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EP0466499A1 - Geschoss mit einer Überwachungsanlage - Google Patents

Geschoss mit einer Überwachungsanlage Download PDF

Info

Publication number
EP0466499A1
EP0466499A1 EP91306333A EP91306333A EP0466499A1 EP 0466499 A1 EP0466499 A1 EP 0466499A1 EP 91306333 A EP91306333 A EP 91306333A EP 91306333 A EP91306333 A EP 91306333A EP 0466499 A1 EP0466499 A1 EP 0466499A1
Authority
EP
European Patent Office
Prior art keywords
capsule
projectile
payload
spin
camera
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.)
Withdrawn
Application number
EP91306333A
Other languages
English (en)
French (fr)
Inventor
Robert John Downes
John Edwin Scammell
Michael George Dr. Slade
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.)
DELTATEK Ltd
BAE Systems Global Combat Systems Munitions Ltd
Original Assignee
DELTATEK Ltd
Royal Ordnance PLC
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 DELTATEK Ltd, Royal Ordnance PLC filed Critical DELTATEK Ltd
Publication of EP0466499A1 publication Critical patent/EP0466499A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/54—Spin braking means
    • 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
    • F42B12/365—Projectiles transmitting information to a remote location using optical or electronic means

Definitions

  • the present invention relates to projectile surveillance apparatus.
  • the present invention is concerned with surveying the landscape by firing from a gun or other conventional propulsion means over the area to be observed a projectile carrying an arrangement for recording and transmitting images to a remote receiver.
  • a surveillance apparatus comprises a projectile for firing toward a region to be surveyed, housed within the body of the projectile a payload capsule and, incorporated within the projectile, an expulsion charge, the projectile body having a construction which splits when the expulsion charge is initiated permitting the payload capsule to be ejected from the body, the payload body having means to retard its forward motion and carrying a surveillance camera and a video transmitter, the camera being arranged so as to survey, in operation, the region in front of the capsule and to provide its output as an input signal to the transmitter the projectile and/or the capsule being provided with means for substantially eliminating the spin of the capsule thereby allowing the picture recorded by the camera to be substantially stabilised.
  • a video imaging projectile which consists of an artillery shell incorporating a single photodiode that looks through a lucite window in the shell. As the shell passes over the area of interest the scene information detected by the spinning photodiode is digitized and transmitted by radio link to the ground where the image is reconstructed on a computer.
  • the apparatus according to the present invention is substantially different from the said projectile of the said publication and shows the following unexpected advantages.
  • the camera carried on the capsule is able to provide to the transmitter real time stabilised picture signals of the scene in front of the camera over a relatively long surveillance period in a selected, localised region at a relatively low height, eg. 500m and less, above the ground.
  • the signals transmitted to a remote receiver can be displayed on a suitable display to which the receiver is connected without the need for substantial signal processing (other than as normally employed to convert a transmitted carrier signal into a display picture) either at the transmitter or receiver end.
  • the signals produced by the detector of the projectile of the said publication would require signal processing to be carried out at both the transmitter and receiver ends in order to produce a stabilised picture, the signal processing would be required to register the precise trajectory shape and spin rate of the projectile. Since these parameters can be affected by such environmental factors as wind and rain causing signal processing errors, the received picture signal may be adversely affected. Because of inevitable delays by the signal processing the picture signal displayed is not a real-time representation of the scene surveyed as the projectile carrying the spinning detector will normally travel rapidly over the surveyed area at an appreciable height above the ground the period of surveillance of a given target region of interest may be unacceptably low.
