US3866226A - Radar-augmented sub-target - Google Patents

Radar-augmented sub-target Download PDF

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Publication number
US3866226A
US3866226A US445153A US44515374A US3866226A US 3866226 A US3866226 A US 3866226A US 445153 A US445153 A US 445153A US 44515374 A US44515374 A US 44515374A US 3866226 A US3866226 A US 3866226A
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US
United States
Prior art keywords
target
drone
radar
targets
accordance
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US445153A
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English (en)
Inventor
Chris Benneche
James W Brochu
Jack S Conner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northrop Grumman Systems Corp
Original Assignee
Northrop Grumman Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Northrop Grumman Corp filed Critical Northrop Grumman Corp
Priority to US445153A priority Critical patent/US3866226A/en
Priority to SE7410562A priority patent/SE7410562L/xx
Priority to NL7412000A priority patent/NL7412000A/xx
Priority to CA209,347A priority patent/CA1010468A/en
Priority to GB4044774A priority patent/GB1443626A/en
Priority to FR7434844A priority patent/FR2262280B3/fr
Priority to IT53607/74A priority patent/IT1023077B/it
Priority to IL45876A priority patent/IL45876A0/xx
Priority to BE149727A priority patent/BE821300A/xx
Priority to DE19742458607 priority patent/DE2458607A1/de
Application granted granted Critical
Publication of US3866226A publication Critical patent/US3866226A/en
Priority to JP50023785A priority patent/JPS50122192A/ja
Assigned to NORTHROP CORPORATION, A DEL. CORP. reassignment NORTHROP CORPORATION, A DEL. CORP. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: NORTHROP CORPORATION, A CA. CORP.
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/26—Teaching or practice apparatus for gun-aiming or gun-laying
    • F41G3/2616—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device
    • F41G3/2622—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device for simulating the firing of a gun or the trajectory of a projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/001—Devices or systems for testing or checking
    • F41G7/002—Devices or systems for testing or checking target simulators
    • F41G7/003—Devices or systems for testing or checking target simulators for seekers using radio waves
    • 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
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures

Definitions

  • ABSTRACT A remote controlled drone aircraft carrying radaraugmented targets or so-called "sub-targets" which are rocket powered and can be individually launched from the drone when at the proper place and time to provide training for crews firing a missile at the target, and to provide a target for missile quality assurance and lot acceptance testing.
  • the targets are extremely simple and economical, comprising only a symmetrical plastic body with fixed tail surfaces, and a cylindrical rocket motor inside.
  • a removable nose cover initially masks the radar reflector of each target except one until ready for use.
  • the present invention relates to targets and target systems, and more particularly, to an expendable radaraugmented sub-target launched from an airborne remote-controlled drone aircraft, for use in weapon training and missile testing for example.
  • Radio-controlled drone targets have been launched from the ground or from piloted aircraft for gun or missile testing and gun crew training, these drones being parachute-recovered and salvaged for re-use if not destroyed by weapon hits or crash landings. Also, targets have been towed from an aircraft at the end of a long tow cable while missiles are fired at the target. Both these methods are wasteful and unsuitable in several respects. Recovery, rebuilding and replacement of the drones is expensive, while automatic loss of the towed target and its long tow cable is also expensive. Further, in the case of the towed target, an angle of attack of the weapon from a head-on direction and up to a prescribed angle away from head-on is prevented due to the position occupied by the towing craft.
  • Another object of this invention is to provide more than one target carried by a drone aircraft, together with means causing the fired weapon to track only the desired single target.
  • a further object is to provide a high speed target simulating present-day high velocity weapons, and a target which will be well away from its launching drone at missile intercept, thus avoiding the necessity of evasive launching drone maneuvers following target launch.
  • our invention comprises a small, simple rocket type oftarget carrying radar reflection augmenting means, and support fitting members on the exterior of the target body for supporting it from a launching drone prior to ignition of the target rocket motor.
  • the target is preferably Wingless but has directional tail fins and preferably has means for spinning itself during its flight after launching.
  • a drone type target carrier is used, with provisions for carrying at least two such targets, provisions for individually launching the targets, means for adequately masking the radar augmenting means of each target except one, and means for removing the respective masking means at a desired chosen time.
  • FIG. 1 is a perspective view of a drone aircraft showing two wing-tip mounted radar-augmented sub-targets each adapted to be launched and fly for a predetermined time as a practice target.
  • FIG. 2 is a front view of the left half of the drone showing details of the sub-target mounting.
  • FIG. 3 is a side inboard profile view of the sub-target.
  • FIG 4 is a cross-section view of the sub-target, viewed as indicated by broken line 4-4 in FIG. 3, showing certain longitudinal reflectors therein.
  • FIG. 4A is a partial perspective view of the structure of FIG. 4 with the outer skin removed, showing more clearly the longitudinal reflectors.
  • FIG. Si is a left side view of the front ofone of the subtargets showing a masking nose cover thereon.
  • FIG. 6 is a partial cross-sectional view taken as indicated by broken line 6-6 in FIG. 5, showing details of the removable nose cover.
  • FIG. 7 is a perspective sketch showing the top shell of the nose cover.
  • FIG. 8 is a perspective sketch showing the bottom shell of the nose cover.
  • a drone aircraft 1 having a fuselage 2, wing 4, tail surfaces 5 and jet engine inlet 6 carries a sub-target 7 at each tip of the wing 4.
  • These are sometimes called subtargets by workers in the art because aircraft having the same or similar characteristics and size of the present drone 1 have normally been used as targets for missile and gun training.
  • the sub-targets 7 are herein referred to as both targets and sub-targets.
  • each sub-target 7 carries two slippers 9 on its top side which slide in a rail 10 attached to the underside of the wing 4 and usually extending ahead of and to the rear of the wing 4.
  • Rail 10 may be curved slightly downward or upward to match the chordwise wing contour-or to launch the target 7 in a slight initial downward or upward direction.
  • Such wing-tip mounted arrangement may of course be modified.
  • FIG. 3 also shows the internal arrangement of each ofthe targets 7.
  • a radar reflector 12 such as a Luneberg lens for example, supported by lens mounting structure 14 which is preferably curved to match the rear side: of the lens 12.
  • the central section is mostly occupied by an inner body tube 15 shaped to contain a conventional fast burning rocket motor 16 having an electrical ignitor l7, and an exhaust nozzle 19.
  • the tail surfaces 18 are preferably canted slightly as is known in the art to provide spin to the target 7 after launch.
  • FIG. 2 shows the trailing edges 21 of the tail canted slightly to one side of the leading edges. Other spinning means can be used if desired, such as canted exhaust nozzles of the rocket motor 16.
  • a special unique radar reflective means is provided between the tube 15 and the outer skin 20.
  • This comprises circumferential reflectors 24 which may be of aluminum acting also as support bulkheads, and a plastic foam filler 25 contains pairs of longitudinal strip reflectors 26 (see FIGS. 4 and 4A) mounted at right angles to each other.
  • the reflectors 24 and 26 thus act as scintillators during target flight.
  • This radar reflective means does not affect incident electromagnetic energy from the front of the target, but when the target is spinning and flying alone after launching, pulsed radar re flections are caused both by the circumferential and longitudinal reflectors 24 and 26, especially when the incident radiation is at an angle to the target line of flight.
  • the firing batteries on the ground can locate and track the drone I by means of the Luneberg lens 12. Then when the missile or weapon is fired, the ground controller of the drone l is notified and remotely sends a radio signal to ignite the first target motor, and the target launches itself at high acceleration from the drone 1.
  • the targettracking radar now tracks only the launched target, since the target has high acceleration (23 g for example) and since a mask, to be described next, is fitted over the nose of the unfired target to cover its Luneberglens.
