US2414103A - Apparatus for controlling missiles in flight - Google Patents

Description

Jan. 14-, p B. HUNTER APPARATUS FOR CONTROLLING A MISSILE IN FLIGHT Filed July 8, 1941 3 Sheets-Sheet l INVENTOR PAUL B. HUNTER Jan, 14, 1947.

P. B. HUNTER 2,414,103

APPARATUS FOR CONTROLLING A MISSILE IN FLIGHT Filed July 8, 1941 5 Sheets-Sheet 2 FIG-@4- lI m I [I2 l2 1 IMPEDANCE IMPEDANCE 2 5 MATCHING MATCHING 'TRANSFOR TRANSFOR- I I ER R OSCILLATOR I 6 I4 I4 1' 4 AMPLIFIER AMPLIFIER 0 Q 0 O I I I I O O 0 u I RATE RATE cIFgc ulT CIRCUIT EIIIII BEAM INTENSITY Fl EnEFI INVENTOR PAUL B. HUNTER BY DISTANCE T NEY Jan. 14, 1947. .P. B. HUNTER Filed July 8, 1941 APPARATUS FOR CONTROLLING A MISSILE IN FLIGHT 3 Sheets-Sheet 3 PAUL INVENTOR B HUNTER Patented Jan. 14, 1947 APPARATUS FOR CONTROLLING MISSILES IN FLIGHT Paul B. Hunter, Basking Ridge, N. 1., assignor to Sperry Gyroscope Company, Inc., Brooklyn, N. Y., a corporation of New York Application July 8, 1941, Serial No. 401,474

6 Claims.

This invention relates, generally, to the use of ultra-high frequency radio waves for controlling bombs and other explosive missiles such as rocket projectiles, shells, etc., after the same have been discharged from their releasing or projecting apparatus and during flight. This application is a continuation-in-part of application Serial No. 190.540, filed February 15, 1938, for radio controlled aerial bomb, by Paul B. Hunter.

Owing to the constantly increasing height at which military aircraft navigate. it is highly desirable to control explosive missiles such as bombs, aerial torpedoes, shells, etc., after they have left the airplane or the ground as the case may be, in order to correct for the initial sighting errors and other errors including drift errors due to variation of side winds at varying altitudes. Thus, in bombing a target on the ground from an airplane, initial errors present at the time of the release of the bomb are generally augmented by the variations of the bomb trajectory due to such thin s as wobbling of the bomb, variation in the wind direction and speed with changing altitude or change in the speed or direction of movement of a moving target.

The principal object of the present invention is to provide novel apparatus for controlling bombs, explosive missiles such as rocket projectiles, aerial torpedoes, shells, etc.. after the same have started their courses and in continuing such control until the target is actually reached by the missiles whereby the latter are caused to hit the target or to explode at substantially their nearest approach thereto.

Another object of the present invention is to provide an ultra-high frequency transmitter ad- ,iacent the point at which the bomb or other missile is released, the missile being equipped with suitable ultra-high frequency radio receiving apparatus and a servo-mechanism controlled therefrom for effecting the transverse movement of the missile in accordance with signals received from the transmitter.

Still another object of the present invention lies in the provision of ultra-high frequency radio transmission means adapted to transmit one or a plurality of beams of either unmodulated or modulated carrier frequency, which beam or beams are adapted to be projected at the missile for controlling the latter in its movement toward the target, any transverse movement of the missile with respect to the beam or beams serving to initiate the movement of the servo-mechanism for effecting desired transverse movement of the missile to direct the same toward the target.

angular movement of the projected beam or beams being controlled either by optical means as during periods of good visibility.

Other objects and advantages will become apparent from the specification, taken in connection with the accompanying drawings wherein the invention is embodied in concrete form.

In the drawings,

Fig. 1 is a schematic view illustrating one use of the apparatus of the present invention employing a single beam of pure carrier radiation.

Fig. 2 is, in part, a sectional view of a bomb projectile equipped with a position sensitive receiver and servo-mechanism.

Fig. 3 is a diagrammatic view of the structure of Fig. 2.

Fig. 3A is a graph illustrating the system of Fi s. 1 to 5.

Fig. 4 is a vertical part sectional view or a transmitter optical sighting means.

