US3118638A - Decoy for guided missiles - Google Patents

Decoy for guided missiles Download PDF

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US3118638A
US3118638A US771059A US77105958A US3118638A US 3118638 A US3118638 A US 3118638A US 771059 A US771059 A US 771059A US 77105958 A US77105958 A US 77105958A US 3118638 A US3118638 A US 3118638A
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casing
decoy
balloon
battery
openings
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US771059A
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Fred H Rohr
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Rohr Inc
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Fred H Rohr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
    • F41J2/02—Active targets transmitting infrared radiation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
    • F41J9/00—Moving targets, i.e. moving when fired at
    • F41J9/08—Airborne targets, e.g. drones, kites, balloons
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/70—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies for dispensing radar chaff or infrared material

Definitions

  • This invention relates to a device for diverting a guided missile from an elevated path along which it is moving.
  • Such missiles are known which are launched from platforms on the ground or released from airplanes in the sky and which are steered toward a target by suitable control members mounted in them. Each missile also carries a charge of high explosive which explodes upon striking the target.
  • the target is an aircraft in iiight, its radio or radar transmitter sends out radio waves of one or more frequencies and its hot exhaust pipe and exhaust gas emit infrared radiations.
  • the missile is provided with a receiver or detector which picks up these radio waves or currents or infrared rays, ampliies them and passes the information as to their direction on to the controls of the missile it can be guided to the target source of radiant energy.
  • lt is a main purpose of my invention to provide a decoy device which remains suspended a long time high in the sky and is continually radiating Waves which may be picked up by such a guided missile, divert it from the path along Which it is moving, steer it towards the decoy and cause it to collide therewith and explode.
  • a further object is to provide such a decoy device which is continually radiating radio waves capable of controlling the radio controls of a guided missile and also infrared rays capable of operating its other controls so that the missile will be guided to the decoy irrespective of which type of wave energy its receiver picks up.
  • Another object is to provide a decoy of the type described with a balloon which will keep it suspended for a long time at a substantially constant elevation in the sky.
  • a further object is to provide a hollow casing for the decoy which will contain and enclose its component parts and is shaped as a rocket which is self propelled to a high elevation where the balloon and radiant energy source or sources are expelled from the casing and remain suspended at a desired high altitude.
  • FlG. l is a diagram showing the decoy on a tiring platform and at different stages after firing
  • FIG. 2 is a longitudinal sectional View through the decoy some of the component parts being shown schematically;
  • FIG. 3 is a front View of the decoy in operative position in the sky
  • FIG. 3a is an enlarged view of the decoy of FIG. 3;
  • FIG. 4 is a cross section on line 4 4 of FIG. 3a;
  • FlG. 5 is a circuit diagram of the radio transmitter and infrared lamp
  • FIG. 6 is a sectional View of a tuning condenser and a schematic View of a spring motor for rotating it and;
  • FlG. 7 is an end view of a rotatable plate of the tuning condenser.
  • the decoy comprises a flexible balloon il) which supports a hollow cylindrical casing Il containing a radio transmitter l2, a spring motor 13, an infrared lamp ld or other source of infrared rays and a non-directional antenna l5.
  • the top of casing lll is provided opposite lamp ifi with four large openings or windows 1.6 so that the infrared rays emitted are radiated in all directions from the sides of the casing.
  • the top of lamp lfi is preferably coated with a reiiecting coating lld Patented dan. 2l, 1954 i7 (FIG. 2) which prevents any substantial amount of the emitted rays from traveling up and heating the bottom of balloon il).
  • the transmitter illustrated comprises an oscillator tube 18 which has a tuned plate circuit 9 to which current is supplied by a battery 2li when the switch 2l is closed.
  • Circuit ll@ comprises an adjustable tuning condenser 22 and an inductance coil 23 to which is inductively coupled a feedback coil 24 in the grid circuit 25 which also includes a small battery Z6 for negative grid bias.
  • Condenser 22 (FlGS. 6 and 7) comprises a plurality of thin metal plates 27 mounted on a rotary shaft 23 supported in insulating bearings 29 carried by a metal supporting frame 3b.
  • Frame 3@ has a plurality of thin metal stator plates 3l which lie closely adjacent plates 27 and are of substantially the same shape as these plates.
  • Spring motor i3 may be of any known type which will slowly rotate shaft 2S to cause the frequency of the oscillations generated by tube lill to increase from a minimum frequency to a maximum frequency at each revolution of shaft 28.
  • the range of radio frequencies through which the oscillator is tuned includes the frequency or frequencies to which the resonant radio receiving or input circuits of the guided missiles to be captured are tuned.