  • the target is usually launched in a slightly upward direction, say at 13 to l7 to the horizon. Assuming an acceleration of about 23 g and a motor burning time of about 1.6 seconds, the trajectory of the target is nearly horizontal through its first seconds of flight.
  • one of the targets 7 When the two targets 7 are carried by the single drone 1, one of the targets has a mask 27 in the form of a non-radio-transparent cover over the target nose, as shown in FIGS. 1 and 5.
  • the left-hand target is the first to be launched, and therefore the nose 11a of the right-hand target has the mask 27 installed.
  • the mask 27 comprises an upper half-shell 29 and a lower half-shell 30 molded and assembled in a size to be snugly slipped over the target nose and be automatically jettisoned upon command.
  • a first collar 31 is bonded to the lower edge of the upper half-shell 29 and a second collar 32 is bonded to the lower half-shell 30 at a position spaced parallel to the upper edge thereof.
  • An encircling pastic foam pad 34 is provided between the edge of the lower half-shell 30 and the collars 31 and 32.
  • a pyrofuse wire or preferably several such wires 35 which are of suitable pyrotechnic material adapted to burn rapidly when ignited.
  • a firing squib 36 with ignition leads 37 is positioned at one end of the pyrofuse wires 35 in igniting contact therewith.
  • the wires are wound around the squib 36 and tiedor taped thereto.
  • the squib leads 37 come from a squib firing circuit 39 which may be in the target 7 but is preferably in the drone 1 so that it is not expended with the target 7.
  • a plastic film strip 40 is placed (without bonding) over the pad 34 and wires 35 on one side, and bonded on the outside only to both the adjacent collars 31 and 32 as shown in FIG. 6, thus holding the nose cover together.
  • the shells may be made of fiberglass and spray-coated with aluminum 41 on the inside, thus forming the mask 27 when installed over the Luneberg lens reflector 12.
  • the foam pad 34 is flexible and preferably somewhat resilient so that the mask 27 will easily stay on the nose during handling and flight until jettisoned.
  • the drone 1 After the first target 7 has been launched and fired upon, the drone 1 will continue being flown by the controller until the gun crew having practice is ready to fire at another target.
  • the controller then brings the drone l to the desired altitude, position and heading for the second tracking procedure, in the meantime having actuated the squib firing circuit 39 by remote command radio signal, which is well knownin the art.
  • the squib 36 As the squib 36 is fired, the pyrofuse wires 35 burn or melt apart the plastic film strip 40, thus separating the shells 29 and 30 and letting them blow or fall away.
  • this second target is tracked, and when a missile is fired at it, the controller launches the second target to be followed and hit by the missile. After this, the drone l is flown back to its take-off site and recovered, to be used again by loading two more targets 7 onto the rails 10.
  • a conventional type of drone tracking system is usually used to inform the drone controller on the ground.
  • the tracking signals from the drone I and the remote flight control signals to the drone are indicated by the arrow 42 in FIG. 1.
  • smoke pulses from the drone can be employed to aid in tracking, and in fact smoke producing means can be installed in some targets 7 in the spaces where the plastic foam 25 is normally placed, if desired.
  • the launching of the target 7 from the drone 1 has been described as following the instant of missile firing.
  • the target 7 may be launched prior to missile firing.
  • the present targets 7 may of course be made in various sizes and with rocket engines of various thrusts.
  • the target is less than five feet long, weighs about 33 pounds, and has a 2.75 inch rocket motor with a thrust of about 760 pounds, which achieves a maximum speed of Mach 1.4 at 10,000 feet altitude.
  • a 7-inch Luneberg lens is provided.
  • An airborne target for launching from a carrier aircraft comprising:
  • a rocket motor extending along the center of said body with means for igniting said motor at a chosen time to launch said target from said carrier aircraft;
  • additional radar reflective means in said body around said motor, said additional means including a plurality of scintillators.
  • Apparatus in accordance with claim 1 including means on said target for spinning it about its flight axis after launching.
  • said additional reflective means comprises lightweight metal circumferential rings extending from said motor to the outer extent of said body.
  • said additional reflective means comprises lightweight metal longitudinal strips located in the annular space between said motor and the outer extent of said body.
  • Apparatus in accordance with claim 1 including removable nose cover means surrounding the front and sides of said radar reflection augmenting means and forming a radar mask, and remote control means operatively connected to said cover means to separate the latter from said target in response to actuation of said remote control means.
  • said nose cover means comprises two half-shells, a separable strip normally connecting said half-shells together, and pryrotechnic means ignitable by said remote control means and extending along said separable strip, said pyrotechnic means structured to burn through and separate said strip, whereby said nose cover means is jettisoned 9.
  • Target means comprising:
  • a rocket motor in each said target being individually ignitable during drone flight for launching said targets individually from said drone.
  • each said target has additional radar reflective means therein and means for spinning said target when launched, said additional reflective means producing pulsed reflections as said target spins.
  • Apparatus in accordance with claim 9 including removable nose cover means forming a radar mask surrounding the front and sides of the radar reflection augmenting means in only one of said targets, and remotecontrol means operatively connected to said cover means to separate the latter from said one target in response to actuation of said remote control means.
  • Target means comprising:
  • removable cover means forming a radar mask effectively surrounding the reflection augmenting means in each of said targets except one, and individual control means operatively connected respectively to said cover means to separate the latter from its respective target in response to actuation of its said control means.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US445153A 1974-02-25 1974-02-25 Radar-augmented sub-target Expired - Lifetime US3866226A (en)

