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US3282540A - Gun launched terminal guided projectile - Google Patents

Gun launched terminal guided projectile Download PDF

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US3282540A
US3282540A US365216A US36521664A US3282540A US 3282540 A US3282540 A US 3282540A US 365216 A US365216 A US 365216A US 36521664 A US36521664 A US 36521664A US 3282540 A US3282540 A US 3282540A
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projectile
charge
target
radiations
detector
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US365216A
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Henry S Lipinski
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/02—Proximity fuzes; Fuzes for remote detonation operated by intensity of light or similar radiation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • 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
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge

Definitions

  • This invention relates to an improvement upon the gun launched terminal guided projectile disclosed in the prior application of Sidney Ross, Serial No. 831,443, filed August 3, 1959, and now Patent No. 3,072,055, dated January 8, 1963.
  • An object of this invention is to utilize the projectile hardware more effectively for its guidance system permitting a shortening of the length of such a projectile thereby making it more stable and accurate in flight.
  • FIG. 1 is a front end view of the projectile of this invention.
  • FIG. 2 is a longitudinal section through this projectile.
  • FIG. 3 illustrates a construction for the perforate mask described in the above mentioned Ross patent.
  • FIG. 2 shows an embodiment possessing the advantage of the Ross patent construction in an all electronic mechanism capable of quickly and automatically correcting an error in the direction of flight of a projectile in response to an image of the target seen and sensed by the projectile.
  • the projectile parts are numbered using most of the numerals up to 31 to designate equivalent parts in both the Ross construction and the present.
  • This projectile includes a head forward of an adapter 11 and a boom 12 to which are connected stabilizing fins 13 whereby only a slow rotation of about to 25 revolutions per second is needed according to custom with this type of fin stabilized projectile.
  • Propellant 14 is usually provided in the boom 12 in the vicinity of the stabilizing fins.
  • a primer 15 is frequently losated in a rear end portion of the projectile.
  • Some known type of safety arming device is customary to preclude accidental firing of explosive charges in the gun or too close to the muzzle.
  • the propellant is frequently surrounded by a consumable or frangible casing 16 for convenience and safety in shipment.
  • a shaped charge 17 is fired by a fuze or primer 18 by an electrical impulse through a conductor 19 leading thereto from a piezoelectric fuze or generator 20 in a forward portion of the projectile, which fuze 20 functions in response to impact on a target.
  • This fuze 20 is mounted well forward of the nose cone in a stand-off sup- Patented Nov. 1, 1966 port 36 to provide adequate stand-01f distance of about 1 to 2 calibers for the fuze 2i) in front of the front end or base 'of the shaped charge cone.
  • this construction contemplates three aluminum ribs 37 for mounting a reflecting surface 20'.
  • These ribs 37 are of an angular width of about 13 degrees at their rear and radial outer ends and provide three circular sections of arc in the nose 21 of approximately 107 degrees each and allow adequate light rays such as those shown by the arrows 38 to enter the nose or cover 21 and be reflected by the curved mirror 22 onto the reflecting surface 20 and thence rearward in a generally axial direction through the lens 23 and into a detector or photocell 40 connected to a timed amplifier 25 through a conductor 26 to a fuze 27 for firing a primer 28 and explosive charge 29.
  • Firing charge 29 generates a gas which is discharged through the nozzle 30 whose axis passes through the gravitational center of the projectile and produces a thrust capable of changing the direction of projectile movement and therefore a change in its trajectory.
  • the medium by means of which this result is obtained is a spot of light or other radiation emitted or reflected by a target hereafter described.
  • the radiations emitted or reflected by a target pass through transparent arc portions 21 of the nose and after being reflected by mirror 22 are again reflected by mirror 20' through the lens 23 onto a mask 31 fixed with respect to the projectile for rotating with the projectile.
  • the construction of the mask is shown in FIG. 3 as having an aperture 32 located from the nozzle 30; the central axis of the nozzle is through the center of gravity along the arrow 33 in FIG. 3, which indicates the direction of gas discharge.
  • the image 35 of the target moves over the mask 31 and increases in size as the target is approached. Rotation of image 35 over the mask and near its center indicates a satisfactory direction for flight of the projectile and nothing happens until the target is hit.
  • the detector 40 senses the image and generates a signal to the fuze 27 which ignites the primer 28 firing charge 29 changing the direction of the projectile.
  • the detector mask 31 and timed amplifier 25 may be electrically tuned to exclude fallacious targets or those lacking a characteristic radiation of a probable target or the prob-able target may reflect only a particular radiation from an illuminator from a displaced vantage point or gun site.
  • the savings in material and greater accuracy resulting from a reduction in the length of the projectile is equivalent to a substantial portion of the head length of the Ross projectile.
  • This reduction in length is measured from the front or radially outer edge of curved mirror 22 to the forward or outer edge of the shaped charge 17.
  • these points are one and the same because the forward inner surface of the shaped charge is now the same as the forward edge of mirror 22 when the mirror 22 is contiguous to or abutting the shaped charge.
  • the mirror 22 should be a foil or other lightweight reflecting surface so as to offer no substantial impediment to the usual hot particles issuing in a narrow stream from a shaped charge.
  • a thrust from nozzle 30 is through the center of gravity of the projectile, and the center of pressure is in rear of the center of gravity a couple about a transverse axis provides a torque resulting in an angular displacement in the trajectory Where nozzle 30 functions, although this is too rapid to be caught by the human eye.
  • a battery or other electric generator 39 has been found desirable located in the boom, as shown.
  • the electronic amplifying apparatus has been found to be desirably placed in the adapter portion of the projectile.
  • a gun fired, fin stabilized projectile having rotation, said projectile comprising a casing attached to a nose, a major portion of the cross-sectional area of said nose being transparent to radiations from a target, an explosive charge carried by said projectile and adapted to fire said charge through a nozzle to produce a thrust transversely of the longitudinal axis of said projectile, electronic means operable to fire said charge in response to radiations from a target received through said transparent area, said electronic means including a detector of target radiations openable to fire said charge in response to such received radiations, means including a mask located in front of said detector, and rotatable with said projectile and provided with an aperture radially displaced from said longitudinal axis but substantially opposite said nozzle, said aperture being located a sufi'icient distance from said longitudinal axis to admit target radiations to said detector when said longitudinal axis is at a definite angle with the line of sight from said projectile to said target, a mirror located to direct target radiations to said detector through said mask aperture after
  • a projectile according to claim 1 in which said projectile has an adapter in rear of said explosive charge, a boom behind said adapter, and stabilizing fins behind said adapter, an electric battery located in said boom and a substantial portion of said electronic means being located within said adapter.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Description