  • the oscillations generated by oscillator tube 18 are amplified by amplifier tube 32 whose output circuit is coupled by transformer 33 and lead 34 to antenna l5.
  • Preferably battery Ztl is also used to supply heating current to lamp 14 through the circuit shown which includes an adjustable resistor 35 which regulates the amount of heating current supplied.
  • a suitable filter such as choke coil 36 and condenser 37 prevents the radio frequency currents in the plate circuit of amplifier 32 from passing through battery 2li and lamp le.
  • Casing l1 terminates at its upper end in a cylindrical portion 3S whose upper end tapers out to provide a seat 39 for a ball check valve 40.
  • the cylindrical lower end 4l of the balloon fits around casing portion 33 and is secured thereto by cord or wire Wrapping 42.
  • One or more holes 43 are made through casing portion 3S for a purpose to be described.
  • Valve dll is biased against seat 39 by spring 4d and a flexible wire or cord 45 connects valve lll to the top 46 of the balloon as shown.
  • the balloon is filled with hydrogen or helium in a manner to be later described and distends as it rises.
  • a rocket To propel the decoy high into the sky, its component parts are stowed in a rocket (see FlG. 2) comprising a generally cylindrical metal casing 1257 having the usual guide fins 43.
  • the rear end of the casing contains a charge of solid propellant fuel 49 which can be ignited by 4any suitable igniter Sti.
  • a metal barrier Sl extends across the casing and is secured thereto as by welding, the center of the barrier supporting a short fuse 52 adapted to ignite a power charge 53.
  • a circular plate S4 separates the powder from the rear or lower end 55 of casing il.
  • Member 55 carries an insulating bushing 56 within which antenna l5 is slidable, the top end of the antenna having a stop ilange 57 adapted to engage bushing 56 and limit the outward motion of the antenna under the bias of spring S3 after the decoy leaves casing 47 as later described.
  • a cylindrical casing l59 extends along the inner face of casing 47, this casing being composed of 6 or more separate segments made of polymerized resin, the sides of each segment abutting the sides of the two f thus close switch 21.
  • Disc 62 has a suitable opening 63 to provide access to any ltnown type of tillerorchecli valve 64.- to which a hose f may be connectedto fill the balloon with gas under pres-k A detachable 'pointed nosey piece '65 lits against' sure.
  • the movable blade of switch 21 carriesk al button 66r which protrudes through a small openingin casing 11 and rests againstk plastic casing 59 toy retain the switch in open position before the lrocket is redp A'spring 67 biases the switch blade toward elosediposition.
  • balloon is filled with hydrogen or helium gas toy the desired pressure through valve 64.
  • the frequency 'of the radio waves transmitted' is slowly varied through a range of frequencies so that a guided missile controlled by a radio receiver Whose resonant circuit or circuits are tuned to any frequency within the band of frequencies transmitted by the decoy will be diverted from the path along which it is moving and steered toward the decoy until it colli-des with it.
  • the missile has steering controls operated by a receiver sensitive to infrared radiations, it will be diverted from its path, guided to the decoy and destroyed.
  • the decoy will remain in the sky in the position shown in FIG. 3 for a long time until the spring motor 13 runs down or the battery 26 becomes exhausted.
  • an electric motor operated by current from battery 26 could be used to rotate a gear reducer (not shown) which rotates shaft 28 slowly.
  • a device for ⁇ diverting a guided missile from a path along which it is movingin response to electromagnetic waves picked up thereby froma, target comprising:y an inflated-balloon; a casing depending from said balloon n f said casingk having a wall ⁇ provided with a plurality of op ⁇ positely disposed openings of large yarea therein; yand a kcontinuous source of electromagnetic waves ⁇ of intensity comparable to those emitted by ksaid target disposed within said casing, said source ycomprisingfa battery and an kinfrared lamp yenergized from said battery and mounted ⁇ Within said casing opposite said openings .for emitting; and
  • a .decoy fordiverting a guided missile froman ele- .vated path along kwhich it is moving comprising: ahollow casing having a detachable cap at its upperend; rocket means having a kcharge of solidk propellant fuel ⁇ and an igniter therefor associated Awithy saidcasing for ypropelling it to a predetermined high altitudefrorn a launching stationk wheny the igniter is ignited andthe charge is tired; a
  • housing disposed within said casing and comprisingy ay plurality of separable members, a balloon disposed and continedfwithin said ⁇ housing andhaving a quantity of f gas under pressure therein; means connected'to said balloon and kadapted to be sLpportedy thereby yfor radiating rsignals forguiding a guided missile to said decoy, saidy radiating means being kdisposed within said housing, means operable in time delayed relation to the launchingof ⁇ said f decoy for ejectingsaid cap ⁇ and ⁇ said separable housing from said casing thereby/.to release said balloon ⁇ and .said ⁇ radiating means .from the khousing .and to distend the balloon as saidinembers separate in response tothe pressure of the balloon ⁇ thereon, and valve means disposed Within ⁇ said balloon.
  • saidejectingmeans comprising a powder charge and a fuse for tiring the same disposed within said solid charge remotely from said igniter therefor.