Priority Applications (11)

Application Number Priority Date Filing Date Title
US445153A US3866226A (en) 1974-02-25 1974-02-25 Radar-augmented sub-target
SE7410562A SE7410562L (xx) 1974-02-25 1974-08-20
NL7412000A NL7412000A (nl) 1974-02-25 1974-09-10 Versterkt radar-subdoel.
CA209,347A CA1010468A (en) 1974-02-25 1974-09-13 Radar-augmented sub-target
GB4044774A GB1443626A (en) 1974-02-25 1974-09-17 Radar-augmented sub-target
FR7434844A FR2262280B3 (xx) 1974-02-25 1974-10-16
IT53607/74A IT1023077B (it) 1974-02-25 1974-10-17 Persaglio da esercotazione ad azione efficace radar aumentata
IL45876A IL45876A0 (en) 1974-02-25 1974-10-18 Radar-augmented sub-target
BE149727A BE821300A (fr) 1974-02-25 1974-10-21 Cible secondaire pour radar
DE19742458607 DE2458607A1 (de) 1974-02-25 1974-12-11 Flugziel mit radarverstaerkung
JP50023785A JPS50122192A (xx) 1974-02-25 1975-02-25

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US445153A US3866226A (en) 1974-02-25 1974-02-25 Radar-augmented sub-target

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US3866226A true US3866226A (en) 1975-02-11

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US445153A Expired - Lifetime US3866226A (en) 1974-02-25 1974-02-25 Radar-augmented sub-target

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US (1) US3866226A (xx)
JP (1) JPS50122192A (xx)
BE (1) BE821300A (xx)
CA (1) CA1010468A (xx)
DE (1) DE2458607A1 (xx)
FR (1) FR2262280B3 (xx)
GB (1) GB1443626A (xx)
IL (1) IL45876A0 (xx)
IT (1) IT1023077B (xx)
NL (1) NL7412000A (xx)
SE (1) SE7410562L (xx)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0235972A1 (en) * 1986-02-10 1987-09-09 The Minister Of National Defence Of Her Majesty's Canadian Government Radar augmentor assembly
US4700190A (en) * 1979-10-17 1987-10-13 The United States Of America As Represented By The Secretary Of The Air Force Missile decoy radar cross section enhancer
FR2687774A1 (fr) * 1989-02-24 1993-08-27 Dornier Gmbh Cible factice.
US5317163A (en) * 1990-02-26 1994-05-31 Dornier Gmbh Flying decoy
US20050000384A1 (en) * 2002-10-17 2005-01-06 Nisim Hazan Soft removable thermal shield for a missile seeker head
US20050128136A1 (en) * 2003-12-12 2005-06-16 Wittenberg Peter S. System and method for radar detection and calibration
US7333044B1 (en) * 2006-09-25 2008-02-19 The United States Of America As Represented By The Secretary Of The Army Rocket-powered sensor target assembly
ES2306542A1 (es) * 2004-05-12 2008-11-01 Jose Manuel Bonilla Sanchez Blanco aereo.
CN113955070A (zh) * 2021-11-18 2022-01-21 北京金朋达航空科技有限公司 无人机
US20220260675A1 (en) * 2021-02-18 2022-08-18 The United States Of America, As Represented By The Secretary Of The Navy Ground based radar cross section measurement of countermeasures
US11726169B1 (en) * 2019-03-14 2023-08-15 The United States Of America, As Represented By The Secretary Of The Navy System for augmenting 360-degree aspect monostatic radar cross section of an aircraft

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE416233B (sv) * 1976-10-04 1980-12-08 Saab Scania Ab Anordning vid en laserljusreflektorenhet som er inrettad att utanpaliggande infestas till ett luftfartygs berande konstruktion
DE3445387A1 (de) * 1984-12-13 1986-06-26 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Signatur-, sensor- und transmittertraeger zur zieldarstellung und gegenmessungen fuer boden/luft- bzw. luft/luft-systeme
DE3621699A1 (de) * 1986-06-27 1988-01-14 Tech Mathematische Studiengese Radarrueckstrahlvorrichtung fuer flugkoerper
RU2544908C1 (ru) * 2013-09-09 2015-03-20 Открытое акционерное общество "Корпорация космических систем специального назначения "Комета" Космический аппарат для калибровки радиолокационной станции по величине эффективной поверхности рассеяния
RU2570126C2 (ru) * 2014-04-11 2015-12-10 Открытое акционерное общество "Корпорация космических систем специального назначения "Комета" Юстировочно-калибровочный космический аппарат
RU2640167C1 (ru) * 2016-07-08 2017-12-26 Акционерное общество "Корпорация космических систем специального назначения "Комета" Многофункциональный космический аппарат
RU2769455C1 (ru) * 2020-10-26 2022-03-31 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Имитатор воздушных целей