GUN LAUNCHED TERMINAL GUIDED PROJECTILE Filed May 5, 1964 INVENTOR.
HENRY S. LIPINSKI ATTORNEYS United rates Patent 3,282,540 GUN LAUNCHED TERMINAL GUTDED PRGJEC'HLE Henry S. Lipinsici, Philadelphia, Pa., assignor to the United States of America as represented by the Secretary of the Army Filed May 5, 1964, Ser. No. 365,216 4 Claims. ((11. 244-316) The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment to me of any royalty thereon.
This invention relates to an improvement upon the gun launched terminal guided projectile disclosed in the prior application of Sidney Ross, Serial No. 831,443, filed August 3, 1959, and now Patent No. 3,072,055, dated January 8, 1963. An object of this invention is to utilize the projectile hardware more effectively for its guidance system permitting a shortening of the length of such a projectile thereby making it more stable and accurate in flight.
Specifically this has been accomplished by this invention in recognizing the desirability of having the forward inner cone surface of a shaped charge perform a new function prior to the initiation of the warhead by combining it with curved reflecting surface against which reflected light rays from the target entering the projectile nose are reflected onto a forward reflecting surface and thence to a target sensing device for determining the effectiveness of the projectile trajectory. As a result the length of the projectile has been shortened very substantially by an amount equal to the linear distance in said Ross patent between the reflecting curved mirror 22 and the forward portion of the shaped charge 17. This has been done by making the forward end portion of the shaped charge function as well as before but having such end portion curved in order that it may serve also as the curved mirror for reflecting the light rays entering through the nose.
Referring to the drawing:
FIG. 1 is a front end view of the projectile of this invention.
FIG. 2 is a longitudinal section through this projectile.
FIG. 3 illustrates a construction for the perforate mask described in the above mentioned Ross patent.
FIG. 2 shows an embodiment possessing the advantage of the Ross patent construction in an all electronic mechanism capable of quickly and automatically correcting an error in the direction of flight of a projectile in response to an image of the target seen and sensed by the projectile. In this drawing, the projectile parts are numbered using most of the numerals up to 31 to designate equivalent parts in both the Ross construction and the present. This projectile includes a head forward of an adapter 11 and a boom 12 to which are connected stabilizing fins 13 whereby only a slow rotation of about to 25 revolutions per second is needed according to custom with this type of fin stabilized projectile. Propellant 14 is usually provided in the boom 12 in the vicinity of the stabilizing fins. A primer 15 is frequently losated in a rear end portion of the projectile. Some known type of safety arming device is customary to preclude accidental firing of explosive charges in the gun or too close to the muzzle. The propellant is frequently surrounded by a consumable or frangible casing 16 for convenience and safety in shipment.
A shaped charge 17 is fired by a fuze or primer 18 by an electrical impulse through a conductor 19 leading thereto from a piezoelectric fuze or generator 20 in a forward portion of the projectile, which fuze 20 functions in response to impact on a target. This fuze 20 is mounted well forward of the nose cone in a stand-off sup- Patented Nov. 1, 1966 port 36 to provide adequate stand-01f distance of about 1 to 2 calibers for the fuze 2i) in front of the front end or base 'of the shaped charge cone. Instead of the all transparent nose of Ross this construction contemplates three aluminum ribs 37 for mounting a reflecting surface 20'. These ribs 37 are of an angular width of about 13 degrees at their rear and radial outer ends and provide three circular sections of arc in the nose 21 of approximately 107 degrees each and allow adequate light rays such as those shown by the arrows 38 to enter the nose or cover 21 and be reflected by the curved mirror 22 onto the reflecting surface 20 and thence rearward in a generally axial direction through the lens 23 and into a detector or photocell 40 connected to a timed amplifier 25 through a conductor 26 to a fuze 27 for firing a primer 28 and explosive charge 29. Firing charge 29 generates a gas which is discharged through the nozzle 30 whose axis passes through the gravitational center of the projectile and produces a thrust capable of changing the direction of projectile movement and therefore a change in its trajectory. The medium by means of which this result is obtained is a spot of light or other radiation emitted or reflected by a target hereafter described.