Description

Jan. 21, 1964 F. H. ROHR DEcoY FOR GUIDED MIssILEs 2 Sheets-Sheet 1 Filed Oct. 3l, 1958 INVENTOR.
F. H. R OH R ATTORNEY Jan. 21, 1964 F. H. RoHR DECOY FOR GUIDED MISSILES 2 Sheets-Sheet 2 Filed Oct. 31, 1958 INV ENTOR.
F.H.ROHR maw-rz. f
ATTORNEY United States Patent O 3,118,638 DECY FR GUEDED MlSlilLES Fred H. Rohr, San Diego, Calif. Filed Oat. 3l, 1958, Ser. No. 77l,t359 2 claims. (or. 24e- 1ro This invention relates to a device for diverting a guided missile from an elevated path along which it is moving.
Such missiles are known which are launched from platforms on the ground or released from airplanes in the sky and which are steered toward a target by suitable control members mounted in them. Each missile also carries a charge of high explosive which explodes upon striking the target. When the target is an aircraft in iiight, its radio or radar transmitter sends out radio waves of one or more frequencies and its hot exhaust pipe and exhaust gas emit infrared radiations. lf the missile is provided with a receiver or detector which picks up these radio waves or currents or infrared rays, ampliies them and passes the information as to their direction on to the controls of the missile it can be guided to the target source of radiant energy.
lt is a main purpose of my invention to provide a decoy device which remains suspended a long time high in the sky and is continually radiating Waves which may be picked up by such a guided missile, divert it from the path along Which it is moving, steer it towards the decoy and cause it to collide therewith and explode.
A further object is to provide such a decoy device which is continually radiating radio waves capable of controlling the radio controls of a guided missile and also infrared rays capable of operating its other controls so that the missile will be guided to the decoy irrespective of which type of wave energy its receiver picks up.
Another object is to provide a decoy of the type described with a balloon which will keep it suspended for a long time at a substantially constant elevation in the sky.
A further object is to provide a hollow casing for the decoy which will contain and enclose its component parts and is shaped as a rocket which is self propelled to a high elevation where the balloon and radiant energy source or sources are expelled from the casing and remain suspended at a desired high altitude.
Other objects will become apparent as a detailed description of my novel decoy proceeds. For a better understanding of the invention reference is made to the accompanying drawings, in which:
FlG. l is a diagram showing the decoy on a tiring platform and at different stages after firing;
FIG. 2 is a longitudinal sectional View through the decoy some of the component parts being shown schematically;
FIG. 3 is a front View of the decoy in operative position in the sky;
FIG. 3a is an enlarged view of the decoy of FIG. 3;
FIG. 4 is a cross section on line 4 4 of FIG. 3a;
FlG. 5 is a circuit diagram of the radio transmitter and infrared lamp;
FIG. 6 is a sectional View of a tuning condenser and a schematic View of a spring motor for rotating it and;
FlG. 7 is an end view of a rotatable plate of the tuning condenser.
Referring to FIGS. 3 and 3a the decoy comprises a flexible balloon il) which supports a hollow cylindrical casing Il containing a radio transmitter l2, a spring motor 13, an infrared lamp ld or other source of infrared rays and a non-directional antenna l5. The top of casing lll is provided opposite lamp ifi with four large openings or windows 1.6 so that the infrared rays emitted are radiated in all directions from the sides of the casing. The top of lamp lfi is preferably coated with a reiiecting coating lld Patented dan. 2l, 1954 i7 (FIG. 2) which prevents any substantial amount of the emitted rays from traveling up and heating the bottom of balloon il).