  • the expulsion charge may be arranged to be initiated by a fuze, which may be a conventional time fuze which operates after a set period of time after firing of the projectile the time being pre-determined to select the area of ground to be surveyed by the apparatus.
  • a fuze which may be a conventional time fuze which operates after a set period of time after firing of the projectile the time being pre-determined to select the area of ground to be surveyed by the apparatus.
  • the said means for substantially eliminating the spin of the capsule may comprise a spring loaded fin assembly providing in operation fins projecting laterally with respect to the axis of spin of the capsule - thereby resisting the spin.
  • the fins may have a concave curvature facing the targential direction of spin to assist the retarding action.
  • the payload capsule may itself incorporate an inner capsule which is adapted to be separated from the payload capsule and its retarding means comprising parachute and fins.
  • the inner capsule may itself have a parachute attached thereto by a flexible coupling further to retard its forward motion and a spring loaded fin assembly providing in operation further laterally projecting fins to retard the spin of the inner capsule.
  • the inner capsule carries the camera, transmitter and their power source which may comprise a conventional thermal or lithium battery. The battery may be arranged to be activated when the payload capsule is separated from the projectile so that after the flight of the inner capsule has been stabilised following its separation from the payload capsule the camera and transmitter are operational.
  • the inner capsule may be separated from the payload capsule by a secondary separation charge.
  • the secondary separation charge may be initiated a pre-determined time after the aforementioned (primary) separation charge by a conventional pyrotechnic delay ignition train between the two charges.
  • the parachute attached to the inner capsule may advantageously be larger than that attached to the payload capsule. If a single large parachute is applied from a capsule travelling at the projectile forward speed there is a significant risk of the parachute being ripped and/or tangled. By retarding the inner capsule in two stages in the preferred form as described this risk is avoided.
  • the said camera may comprise a conventional television camera operating in the visible and/or infra-red spectral region (ie. detecting either a visual or thermal image of the surveyed region). It may for example comprise a known charge coupled device (CCD) photoconductive array.
  • the video transmitter arranged to transmit electromagnetic signals corresponding to the detected picture may operate in any of the conventional television frequencies.
  • a conventional television receiver receiving pictures transmitted by the transmitter may be at a remote command site and operated and observed by a person who is in radio contact with persons who are in different locations. Alternatively, the persons could carry man-portable receiver packs to observe pictures of the surveyed region themselves.
  • a plurality of projectiles each comprising apparatus according to the present invention may be deployed to survey a given region. It may be advantageous to transmit the signals from the various transmitters on such projectiles at different frequencies so that the origin of the received signal can be designated. This may be achieved by incorporating within each apparatus a device permitting the transmitter to operate at one of a number of frequencies and a switch for pre-selecting the frequency. The switch may be conveniently be set electrically by applying a suitable current pulse to contact studs on the outside of the projectile body.
  • the said projectile may comprise a carrier shell for firing from a howitzer, eg. having one of the widely used calibres, eg. 155mm, 105mm, 4.5 inches or 76mm.
  • a carrier shell for firing from a howitzer eg. having one of the widely used calibres, eg. 155mm, 105mm, 4.5 inches or 76mm.
  • it may comprise a mortar projectile for firing from a conventional mortar tube.
  • the packaging of the various components of the apparatus within the projectile need to be "gun hardened” so that they can withstand the setback forces produced upon the projectile being fired.
  • the apparatus may comprise a lens, video camera, thermal battery and transmitter, all of which have been encapsulated in suitable packs to ruggedise them.