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3230531A (en) * 1961-11-24 1966-01-18 Gen Electric Broadband streamlined radar reflector
US3283324A (en) * 1964-06-29 1966-11-01 Hayes Internat Corp Means for changing the radar signature of aerial vehicles
US3334345A (en) * 1965-06-02 1967-08-01 Micronetics Inc Passive radar target augmentor
US3413636A (en) * 1967-01-31 1968-11-26 Philip N. Migdal Radar cross section augmenter

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3230531A (en) * 1961-11-24 1966-01-18 Gen Electric Broadband streamlined radar reflector
US3283324A (en) * 1964-06-29 1966-11-01 Hayes Internat Corp Means for changing the radar signature of aerial vehicles
US3334345A (en) * 1965-06-02 1967-08-01 Micronetics Inc Passive radar target augmentor
US3413636A (en) * 1967-01-31 1968-11-26 Philip N. Migdal Radar cross section augmenter

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4700190A (en) * 1979-10-17 1987-10-13 The United States Of America As Represented By The Secretary Of The Air Force Missile decoy radar cross section enhancer
EP0235972A1 (en) * 1986-02-10 1987-09-09 The Minister Of National Defence Of Her Majesty's Canadian Government Radar augmentor assembly
US4989007A (en) * 1986-02-10 1991-01-29 Her Majesty In Right Of Canada, As Represented By The Minister Of National Defence Passive radar augmented projectile (PRAP)
FR2687774A1 (fr) * 1989-02-24 1993-08-27 Dornier Gmbh Cible factice.
US5317163A (en) * 1990-02-26 1994-05-31 Dornier Gmbh Flying decoy
US6854393B2 (en) * 2002-10-17 2005-02-15 Rafael-Armament Development Authority Ltd. Soft removable thermal shield for a missile seeker head
US20050000384A1 (en) * 2002-10-17 2005-01-06 Nisim Hazan Soft removable thermal shield for a missile seeker head
US20050128136A1 (en) * 2003-12-12 2005-06-16 Wittenberg Peter S. System and method for radar detection and calibration
US6927725B2 (en) * 2003-12-12 2005-08-09 The Boeing Company System and method for radar detection and calibration
ES2306542A1 (es) * 2004-05-12 2008-11-01 Jose Manuel Bonilla Sanchez Blanco aereo.
US7333044B1 (en) * 2006-09-25 2008-02-19 The United States Of America As Represented By The Secretary Of The Army Rocket-powered sensor target assembly
US11726169B1 (en) * 2019-03-14 2023-08-15 The United States Of America, As Represented By The Secretary Of The Navy System for augmenting 360-degree aspect monostatic radar cross section of an aircraft
US20220260675A1 (en) * 2021-02-18 2022-08-18 The United States Of America, As Represented By The Secretary Of The Navy Ground based radar cross section measurement of countermeasures
CN113955070A (zh) * 2021-11-18 2022-01-21 北京金朋达航空科技有限公司 无人机
CN113955070B (zh) * 2021-11-18 2022-08-30 北京金朋达航空科技有限公司 无人机

Also Published As

Publication number Publication date
IT1023077B (it) 1978-05-10
GB1443626A (en) 1976-07-21
DE2458607A1 (de) 1975-08-28
BE821300A (fr) 1975-04-21
NL7412000A (nl) 1975-08-27
FR2262280A1 (xx) 1975-09-19
CA1010468A (en) 1977-05-17
IL45876A0 (en) 1975-02-10
JPS50122192A (xx) 1975-09-25
FR2262280B3 (xx) 1977-07-22
SE7410562L (xx) 1975-08-26

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AS Assignment

Owner name: NORTHROP CORPORATION, A DEL. CORP.

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:NORTHROP CORPORATION, A CA. CORP.;REEL/FRAME:004634/0284

Effective date: 19860516