Referring to FIG. 5, the transmitter illustrated comprises an oscillator tube 18 which has a tuned plate circuit 9 to which current is supplied by a battery 2li when the switch 2l is closed. Circuit ll@ comprises an adjustable tuning condenser 22 and an inductance coil 23 to which is inductively coupled a feedback coil 24 in the grid circuit 25 which also includes a small battery Z6 for negative grid bias. Condenser 22 (FlGS. 6 and 7) comprises a plurality of thin metal plates 27 mounted on a rotary shaft 23 supported in insulating bearings 29 carried by a metal supporting frame 3b. Frame 3@ has a plurality of thin metal stator plates 3l which lie closely adjacent plates 27 and are of substantially the same shape as these plates. Spring motor i3 may be of any known type which will slowly rotate shaft 2S to cause the frequency of the oscillations generated by tube lill to increase from a minimum frequency to a maximum frequency at each revolution of shaft 28. The range of radio frequencies through which the oscillator is tuned includes the frequency or frequencies to which the resonant radio receiving or input circuits of the guided missiles to be captured are tuned. The oscillations generated by oscillator tube 18 are amplified by amplifier tube 32 whose output circuit is coupled by transformer 33 and lead 34 to antenna l5. Preferably battery Ztl is also used to supply heating current to lamp 14 through the circuit shown which includes an adjustable resistor 35 which regulates the amount of heating current supplied. A suitable filter such as choke coil 36 and condenser 37 prevents the radio frequency currents in the plate circuit of amplifier 32 from passing through battery 2li and lamp le.
Casing l1 (see FIG. 3a) terminates at its upper end in a cylindrical portion 3S whose upper end tapers out to provide a seat 39 for a ball check valve 40. The cylindrical lower end 4l of the balloon fits around casing portion 33 and is secured thereto by cord or wire Wrapping 42. One or more holes 43 are made through casing portion 3S for a purpose to be described. Valve dll is biased against seat 39 by spring 4d and a flexible wire or cord 45 connects valve lll to the top 46 of the balloon as shown. The balloon is filled with hydrogen or helium in a manner to be later described and distends as it rises. When it reaches a certain height, its small ascent above this level would cause its further distention which would cause wire l5 to lift valve dll from its seat 39, permitting some of its contained gas to escape through the openings 43 and restore the balloon to its desired maximum size. Means is thus provided to keep the balloon for a long time approximately at a desired height.
To propel the decoy high into the sky, its component parts are stowed in a rocket (see FlG. 2) comprising a generally cylindrical metal casing 1257 having the usual guide fins 43. The rear end of the casing contains a charge of solid propellant fuel 49 which can be ignited by 4any suitable igniter Sti. A metal barrier Sl extends across the casing and is secured thereto as by welding, the center of the barrier supporting a short fuse 52 adapted to ignite a power charge 53. A circular plate S4 separates the powder from the rear or lower end 55 of casing il. Member 55 carries an insulating bushing 56 within which antenna l5 is slidable, the top end of the antenna having a stop ilange 57 adapted to engage bushing 56 and limit the outward motion of the antenna under the bias of spring S3 after the decoy leaves casing 47 as later described. A cylindrical casing l59 extends along the inner face of casing 47, this casing being composed of 6 or more separate segments made of polymerized resin, the sides of each segment abutting the sides of the two f thus close switch 21.
o? adjacent seg. ents so that casing 59 can easily tall apart after it leaves casing 47.k The top end or" casing 591s provided with a ygroover 6i? which receives kan expansible tasas snap ring 6i which retains a circular plasticy disc62 yin position,this disci having a concave `face against which the top'portionof balloon itl presses, as illustrated Disc 62 has a suitable opening 63 to provide access to any ltnown type of tillerorchecli valve 64.- to which a hose f may be connectedto fill the balloon with gas under pres-k A detachable 'pointed nosey piece '65 lits against' sure. the `ends of casings 47 yand 59 and minimizes the air resistance as the rocket risesy quickly to altitude. kThe movable blade of switch 21 carriesk al button 66r which protrudes through a small openingin casing 11 and rests againstk plastic casing 59 toy retain the switch in open position before the lrocket is redp A'spring 67 biases the switch blade toward elosediposition. f
`To launch the decoyinto the sky ina localityk where enemy guided missiles rare expected, kbt'eforenose Cap 615 is applied, balloon is filled with hydrogen or helium gas toy the desired pressure through valve 64.