The radiations emitted or reflected by a target pass through transparent arc portions 21 of the nose and after being reflected by mirror 22 are again reflected by mirror 20' through the lens 23 onto a mask 31 fixed with respect to the projectile for rotating with the projectile. The construction of the mask is shown in FIG. 3 as having an aperture 32 located from the nozzle 30; the central axis of the nozzle is through the center of gravity along the arrow 33 in FIG. 3, which indicates the direction of gas discharge. As the projectile rotates the image 35 of the target moves over the mask 31 and increases in size as the target is approached. Rotation of image 35 over the mask and near its center indicates a satisfactory direction for flight of the projectile and nothing happens until the target is hit. However when the image is displaced far enough for the center of the mask to pass over aperture 32, the detector 40 senses the image and generates a signal to the fuze 27 which ignites the primer 28 firing charge 29 changing the direction of the projectile. The detector mask 31 and timed amplifier 25 may be electrically tuned to exclude fallacious targets or those lacking a characteristic radiation of a probable target or the prob-able target may reflect only a particular radiation from an illuminator from a displaced vantage point or gun site.
Among the advantages of this invention may be mentioned the savings in material and greater accuracy resulting from a reduction in the length of the projectile. The reduction in length is equivalent to a substantial portion of the head length of the Ross projectile. This reduction in length is measured from the front or radially outer edge of curved mirror 22 to the forward or outer edge of the shaped charge 17. In the present invention these points are one and the same because the forward inner surface of the shaped charge is now the same as the forward edge of mirror 22 when the mirror 22 is contiguous to or abutting the shaped charge. Preferably the mirror 22 should be a foil or other lightweight reflecting surface so as to offer no substantial impediment to the usual hot particles issuing in a narrow stream from a shaped charge. Because a thrust from nozzle 30 is through the center of gravity of the projectile, and the center of pressure is in rear of the center of gravity a couple about a transverse axis provides a torque resulting in an angular displacement in the trajectory Where nozzle 30 functions, although this is too rapid to be caught by the human eye. A battery or other electric generator 39 has been found desirable located in the boom, as shown. Likewise the electronic amplifying apparatus has been found to be desirably placed in the adapter portion of the projectile.
I claim:
1. In a gun fired, fin stabilized projectile having rotation, said projectile comprising a casing attached to a nose, a major portion of the cross-sectional area of said nose being transparent to radiations from a target, an explosive charge carried by said projectile and adapted to fire said charge through a nozzle to produce a thrust transversely of the longitudinal axis of said projectile, electronic means operable to fire said charge in response to radiations from a target received through said transparent area, said electronic means including a detector of target radiations openable to fire said charge in response to such received radiations, means including a mask located in front of said detector, and rotatable with said projectile and provided with an aperture radially displaced from said longitudinal axis but substantially opposite said nozzle, said aperture being located a sufi'icient distance from said longitudinal axis to admit target radiations to said detector when said longitudinal axis is at a definite angle with the line of sight from said projectile to said target, a mirror located to direct target radiations to said detector through said mask aperture after being reflected from a substantially axial reflecting surface, a shaped charge located forward of said explosive charge and provided with a piezoelectric impact fuze located at a forward end of said nose, and electrical connections from said fuze to said shaped charge for firing said shaped charge, the combination therewith of the improvement for shortening the overall length of said projectile and enhancing the stability and accuracy of said projectile, said improvement comprising said mirror being disposed adjacent a forward portion of said shaped charge, and said transparent portions of said nose constituting sectors bounded by radial supporting ribs having included equal obtuse angles.
2. A projectile according to claim 1 in which each of said included angles is about 107.
3. A projectile according to claim 1 in which said piezoelectric fuze is carried by a standoff support extending in front of a forward end of said shaped charge for a distance of between about 1 to 2 calibers.
4. A projectile according to claim 1 in which said projectile has an adapter in rear of said explosive charge, a boom behind said adapter, and stabilizing fins behind said adapter, an electric battery located in said boom and a substantial portion of said electronic means being located within said adapter.
References Cited by the Examiner UNITED STATES PATENTS 3,072,055 1/1963 Ross l0250 FOREIGN PATENTS 944,961 12/1963 Great Britain.
SAMUEL FEINBERG, Primary Examiner.
BENJAMIN A. BORCHELT, Examiner.
W. C. ROCH, Assistant Examiner.