Fig. 5 is a sectional view along line 55 of Fig. 2.

Fig. 6 is a plan view of the structure of Fig. 2. Figs. 7 to 10 are, respectively, elevational, vertical sectional, schematic and transverse sectional views of a somewhat modified form of a bomb projectile.

Similar characters of reference are used in all of the above figures to indicate corresponding parts.

Referring now to Fig. 1, reference numeral I designates an airplane equipped with one form of the transmitter apparatus of the present invention. This craft is adapted to carry an ultrahigh frequency oscillator 2 (Fig. 4), as of the type disclosed in Patent No. 2,242,275 of R. H. Varian,

dated May 20, 1941, for delivering to an aerial transmitter antenna 3, ultra-high frequency carrier waves of the order of 10 cycles per second, such waves being subject to propagation in substantially straight lines and also having the property of penetrating fog, etc., and not being appreciably interfered with by uncontrollable natural phenomena such as radiation from the sun. The antenna 3 is shown provided with a parabolic 5o reflector 4 which has a diameter preferably twenty or more times the wavelength used, whereby this reflector has high resolving power and produces a high directional beam of electromagnetic energy. The reflector 4 and antenna 3 are shown as carried by the lower end of a telescope 5 that has its line of vision coaxial with that of the electromagnetic radiation beam projected from the antenna 3. The telescope is universally mounted as by means of a ball Joint 6 so that I this telescope and the connected transmitter antenna may be turned to any desired angle.

In the event of bombing through the overcast, the telescope 5 need merely be used as an angular shifting means for turning the antenna 3 and reflector 4, the information used for then directing the beam being obtained from a suitable scanning indicator such as a cathode ray tube, as of the type described in copending application Serial No. 406,494, filed August 12, 1941. The ultra-high frequency radio output of the transmitter antenna 3 is adapted to be received by four antennae I, I, 8, 8' carried by the bomb projectile 9, shown in Fig. 2.

As is clearly evident from Fig. 6, antennae I, I' are spaced an appreciable distance apart as by placing these antennae on the outer edges of opposed fins Ill. Similarly, the antennae 8, 8'

are spaced appreciably apart as by being located' on the outer edges of fins I0 extending at right angles to the plane of fins Ill carrying antennae I, I.

In Fig. 3 the antennae I, I are shown as dipoles connected through concentric lines II, I I' to impedance matching transformers I2, I2 of the type disclosed in copending application Serial No. 393,868, filed May17, 1941, William W. Hansen and John R. Woodyard, which in turn supply the received ener y to crystal detectors I3, I3

of the type disclosed in application Serial No.

394,239, filed May 19, 1941, Frederick L. Salisbury. The detected outputs of crystal detectors I3, I3 are supplied to amplifiers I4, I 4 the outputs of which are shown supplied through rate circuits I5, I5 as of the, type disclosed in application Serial No. 11,424, filed March 16, 1935, Francis L. Moseley and William T. Cooke. If desired, the rate. circuits I5, I5 could be omitted. The outputs of these rate circuits are connected respectively to solenoids IE, IS arranged for opposite actuation of armatures I9, I9 connected to a piston II of a balanced valve I8. The central portion of valve I8 is supplied with compressed air or carbon dioxide gas from a tank 2|] through pipe .28. When carbon dioxide is used it may be carried in liquid form in tank 20. Valve I8 has two upper pipes 2I and 2| that have their outer portions extending radially within the cylindrical body of the bomb 9 in opposite directions, the common axis of these portions of the pipes 2 I, 2| passing preferably through the center of gravity of the bomb. Thaouter ends of the pipes 2 I, 2 I project through the housing of the bomb for delivering compressed air or carbon dioxide gas in opposite directions diametrically of the bomb. The radial portion of pipes 2| and 2I' lie in the vertical plane also containing the spaced antennae I and I. I

The antennae 8 and 8' are similarly connected to a receiver circuit, such as shown in Fig. 3, for controlling the operation of solenoids 22 and 22', shown in Fig. 5, the armatures of these solenoids being employed for operating the balanced valve l8 similar to valve I8, valve I8 controlling the flow of compressed air from the pipe 23 to two outwardly extending pipes 24 and 24' extending through the wall of the bomb 9 for directing air or carbon dioxide blasts in diametrically opposite directions. The radial portions of pipes 24 and 24' lie in the plane of antennae 8, 8.