  • the projectile is an artillery shell this may carry a range extending device such as a base bleed unit to extend its normal range by reducing its base drag.
  • a range extending device such as a base bleed unit to extend its normal range by reducing its base drag.
  • Such a unit if employed is preferably of a known screw-in type.
  • the projectile body when split by the expulsion charge may be split by blowing out its base bleed unit. Alternatively, it may be split at a predefined zone of weakness elsewhere on its surface.
  • the expulsion charge may comprise known solid propellant charges, eg. similar to those used in gas operated actuators.
  • Figure 1 is a cross-sectional side elevation of a surveillance shell embodying the present invention.
  • Figure 2 is a schematic flow diagram illustrating the various stages of operation of the shell shown in Figure 1.
  • the shell shown in Figure 1 has a body 1 carrying a driving band 2 and has at its front end a mechanical time fuze 3 and its rear end a base bleed unit 5 attached by a screw thread joint 7 to the side of the body 1.
  • the base bleed unit 5 is provided to extend the normal range of the shell body 1. Housed inside the body 1 is an expulsion payload tube 9 and its contents together with a drag parachute 11 for the payload tube 9 packed inside the space between the rear end of the tube 9, the inside wall of the body 1 and the wall of the base bleed unit 5.
  • the drag parachute 11 is attached by a flexible coupling 13 to a rear end cap 14 fitted on the payload tube 9.
  • the end cap 14 forms an inner tubular sleeve 16 within the tube 9 which has a shear ring 18 providing a zone of weakness in the end cap 14.
  • a main parachute 15 is packed inside the sleeve 16 in front of the rear portion of the end cap 14.
  • An inner tube 21 is provided inside the payload tube 9 in front of the parachute 15.
  • the rear end of the inner tube 21 is formed by a housing 17 to which the main parachute 15 is attached by a flexible coupling 19.
  • the housing 17 houses a container 20 for a thermal battery.
  • the inner tube 21 incorporates a video camera 23 located in front of and electrically connected to and arranged to provide an input to a uhf (video) transmitter 25.
  • a lens 26 is fitted in front of the camera 23.
  • the payload tube 9 on its outer side wall at its front end, carries a fin assembly 27 comprising a set of four spring-loaded retarder fins and the housing 17 carries on its outer side wall a fin assembly 29 comprising a set of two spring-loaded retarder fins.
  • the fin assembly 29 and the battery housing 17 attached to it form a rear closure for the inner tube 21.
  • the front end of the payload tube 9 is in the form of a forward facing projection 31 having on its outer surface a forward facing recess 33 and on its inner surface a rearward facing recess 35.
  • the rearward facing recess 35 houses a secondary expulsion charge 37 and the forward facing recess 33 receives a primary expulsion charge 39 also attached to and arranged to be energised by the fuze 3.
  • the charges 37, 39 are linked by a delay pyrotechnic train 38.
  • the operation sequence of the surveillance shell shown in Figure 1 is illustrated in Figure 2.
  • the shell is fired in a conventional manner from a howitzer 49. It is spun during firing by its driving band 2.
  • the spinning shell is illustrated at this first stage by symbol A in Figure 2.
  • the fuze 3 operates to initiate the primary expulsion charge 39 which expels the payload tube 9 from the body 1 by blowing out the base bleed unit 5.
  • This second stage is illustrated by symbol B in Figure 2.
  • the fins of the assembly 27 are allowed to open at the second stage and these fins retard the spin of the tube 9.
  • the drag parachute 11 is allowed to open and the tube 9 with the parachute 11 retarding its forward motion of is illustrated at the stage illustrated by symbol C in Figure 2.
  • the thermal battery (not shown) inside the housing 17 is activated at stage B.
  • the battery begins to energise electrically the appliances connected to it, namely the camera 23 and transmitter 25 and by the time the inner tube 21 reaches stage E the camera 23 and transmitter 25 are operational allowing radio signals and describing the picture of a target T observed by the camera 23 to be transmitted by the transmitter 25 to a remote receiver (not shown).