63 (FIG. 1)and` redby operating igniter 5G. The thrust 'The separation of the lsegments of casing S9 permits button 66 tomove out under thebias of spring 67 and Current from battery Ztl soon renders oscillator 1S and amplifier 32 operative and since `antenna `is now projecting below the bottom S5 of f ,casingfiL as'shown in FIGS. 3 and 3a, radio1 Wavesare transmitted in all kdirections from thek antenna and also infrared radiations are propagated in all directionsk out-y wardly from lamp 14, as shown in PEG. 3.' As above explained the frequency 'of the radio waves transmitted' is slowly varied through a range of frequencies so that a guided missile controlled by a radio receiver Whose resonant circuit or circuits are tuned to any frequency within the band of frequencies transmitted by the decoy will be diverted from the path along which it is moving and steered toward the decoy until it colli-des with it. On the other hand if the missile has steering controls operated by a receiver sensitive to infrared radiations, it will be diverted from its path, guided to the decoy and destroyed. The decoy will remain in the sky in the position shown in FIG. 3 for a long time until the spring motor 13 runs down or the battery 26 becomes exhausted. Instead of spring motor 13, an electric motor operated by current from battery 26 could be used to rotate a gear reducer (not shown) which rotates shaft 28 slowly.
This invention may be embodied in other forms or carried out in other ways without departing from the spirit or essential characteristics thereof. The present embodiment of the invention is therefore to be considered as in all respects illustrative and not restrictive, the scope of the invention being indicated by the appended claims, and all changes which come within the meaning and range of equivalency of the claims are intended to be embraced therein.
Cap r65' is ythen attached and the rocket put on a launching platform Havingthns described my invention, what Iclaim as new and useful and desire to secure by Letters Patentis: 1. A device for` diverting a guided missile from a path along which it is movingin response to electromagnetic waves picked up thereby froma, target comprising:y an inflated-balloon; a casing depending from said balloon n f said casingk having a wall` provided with a plurality of op` positely disposed openings of large yarea therein; yand a kcontinuous source of electromagnetic waves` of intensity comparable to those emitted by ksaid target disposed within said casing, said source ycomprisingfa battery and an kinfrared lamp yenergized from said battery and mounted `Within said casing opposite said openings .for emitting; and
radiating infraredrays through said openings in substanf tially all directions from the sides of said casing.
2. A .decoy fordiverting a guided missile froman ele- .vated path along kwhich it is moving comprising: ahollow casing having a detachable cap at its upperend; rocket means having a kcharge of solidk propellant fuel` and an igniter therefor associated Awithy saidcasing for ypropelling it to a predetermined high altitudefrorn a launching stationk wheny the igniter is ignited andthe charge is tired; a
housing disposed within said casing and comprisingy ay plurality of separable members, a balloon disposed and continedfwithin said` housing andhaving a quantity of f gas under pressure therein; means connected'to said balloon and kadapted to be sLpportedy thereby yfor radiating rsignals forguiding a guided missile to said decoy, saidy radiating means being kdisposed within said housing, means operable in time delayed relation to the launchingof `said f decoy for ejectingsaid cap `and` said separable housing from said casing thereby/.to release said balloon` and .said` radiating means .from the khousing .and to distend the balloon as saidinembers separate in response tothe pressure of the balloon` thereon, and valve means disposed Within `said balloon. and responsive. to a predetermined distentionthereof in excesszof that obtainable at said n predeterminedl altitude. for, effecting partial deflation of ythe balloon suticient to maintain the` same at said predetermined altitude, saidejectingmeans comprising a powder charge and a fuse for tiring the same disposed within said solid charge remotely from said igniter therefor.
References Cited in the tile of this patent UNITED STATES PATENTS 39,636 Felt Aug. 25, 1863 2,027,367 Blair Jan. 14, 1936 2,192,450 Miller Mar. 5, 1940 2,341,351 Barkley Feb. 8, 1944 2,381,443 Golay Aug. 7, 1945 2,397,114 Anzalone Mar. 26, 1946 2,405,134 Brown et al. Aug. 6, 1946 2,447,972 Weinert Aug. 24, 1948 2,587,564 Williams Feb. 26, 1952 2,603,433 Noslter July 15, 1952 2,655,649 Williams Oct. 13, 1953 2,861,165 Aigrain et al. Nov. 18, 1958 2,869,120 Lolniaugh Jan. 13, 1959 2,913,983 Lytel Nov. 24, 1959 2,987,269 Weller June 6, 1961