In use, preferably a suitable bomb sight is provided on the aircraft such as that disclosed in Patent No. 2,162,698, dated June 20, 1939, and is employed for releasing the bomb 9 at the proper time and in the proper direction for hitting the target desired. After releasing the bomb and before the same has reached its target the bombardier look through the telescope 5 and observes the falling bomb. To aid him in observing the bomb, the same may be provided with a lamp 25, if desired. Inasmuch as the forward velocity of the bomb decreases gradually after release thereof due to air friction the bombardier would ordinarily direct the pilot to reduce speed so that the aircraft flies over the target at about the same time as the predicted time for the bomb to strike the same.

It is preferable for the bombardier to keep the target or point in sight through the telescope 5 as'the bomb falls. As the bomb approaches the target, the latter moves into the field of vision of the bombardier looking down through the telescope 5 although the target is probably not in the central line of sight of the telescope at this time. If the oscillator 2 is now turned on producing a pencil beam of ultra-high frequency electro-magnetic radiation the field intensity of any cross section of which is greatest at the center .of the beam and tapers off in substantially the fashion shown in Fig. 3A to the side edges thereof, the bomb will ordinarily line itself up with the center of the beam. Assuming that the bomb is not initially lined up with the center of the beam then due to the varying field intensity of the beam across its cross section one of the antennae I or I', for example, will receive more energy than the other, so that the output of amplifier I4, for example, will be made greater than that of amplifier I4, whereby solenoid \IB is energized to a greater extent than solenoid I8 so that the balanced valve I1 is moved to uncover pipe 2| thereby causing tank 20 to discharge compressed air or gas through valve IB and pipe 2I and effecting a movement of the bomb toward the center of the radiating beam, 1. e., toward the left in Fig. 3A. Similarly, if antenna 8, for example, should receive more energy than antenna 8' it would act to shift the bomb transversely in the plane of these antennae to bring the bomb into the central axis 21 of the radiating beam corresponding to the center of the line of sight of the telescope 5. As the bomb projectile is about to strike the target the bombardier gradually shifts the telescope 5 angularly so as to bring his line of sight and hence the bomb into the direct line of the target so that the latter will be hit as desired.

It will be noted from Fig. 3A that as long as the bomb is lined up with the center of line 21 of the radiating electro-magnetic beam, the antennae I, I and 8, 8' will receive equal intensity of signal so that the balanced valves I8, I8 will be held in their neutral positions so that the outthe radiating beam. Owing to the high'pressure of the air or gas within the tank 20 and to the fact that the period of time 01 flight of the bomb is short, the flow of air or gas through ipes 2|, 2| and 24,24 is quite rapid so thatthe reaction force of the jets issuing from these pipes is large,

thereby resulting in an immediate response of the projectile to any deviation of the same from the path of the beam effecting a rapid return of the projectile to the beam.

If desired, instead of using the reaction force of air jets for controlling the transverse movement of the projectile the same may be controlled by movable fins, as shown in Figs. 7 to 10. In these figures t e bomb 3!! is shown provided with four upper fins placed 90' apart around the periphery of the bomb and with four lower fins similarly spaced. Diametrically'opposite upper fins 3i, 3| are fixed upon the ends of a turnable transverse tubular shaft 35 extending through the bomb housing and in these figures, antennae 1 and I are shown connected to concentric lines 28 and 28' that conduct the energy similarly to lines H, II of Fig. 3 to the receiver apparatus 29 similar to the receiver of Fig. 3.

Similarly, the diametrically opposite upper fins 32 and 32 are fixed upon the ends of a turnable transverse tubular shaft .36 that extends through the housing of the bomb. The antennae 8 and 8' in this case feed energy through concentric lines contained within shaft 36 to the receiver 29.