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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)
  • Closed-Circuit Television Systems (AREA)
  • Studio Devices (AREA)
EP91306333A 1990-07-13 1991-07-12 Geschoss mit einer Überwachungsanlage Withdrawn EP0466499A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9015445 1990-07-13
GB909015445A GB9015445D0 (en) 1990-07-13 1990-07-13 Projectile surveillance apparatus

Publications (1)

Publication Number Publication Date
EP0466499A1 true EP0466499A1 (de) 1992-01-15

Family

ID=10679050

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91306333A Withdrawn EP0466499A1 (de) 1990-07-13 1991-07-12 Geschoss mit einer Überwachungsanlage

Country Status (3)

Country Link
EP (1) EP0466499A1 (de)
GB (2) GB9015445D0 (de)
IL (1) IL98819A0 (de)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5432546A (en) * 1992-12-21 1995-07-11 Enel Company Weapon impact assessment system
FR2726643A1 (fr) * 1994-11-04 1996-05-10 Giat Ind Sa Dispositif d'observation d'une zone de terrain
FR2754052A1 (fr) * 1996-10-02 1998-04-03 Diehl Gmbh & Co Projectile d'exercice balistique
EP0800052A3 (de) * 1996-04-04 1998-10-28 Diehl Stiftung & Co. Aufklärungseinrichtung
US7283156B1 (en) * 2002-09-12 2007-10-16 Lockheed Martin Corporation Airborne imaging system and method
US7631601B2 (en) * 2005-06-16 2009-12-15 Feldman Paul H Surveillance projectile
JP2010085040A (ja) * 2008-10-01 2010-04-15 Ihi Aerospace Co Ltd 着弾観測システム
EP1761431A4 (de) * 2004-03-15 2010-09-22 Georgia Tech Res Inst Geschoss und system zur bereitstellung von luft-zu-oberfläche-erkennung
CN101949669A (zh) * 2010-08-10 2011-01-19 吉林保利科技中试有限公司 60毫米迫击炮微型电视侦察弹
CN102162712A (zh) * 2010-12-20 2011-08-24 吉林保利科技中试有限公司 63-1式60毫米迫击炮照明弹
KR101305202B1 (ko) 2012-03-23 2013-09-12 국방과학연구소 다중 기폭관
WO2014173916A1 (de) * 2013-04-24 2014-10-30 Rheinmetall Waffe Munition Gmbh Drallstabilisiertes leuchtgeschoss
GB2517448A (en) * 2013-08-20 2015-02-25 Bae Systems Plc Frangible munition
GB2517445A (en) * 2013-08-20 2015-02-25 Bae Systems Plc Illumination Munition
FR3011919A1 (fr) * 2013-10-15 2015-04-17 Nexter Munitions Dispositif de freinage en rotation d'une enveloppe d'une charge utile, et projectile gyrostabilise equipe d'un tel dispositif
US9778004B2 (en) 2013-08-20 2017-10-03 Bae Systems Plc Smoke payload apparatus
US9784544B2 (en) 2013-08-20 2017-10-10 Bae Systems Plc Frangible munition
US9797698B2 (en) 2013-08-20 2017-10-24 Bae Systems Plc Common carrier munition
US10030953B2 (en) 2013-08-20 2018-07-24 Bae Systems Plc Illumination munition
US10633091B2 (en) 2015-01-29 2020-04-28 Scope Technologies Holdings Limited Accident monitoring using remotely operated or autonomous aerial vehicles
WO2021034424A2 (en) 2019-07-12 2021-02-25 Leonardo Electronics Us Inc. Method and system for electronic warfare obscuration and suppression of enemy defenses
GB2590993A (en) * 2019-09-04 2021-07-14 Bae Systems Plc A reconnaisance and communciation assembly
US11157973B2 (en) 2012-11-16 2021-10-26 Scope Technologies Holdings Limited System and method for estimation of vehicle accident damage and repair

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4123649C2 (de) * 1991-07-17 1993-11-11 Rheinmetall Gmbh Ausstoßvorrichtung
GB2320556B (en) * 1993-02-23 1998-09-23 Marconi Gec Ltd Gun launchable sensor
US5537928A (en) 1995-04-17 1996-07-23 Hughes Missile Systems Company Piggyback bomb damage assessment system
GB2498185B (en) 2012-01-03 2016-04-27 Bae Systems Plc Surveillance system
SE2000241A1 (sv) * 2020-12-18 2022-06-19 Bae Systems Bofors Ab Kanister

