory of a missile in flight comprising, a transmitter under the control of ano'perator and having means for transmitting signals of different selected fixed frequencies, a receiver in said missile for. receiving said signals, a clock constructed and arranged to be started as the missile is launched, tuning means continuously driven by said clock for adjusting said receiver continuously and progressively to receive a different one of said signals during each of a plurality of successive periods of time after the launching of the missile whereby a transmitted signal of a selected frequency. may be received by the receiver only during a certain period of time after the launching of the missile, an explosive steering charge carried by the missile,and circuitrclosingmeans operated by said receiver for firing said charge when said' signal of selected frequency is receivedduring the period of time when the receiver is tuned to receive said frequency.

3. Apparatus for changing the trajectory ofa missile in fiightcomprising, a clock in said missile arranged to be started as the missilelis launched, a radio receiver carried by the missile, frequency tuning apparatus driven by saidv clock and operatively connected to said receiver for continuously and progressively varying the signal frequency which the receiver is adapted to receive whereby the receiver is tuned to receive certain signals, each of a different frequency only at certain periods of time during the flight of the missile, an explosive steering charge, and means controlled by said receiver for exploding said charge when the receiver receives a signal of a frequency in matching relation to the period of time during which it is received.

4. In apparatus for changing the trajectory of a missile in flight comprising, a clock arranged to be started as the missile is launched, a variable condenser continuously driven by said clock and arranged in the tuning circuit of a radio receiver whereby the receivable frequency of the receiver is progressively and continuously changed during the flight of the missile, an explosive steering charge, and circuit closing means operatively connected to said receiver for exploding said charge when the condenser is tuned to the frequency of a transmitted signal.

5. In a missile comprising a casing having a pair of electrically conducting sections insulated one from the other, a radio receiver mounted Within said casing, one of said sections being operatively connected to said receiver to provide an antenna therefor, the other of said sections being operatively connected tosaid receiver to provide a ground therefor, a clock in said casing arranged to be started as the missile is launched, a tuning mechanism' for the receiver arranged to be driven continuously by said clock at a predetermined rate and to continuously and progressively change the frequency receivable by said receiver during the flight of the missile, an-explosive steering charge arranged to exhaust at one side of the casing, and means controlled by said receiver for firing said steering charge when the receiver receives a signal corresponding in frequency to the tuned frequency thereof.

6. An apparatus of the character disclosed for changing the trajectory of a missile comprising, a radio receiver carried by the missile, means for continuously and progressively changing the tuning of said receiver at a predetermined rate while the missile is in flight, means for setting the tuning means in operation as the missile starts on said flight, an explosive steering charge carried by the missile and adapted to exhaust therefrom laterally with respect to the line of flight, and means operatively connected to said receiver and controlled thereby for firing said charge when the receiver receives a radio signal to which it is tuned.

7. In a system for altering the course of a projectile, in combination, a transmitting station having means for transmitting radio signals selectively of different fixed frequencies, each of said signals having a frequency corresponding to a different incremental fractional portion of the trajectory of the projectile, a radio receiver carried by said projectile, means for continuously and progressively changing the tuning of said receiver at a predetermined fixed rate during the flight of the projectile whereby the receiver is responsive to a selected signal from said transmitting station during a selected portion of said trajectory corresponding thereto, an explosive steering charge carried by the projectile and arranged to exhaust from one side thereof as the charge is fired, and means including an elect-ro-responsive detonator operatively connected to said receiver and controlled thereby for exploding said charge as a signal is received by the receiver.

8. In a system of the character disclosed for changing the trajectory of a missile in flight, in combination, a source of radio signals of fixed frequency at a control station, means for initiating radio transmission of said signals at a predetermined interval of time after the projectile has been fired from a gun, radio receiving means on the projectile, means carried by the projectile for continuously and progressively changing the tuning of said receiver at a rate proportional to the distance traveled by the projectile during flight thereby to maintain correlative relation between the instant position of the projectile and the signal frequency received by said receiver, an explosive deflecting charge carried by the projectile and adapted to exhaust radially in one direction from the axis thereof, and means including an electroresponsive detonator controlled by said receiver for exploding said charge when a signal is received from the control station corresponding to the instant frequency of the receiver to which the receiver is tuned.

9. In a system for selecting a missile from a group of missiles in flight and fired from a gun in successive order, in combination, a plurality of tuned radio receivers respectively carried by the missiles, means on each missile for continuously and progressively changing the tuning of the receiver during the flight of the missile, means at a control station for suddenly transmitting a radio signal corresponding in frequency to the instant tuned frequency of a missile to be selected, an explosive steering charge on each of the missiles, and means for firing said charge as a signal is received by the receiver.

10. A radio controlled missile of the character dis closed comprising a tuned radio receiver, a control circuit connected to said receiver and rendered effective as a signal is received by the receiver, and means for continuously and progressively changing the tuning of the receiver during flight of the missile whereby the missile is controlled by a radio signal matching in frequency the instant tuned frequency of the receiver.

11. A claim according to claim 10 and including means for initiating operation of the tuning means at the instant the missile is in flight.

12. A Selective system for the remote control of missiles in flight, each of said missiles having a tuned radio receiver carried thereby, means for changing the tuning of said receiver continuously and progressively at a predetermined rate during said flight, a control circuit operatively connected to said receiver and rendered effective as a signal is received by the receiver, means for setting said tuning means in operation as the flight is started, and means at a control station for transmitting a radio impulse signal of a frequency corresponding to the instant tuned frequency of one of said receivers whereby the missile carrying said one of the receivers is selected for control from a plurality of said missiles launched in flight in successive order.

References Cited in the file of this patent UNITED STATES PATENTS 2,444,750 Ptacek July 6, 1943 2,415,348 Haigney Feb. 4, 1947 2,446,279 Hammond Aug. 3, 1948 2,490,844 Sorensen Dec. 13, 1949 2,520,433 Robinson Aug. 29, 1950 2,557,949 Deloraine June 26, 1951