The opposite fins 33 and 33' and the fins 34 and 34' at the lower portion of the bomb are mounted upon shafts 31 and 38, respectively, the shafts also extending through the bomb and being turnably mounted in the housing thereof. Pulleys 39 and 39' are fixed upon shafts 35 and 31 and have a cable 40 passing thereover, this cable being passed one or more times about each of these pulleys, the ends of this cable being connected by piston rods to the opposite sides of a hydraulic or pneumatically operated piston 4| (see Fig. 9) working within a servo cylinder 42 connected to be supplied with working pressure fluid by means of pipes 43 and 43' extending to a balanced piston valve casing 44 within which a balanced piston valve 45 is movable by means of the armatures l9 and I9 operated from solenoids l and 16' as explained in connection with Figs. 1 to 5.

Fluid pressure is supplied to the valve casing 44 through a pipe 46 from a pump 41. The pressure fluid returned from casing 44 passes into branch pipes 49 and 49' leading to pipe 50 connected to the reservoir or sump 48, which, in turn, is connected by pipe 5| to the pump 41. A by-pass valve 52 is provided for by-passing fluid pressure when the servo motor is not operating. The fins 32 and 32' and fins 34 and 34' are also adapted to be operated by a servo motor 52', actuating a cable 53 passing around pulleys 54 and 54' fixed upon shafts 36 and 38. The master control valve 55 for controlling the fiow of pressure fluid to the servo motor 52' is actuated by the armatures of solenoid 22 and 22' as in Figs. 1 to 5. Master valve 55 is connected to be supplied with pressure fiuid from the pump 41.

n use. a y departure of the projectile from the center of the radiated beam will cause the proper control valve 45 or 55, as the case may be, to be operated from the solenoids I 5, 16' or 22, 22' to effect the supply of fluid from pump 41 through pipes 43 or 43 as the case may be to operate piston 4| in the proper direction to so move vanes 3I-3l', 3333', or 32-32, 34-34 so as to bring the bomb back into the central portion or the beam, whereupon the deflected vanes will again be straightened or aligned with the lonsltu axis 0! the bomb.

As many changes could be made in the above construction and many apparently widely different embodiments of this invention could be made without departing from the scope thereof, it is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a lirnting sense.

What is claimed is:

1. In an apparatus for controlling aerial missiles after their release from an aircraft, an angularly adjustable parabolic reflector carried by the craft, an ultra short wave radiator located near the focus of said parabolic reflector for producing a radio beam of substantially pencil shape defining an axis of maximum intensity, 9. radio receiver having angularly spaced antenna elements carried by the missile, servo mechanism controlled from said receiver for moving said missile transversely to steer the same toward the maximum intensity axis of the beam from said radiator, and means for adjusting the angular position of said parabolic reflector so as to direct said radiated beam toward a target.

2. In an apparatus for controlling aerial missiles after their release from an aircraft, an angularly adjustable directive radiator for producing a highly directive radio beam defining an axis of maximum intensity, a plurality of relatively displaced antenna means positioned on the missile, a radio receiver carried by said missile responsive to said antenna means, and servo mechanism controlled from said receiver for deflecting said missile toward the maximum intensity axis of said beam.

3. The apparatus described in claim 2, further characterized by means for adjusting the bearing of said radiator for guiding said missile toward a target.

4. In apparatus for controlling a missile in flight, an ultra high frequency transmitter, directive radiating means fed from said transmitter for radiating a beam of ultra high frequency electromagnetic energy having a predetermined pattern defining an intensity gradient of said energy, movable directing means for directing said energy from said radiating means toward the vicinity of the missile, and receiving means including antenna means disposed on said missile and responsive to said intensity gradient for steering said missile toward a region of maximum intensity of said energy.

5. In apparatus for controlling a missile in flight, an ultra high frequency transmitter, directive antenna means fed from said transmitter, movable directing means for directing ultra high frequency electromagnetic energy from said antenna means toward the vicinity of th missile, receivin means including antenna means disposed on said missile for receiving a portion of said energy, and means in said missile responsive to said received energy for steering said missile according to the directivity of said antenna means.

6. The apparatus described in claim 2, wherein said servo mechanism comprises a source of compressed gas within said missile, jet conduits connected to said source for delivering gas from said source at high velocity to the exterior of the missile, and valve meansfor controlling the supply of compressed gas from said source to said conduits.

PAUL B. HUNTER.

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