Claims (1)

1. A DEVICE FOR DIVERTING A GUIDED MISSILE FROM A PATH ALONG WHICH IT IS MOVING IN RESPONSE TO ELECTROMAGNETIC WAVES PICKED UP THEREBY FROM A TARGET COMPRISING: AN INFLATED BALLOON; A CASING DEPENDING FROM SAID BALLOON SAID CASING HAVING A WALL PROVIDED WITH A PLURALITY OF OPPOSITELY DISPOSED OPENINGS OF LARGE AREA THEREIN; AND A CONTINUOUS SOURCE OF ELECTROMAGNETIC WAVES OF INTENSITY COMPARABLE TO THOSE EMITTED BY SAID TARGET DISPOSED WITHIN SAID CASING, SAID SOURCE COMPRISING A BATTERY AND AN INFRARED LAMP ENERGIZED FROM SAID BATTERY AND MOUNTED WITHIN SAID CASING OPPOSITE SAID OPENINGS FOR EMITTING AND RADIATING INFRARED RAYS THROUGH SAID OPENINGS IN SUBSTANTIALLY ALL DIRECTIONS FROM THE SIDES OF SAID CASING.
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Cited By (8)

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US3457861A (en) * 1968-01-25 1969-07-29 Us Navy Missile booster pressure control mechanism
US3626854A (en) * 1969-09-19 1971-12-14 Jerry R Brooks Self-inflating target projectile
US3930448A (en) * 1972-06-23 1976-01-06 The United States Of America As Represented By The Secretary Of The Navy Rocket-deployed balloon for position marker
US4110724A (en) * 1963-06-25 1978-08-29 Bolkow Gesellschaft Mit Beschrankter Haftung Apparatus for transmission of messages by means of electromagnetic waves
US4753169A (en) * 1985-12-23 1988-06-28 General Dynamics, Pomona Division Ablating electromagnetic shield sheath
US5049883A (en) * 1978-05-30 1991-09-17 The United States Of America As Represented By The Secretary Of The Navy Combined microwave and infrared chaff
US20050151006A1 (en) * 2003-07-16 2005-07-14 Krill Jerry A. High altitude reconnaissance vehicle
EP1735583A2 (en) * 2004-04-05 2006-12-27 Nicholas V. Perricone Illuminated aircraft countermeasures

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US2447972A (en) * 1947-04-07 1948-08-24 Fed Lab Inc Target balloon
US2587564A (en) * 1947-06-07 1952-02-26 Williams Paul Automatic distress signaling device
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US2861165A (en) * 1953-05-05 1958-11-18 Cie Generale Telegraphie Sans Infra-red emitting device
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US2397114A (en) * 1941-01-21 1946-03-26 Aerial Products Inc Rocket construction
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US2655649A (en) * 1945-03-06 1953-10-13 Everard M Williams Object location relay system
US2447972A (en) * 1947-04-07 1948-08-24 Fed Lab Inc Target balloon
US2587564A (en) * 1947-06-07 1952-02-26 Williams Paul Automatic distress signaling device
US2987269A (en) * 1949-06-03 1961-06-06 Weller Royal Method for radar direction of missiles
US2861165A (en) * 1953-05-05 1958-11-18 Cie Generale Telegraphie Sans Infra-red emitting device
US2913983A (en) * 1954-11-29 1959-11-24 Ardell L Lytle Rocket motor
US2869120A (en) * 1956-09-17 1959-01-13 Del Mar Eng Lab Tow target having combustion signal means

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4110724A (en) * 1963-06-25 1978-08-29 Bolkow Gesellschaft Mit Beschrankter Haftung Apparatus for transmission of messages by means of electromagnetic waves
US3457861A (en) * 1968-01-25 1969-07-29 Us Navy Missile booster pressure control mechanism
US3626854A (en) * 1969-09-19 1971-12-14 Jerry R Brooks Self-inflating target projectile
US3930448A (en) * 1972-06-23 1976-01-06 The United States Of America As Represented By The Secretary Of The Navy Rocket-deployed balloon for position marker
US5049883A (en) * 1978-05-30 1991-09-17 The United States Of America As Represented By The Secretary Of The Navy Combined microwave and infrared chaff
US4753169A (en) * 1985-12-23 1988-06-28 General Dynamics, Pomona Division Ablating electromagnetic shield sheath
US20050151006A1 (en) * 2003-07-16 2005-07-14 Krill Jerry A. High altitude reconnaissance vehicle
US7073749B2 (en) * 2003-07-16 2006-07-11 The Johns Hopkins University High altitude reconnaissance vehicle
EP1735583A2 (en) * 2004-04-05 2006-12-27 Nicholas V. Perricone Illuminated aircraft countermeasures
EP1735583A4 (en) * 2004-04-05 2008-04-23 Nicholas V Perricone Illuminated aircraft countermeasures

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