Claims (1)

1. IN A GUN FIRED, FIN STABILIZED PROJECTILE HAVING ROTATION, SAID PROJECTILE COMPRISING A CASING ATTACHED TO A NOSE, A MAJOR PORTION OF THE CROSS-SECTIONAL AREA OF SAID NOSE BEING TRANSPARENT TO RADIATIONS FROM A TARGET, AN EXPLOSIVE CHARGE CARRIED BY SAID PROJECTILE AND ADAPTED TO FIRE SAID CHARGE THROUGH A NOZZLE TO PRODUCE A THRUST TRANSVERSELY OF THE LONGITUDINAL AXIS OF SAID PROJECTILE, ELECTRONIC MEANS OPERABLE TO FIRE SAID CHARGE IN RESPONSE TO RADIATIONS FROM A TARGET RECEIVED THROUGH SAID TRANSPARENT AREA, SAID ELECTRONIC MEANS INCLUDING A DETECTOR OF TARGET RADIATIONS OPERABLE TO FIRE SAID CHARGE IN RESPONSE TO SUCH RECEIVED RADIATIONS, MEANS INCLUDING A MASK LOCATED IN FRONT OF SAID DETECTOR, AND ROTATABLE WITH SAID PROJECTILE AND PROVIDED WITH AN APERTURE RADIALLY DISPLACED FROM SAID LONGITUDINAL AXIS BUT SUBSTANTIALLY OPPOSITE SAID NOZZLE, SAID APERTURE BEING LOCATED A SUFFICIENT DISTANCE FROM SAID LONGITUDINAL AXIS TO ADMIT TARGET RADIATIONS TO SAID DETECTOR WHEN SAID LONGITUDINAL AXIS IS AT A DEFINITE ANGLE WITH THE LINE OF SIGHT FROM SAID PROJECTILE TO SAID TARGET, A MIRROR LOCATED TO DIRECT TARGET RADIATIONS TO SAID DETECTOR THROUGH SAID MASK APERTURE AFTER BEING REFLECTED FROM A SUBSTANTIALLY AXIAL REFLECTING SURFACE, A SHAPED CHARGE LOCATED FORWARD OF SAID EXPLOSIVE CHARGE AND PROVIDED WITH A PIEZOELECTRIC IMPACT FUZE LOCATED AT A FORWARD END OF SAID NOSE, AND ELECTRICAL CONNECTIONS FROM SAID FUZE TO SAID SHAPED CHARGE FOR FIRING SAID SHAPED CHARGE, THE COMBINATION THEREWITH OF THE IMPROVEMENT FOR SHORTENING THE OVERALL LENGTH OF SAID PROJECTILE AND ENHANCING THE STABILITY AND ACCURACY OF SAID PROJECTILE, SAID IMPROVEMENT COMPRISING SAID MIRROR BEING DISPOSED ADJACENT A FORWARD PORTION OF SAID SHAPED CHARGE, AND SAID TRANSPARENT PORTIONS OF SAID SHAPED CHARGE, AND SAID BOUNDED BY RADIAL SUPPORTING RIBS HAVING INCLUDED EQUAL OBTUSE ANGLES.
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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3485461A (en) * 1968-04-26 1969-12-23 Us Army Firing control system for laser-guided projectiles
US3727553A (en) * 1965-12-06 1973-04-17 Hawker Siddeley Dynamics Ltd Fuze device with target detecting means
FR2425049A1 (en) * 1978-03-09 1979-11-30 Serat Ground-ground anti-tank missile - has target sensor to initiate orientation swivelling about centre of gravity using transverse acting powder charges
US4213394A (en) * 1972-12-13 1980-07-22 Motorola, Inc. Spin processing active optical fuze
FR2517818A1 (en) * 1981-12-09 1983-06-10 Thomson Brandt GUIDING METHOD TERMINAL AND MISSILE GUIDE OPERATING ACCORDING TO THIS METHOD
US4408735A (en) * 1979-11-09 1983-10-11 Thomson-Csf Process for piloting and guiding projectiles in the terminal phase and a projectile comprising means for implementing this process
FR2612288A1 (en) * 1985-07-29 1988-09-16 France Etat Armement Over-flight munition with tilting charge
US5037040A (en) * 1989-03-01 1991-08-06 Rheinmetall Gmbh Fin stabilized subammunition body
US5261629A (en) * 1989-04-08 1993-11-16 Rheinmetall Gmbh Fin stabilized projectile
US5275355A (en) * 1986-02-05 1994-01-04 Rheinmetall Gmbh Antitank weapon for combating a tank from the top
US5780766A (en) * 1996-04-30 1998-07-14 Diehl Gmbh & Co. Guided missile deployable as mortar projectile
US5788178A (en) * 1995-06-08 1998-08-04 Barrett, Jr.; Rolin F. Guided bullet
US7823510B1 (en) 2008-05-14 2010-11-02 Pratt & Whitney Rocketdyne, Inc. Extended range projectile
US7891298B2 (en) 2008-05-14 2011-02-22 Pratt & Whitney Rocketdyne, Inc. Guided projectile