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DE2429912A1 (de) * 1973-06-21 1975-01-23 Bofors Ab Verfahren und vorrichtung zum freigeben einer fallschirmgetragenen nutzlast
FR2260772A1 (de) * 1974-02-08 1975-09-05 France Etat
US3962537A (en) * 1975-02-27 1976-06-08 The United States Of America As Represented By The Secretary Of The Navy Gun launched reconnaissance system
US4267562A (en) * 1977-10-18 1981-05-12 The United States Of America As Represented By The Secretary Of The Army Method of autonomous target acquisition
FR2541444A1 (fr) * 1982-06-25 1984-08-24 Thomson Csf Dispositif de detection a distance du type mine et systeme de tir comportant de tels dispositifs
DE8703985U1 (de) * 1987-03-17 1988-07-14 Diehl GmbH & Co, 8500 Nürnberg Munition mit Drallbremse

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GB1258044A (de) * 1967-11-02 1971-12-22
SE339646B (de) * 1970-01-08 1971-10-11 Bofors Ab
FR2321723A1 (fr) * 1975-07-29 1977-03-18 Thomson Brandt Systeme de controle d'attitude et engin equipe d'un tel systeme
SE416235B (sv) * 1976-12-27 1980-12-08 Bofors Ab Bromsanordning for roterande kropp
DE3421607A1 (de) * 1984-06-09 1985-12-12 Dynamit Nobel Ag, 5210 Troisdorf Aufklaerungssystem
GB2162623B (en) * 1984-06-15 1988-08-10 Diehl Gmbh & Co A mechanism for aerodynamic deceleration and a body including such a mechanism
SE460436B (sv) * 1986-12-01 1989-10-09 Bofors Ab Anordning foer att minska rotationen och samtidigt aastadkomma en sidohastighet hos en roterande ammunitionsenhet
DE3643293A1 (de) * 1986-12-18 1988-06-30 Rheinmetall Gmbh Drallstabilisiertes traegergeschoss mit mindestens zwei submunitionsgeschossen
DE3730019C1 (de) * 1987-09-08 1988-12-22 Diehl Gmbh & Co Submunitions-Flugkoerper

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2429912A1 (de) * 1973-06-21 1975-01-23 Bofors Ab Verfahren und vorrichtung zum freigeben einer fallschirmgetragenen nutzlast
FR2260772A1 (de) * 1974-02-08 1975-09-05 France Etat
US3962537A (en) * 1975-02-27 1976-06-08 The United States Of America As Represented By The Secretary Of The Navy Gun launched reconnaissance system
US4267562A (en) * 1977-10-18 1981-05-12 The United States Of America As Represented By The Secretary Of The Army Method of autonomous target acquisition
FR2541444A1 (fr) * 1982-06-25 1984-08-24 Thomson Csf Dispositif de detection a distance du type mine et systeme de tir comportant de tels dispositifs
DE8703985U1 (de) * 1987-03-17 1988-07-14 Diehl GmbH & Co, 8500 Nürnberg Munition mit Drallbremse