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3072055A (en) * 1959-08-03 1963-01-08 Ross Sidney Gun launched, terminal guided projectile
GB944961A (en) * 1960-06-11 1963-12-18 Ludwig Bolkow Improvements relating to missiles with homing device

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3072055A (en) * 1959-08-03 1963-01-08 Ross Sidney Gun launched, terminal guided projectile
GB944961A (en) * 1960-06-11 1963-12-18 Ludwig Bolkow Improvements relating to missiles with homing device

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3727553A (en) * 1965-12-06 1973-04-17 Hawker Siddeley Dynamics Ltd Fuze device with target detecting means
US3485461A (en) * 1968-04-26 1969-12-23 Us Army Firing control system for laser-guided projectiles
US4213394A (en) * 1972-12-13 1980-07-22 Motorola, Inc. Spin processing active optical fuze
FR2425049A1 (en) * 1978-03-09 1979-11-30 Serat Ground-ground anti-tank missile - has target sensor to initiate orientation swivelling about centre of gravity using transverse acting powder charges
US4408735A (en) * 1979-11-09 1983-10-11 Thomson-Csf Process for piloting and guiding projectiles in the terminal phase and a projectile comprising means for implementing this process
FR2517818A1 (en) * 1981-12-09 1983-06-10 Thomson Brandt GUIDING METHOD TERMINAL AND MISSILE GUIDE OPERATING ACCORDING TO THIS METHOD
EP0081421A1 (en) * 1981-12-09 1983-06-15 Thomson-Brandt Armements Terminal guidance method and guided missile using it
US4568040A (en) * 1981-12-09 1986-02-04 Thomson-Brandt Terminal guidance method and a guided missile operating according to this method
FR2612288A1 (en) * 1985-07-29 1988-09-16 France Etat Armement Over-flight munition with tilting charge
US5275355A (en) * 1986-02-05 1994-01-04 Rheinmetall Gmbh Antitank weapon for combating a tank from the top
US5037040A (en) * 1989-03-01 1991-08-06 Rheinmetall Gmbh Fin stabilized subammunition body
EP0384965A3 (en) * 1989-03-01 1992-08-12 Rheinmetall GmbH Fin-stabilized subprojectile
US5261629A (en) * 1989-04-08 1993-11-16 Rheinmetall Gmbh Fin stabilized projectile
US5788178A (en) * 1995-06-08 1998-08-04 Barrett, Jr.; Rolin F. Guided bullet
US5780766A (en) * 1996-04-30 1998-07-14 Diehl Gmbh & Co. Guided missile deployable as mortar projectile
US7823510B1 (en) 2008-05-14 2010-11-02 Pratt & Whitney Rocketdyne, Inc. Extended range projectile
US7891298B2 (en) 2008-05-14 2011-02-22 Pratt & Whitney Rocketdyne, Inc. Guided projectile

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