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5432546A (en) * 1992-12-21 1995-07-11 Enel Company Weapon impact assessment system
FR2726643A1 (fr) * 1994-11-04 1996-05-10 Giat Ind Sa Dispositif d'observation d'une zone de terrain
EP0800052A3 (de) * 1996-04-04 1998-10-28 Diehl Stiftung & Co. Aufklärungseinrichtung
DE19613492C2 (de) * 1996-04-04 2001-10-04 Diehl Stiftung & Co Aufklärungseinrichtung
FR2754052A1 (fr) * 1996-10-02 1998-04-03 Diehl Gmbh & Co Projectile d'exercice balistique
US7283156B1 (en) * 2002-09-12 2007-10-16 Lockheed Martin Corporation Airborne imaging system and method
EP1761431A4 (de) * 2004-03-15 2010-09-22 Georgia Tech Res Inst Geschoss und system zur bereitstellung von luft-zu-oberfläche-erkennung
US7631601B2 (en) * 2005-06-16 2009-12-15 Feldman Paul H Surveillance projectile
JP2010085040A (ja) * 2008-10-01 2010-04-15 Ihi Aerospace Co Ltd 着弾観測システム
CN101949669A (zh) * 2010-08-10 2011-01-19 吉林保利科技中试有限公司 60毫米迫击炮微型电视侦察弹
CN101949669B (zh) * 2010-08-10 2013-03-13 吉林保利科技中试有限公司 60毫米迫击炮微型电视侦察弹
CN102162712A (zh) * 2010-12-20 2011-08-24 吉林保利科技中试有限公司 63-1式60毫米迫击炮照明弹
KR101305202B1 (ko) 2012-03-23 2013-09-12 국방과학연구소 다중 기폭관
US11157973B2 (en) 2012-11-16 2021-10-26 Scope Technologies Holdings Limited System and method for estimation of vehicle accident damage and repair
WO2014173916A1 (de) * 2013-04-24 2014-10-30 Rheinmetall Waffe Munition Gmbh Drallstabilisiertes leuchtgeschoss
GB2517445B (en) * 2013-08-20 2020-04-29 Bae Systems Plc Illumination munition
GB2517445A (en) * 2013-08-20 2015-02-25 Bae Systems Plc Illumination Munition
GB2517448A (en) * 2013-08-20 2015-02-25 Bae Systems Plc Frangible munition
GB2517448B (en) * 2013-08-20 2017-04-12 Bae Systems Plc Frangible munition
US9778004B2 (en) 2013-08-20 2017-10-03 Bae Systems Plc Smoke payload apparatus
US9784544B2 (en) 2013-08-20 2017-10-10 Bae Systems Plc Frangible munition
US9797698B2 (en) 2013-08-20 2017-10-24 Bae Systems Plc Common carrier munition
US10030953B2 (en) 2013-08-20 2018-07-24 Bae Systems Plc Illumination munition
FR3011919A1 (fr) * 2013-10-15 2015-04-17 Nexter Munitions Dispositif de freinage en rotation d'une enveloppe d'une charge utile, et projectile gyrostabilise equipe d'un tel dispositif
EP2863164A1 (de) 2013-10-15 2015-04-22 Nexter Munitions Rotationsbremsvorrichtung eines Mantels einer Nutzlast, und drallstabilisiertes Geschoss, das mit einer solchen Vorrichtung ausgestattet ist
US10633091B2 (en) 2015-01-29 2020-04-28 Scope Technologies Holdings Limited Accident monitoring using remotely operated or autonomous aerial vehicles
US11370541B2 (en) 2015-01-29 2022-06-28 Scope Technologies Holdings Limited Accident monitoring using remotely operated or autonomous aerial vehicles
WO2021034424A2 (en) 2019-07-12 2021-02-25 Leonardo Electronics Us Inc. Method and system for electronic warfare obscuration and suppression of enemy defenses
EP3833927A4 (de) * 2019-07-12 2022-06-08 Leonardo Electronics US Inc. Verfahren und system zur verschleierung von elektronischer kriegsführung und unterdrückung der abwehr des feindes
US11802940B2 (en) 2019-07-12 2023-10-31 Leonardo Electronics Us Inc Method and system for electronic warfare obscuration and suppression of enemy defenses
GB2590993A (en) * 2019-09-04 2021-07-14 Bae Systems Plc A reconnaisance and communciation assembly
GB2590993B (en) * 2019-09-04 2023-06-07 Bae Systems Plc A reconnaisance and communciation assembly
US11906274B2 (en) 2019-09-04 2024-02-20 Bae Systems Plc Reconnaissance and communication assembly
US11982519B2 (en) 2019-09-04 2024-05-14 Bae Systems Plc Reconnaissance and communication assembly

Also Published As

Publication number Publication date
GB9015445D0 (en) 1991-02-20
GB9115157D0 (en) 1991-09-04
IL98819A0 (en) 1992-07-15
GB2246420A (en) 1992-01-29

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