EP0095387B1 - Cible aérienne remorquée - Google Patents

Cible aérienne remorquée Download PDF

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Publication number
EP0095387B1
EP0095387B1 EP83303024A EP83303024A EP0095387B1 EP 0095387 B1 EP0095387 B1 EP 0095387B1 EP 83303024 A EP83303024 A EP 83303024A EP 83303024 A EP83303024 A EP 83303024A EP 0095387 B1 EP0095387 B1 EP 0095387B1
Authority
EP
European Patent Office
Prior art keywords
target
dispositions
collapsed
pivotal arms
valise
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
Application number
EP83303024A
Other languages
German (de)
English (en)
Other versions
EP0095387A3 (en
EP0095387A2 (fr
Inventor
Klaus Büll
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.)
GQ Parachutes Ltd
Original Assignee
GQ Defence Equipment Ltd
GQ Parachutes Ltd
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 GQ Defence Equipment Ltd, GQ Parachutes Ltd filed Critical GQ Defence Equipment Ltd
Priority to AT83303024T priority Critical patent/ATE29582T1/de
Publication of EP0095387A2 publication Critical patent/EP0095387A2/fr
Publication of EP0095387A3 publication Critical patent/EP0095387A3/en
Application granted granted Critical
Publication of EP0095387B1 publication Critical patent/EP0095387B1/fr
Expired legal-status Critical Current

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Classifications

    • 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
    • F41J9/10—Airborne targets, e.g. drones, kites, balloons towed

Definitions

  • the present invention relates to targets and is particularly although not exclusively concerned with towed aerial targets launchable in a collapsed configuration from an aircraft in flight and deployable into an open configuration in which the target is towed by the aircraft on a tow line for engagement by aircraft during weapon firing practice.
  • Air-launchable towed aerial targets have been in use for many years and have taken various forms. While many have been launchable in a collapsed configuration and deployable on launching in to an open configuration the air speeds of the aircraft used for towing the targets have usually been low and the loads placed on the target during deployment also low. The packing of the target into its collapsed configuration and the manner in which it deploys into its open configuration has not therefore been critical.
  • the target is in accordance with the preamble of claim 1 launchable in a collapsed configuration from an aircraft in flight and deployable after launching into an open configuration.
  • the target comprises four right triangular panels of a flexible material, each having a long side and a short side forming the right angle and being connected together along their long sides with their short sides positioned at the rear of the target from the point of view of the direction of towing and a support frame comprising four pivotal arms attached to the short sides of the triangular panels and pivotally connected to the rear end of a mounting bar extending forwardly along and attached to the connected long sides of the panels.
  • a tow line is connected to the panels at their foremost points at their common apex.
  • the target is collapsed by swinging the four pivotal arms forwardly so that they lie against the mounting bar and then folding the panels upon the collapsed frame to form a package which is stowed in a container provided on the towing aircraft.
  • an explosive charge is detonated to project the target package into the air in which it automatically unfolds to its deployed form by the drag imposed upon it by its passage through the air.
  • the panels attached to the tow line at their common apex first unfold forwardly of the collapsed frame, and the pivotal arms then move from their collapsed dispositions to their extended dispositions under the loads exerted on the frame by the deploying panels.
  • Unfolding of the target in this way is usually very abrupt especially when the launch speed of the aircraft is high. Any asymmetrical loading of the frame during deployment can give rise to permanent distortion of the pivotal arms or their pivotal connections and lead to an irregular target flight path, making the target completely unusable unless the frame is repaired or replaced.
  • the four right triangular front panels are supplemented by four small rectangular rear panels of a flexible material which are connected to the pivotal arms and arranged to take up a streaming configuration to the rear of the frame.
  • the rear panels clearly add to the stresses placed on the frame during deployment of the target.
  • An object of the present invention is to provide an air-launchable towed aerial target which utilises a collapsible frame which extends during deployment of the target but in which the risk of permanently distorting the frame is substantially reduced.
  • an air-launchable towed aerial target stowable in a collapsed configuration in a towing aircraft and deployable into an open configuration in which the target is towed by the aircraft on a tow line comprising a support frame having a mounting bar and a plurality of pivotal arms pivotally connected to the rear end of the mounting bar and pivotal from collapsed dispositions in which they lie adjacent the mounting bar and extended dispositions in which they extend radially from the rear end of the bar, front panels of a flexible material connected to the pivotal arms and the mounting bar, and rear panels of a flexible material, each of the rear panels having a long side and a short side, and the rear panels being connected along their short sides to the pivotal arms from which they take up a streaming configuration behind the arms when the target is deployed and the pivotal arms are in their extended dispositions, characterised by the fact that the rear panels when deployed extend rearwardly of the pivotal arms by an amount greater than that by which the front panels extend forwardly of the pivotal arms, whereby the
  • the biasing means takes the form of a resilient ring mounted on the mounting bar and compressible by the pivotal arms when they are moved into their collapsed dispositions adjacent the mounting bar and the pivotal arms are releasably held in their collapsed dispositions prior to launching of the target and released after launching so that the arms are deployed to their extended dispositions under the biasing action of the ring.
  • the long sides of the rear panels which are adjacent each other may be connected together over a part at least of their length.
  • the target forms part of a target assembly which also includes a valise for housing the target in its collapsed configuration.
  • the valise in the preferred embodiment of the invention serves to hold the target in its collapsed configuration against the biasing action of the resilient ring and is held closed by quick release ties which upon release after launching of the assembly from an aircraft allow the valise to open out and fall away from the target which then deploys under the action of the resilient ring.
  • the valise containing the target in its collapsed configuration is preferably connected at its forward end to a main tow line paid out from the towing aircraft when the target is launched and the main tow line is arranged when paid out to effect release the quick release ties on the valise.
  • the main tow line is preferably connected at its paid out end to one end of an intermediate tow line which is contained in the valise and which commences to pay out when the valise falls away and the target commences to deploy and the intermediate tow line is connected at its other end to a nose element of the target for towing the deployed target.
  • the load applied to the frame by the rear panels can with advantage be increased without leading to distortion of the frame.
  • the rear panels which take up a streaming configuration to the rear of the support frame may be made substantially larger than those provided in the target hitherto proposed.
  • the target according to the present invention may be provided with front panels less forwardly extended than those provided in the hitherto proposed target.
  • the target configuration then changes from one in which the frame is located generally to the rear of the target to one in which the frame is positioned generally to the front of the target.
  • the target shown comprises a support frame 11 consisting of a mounting bar 12, a pivot block 13 rigidly attached to the rear end of the bar 12 and three pivotal arms 14, 15 and 16 which are pivotally mounted in the pivot block 13 and which are shown in Fig. 1 in extended dispositions in which they extend radially outwardly from the rear end of the mounting bar 12 in a plane at right angles to the axis of the mounting bar 12.
  • the pivotal arms 14, 15 and 16 support right triangular front panels 17, 18 and 19 and rectangular rear panels 20, 21 and 22.
  • the panels 17, 18 and 19 are of identical size and shape and each has a long side and a short side forming the right angle.
  • the long sides of the three panels 17 to 19 are connected together and a sleeve is provided along their connection into which the mounting bar 12 is fitted.
  • the short sides of the panels 17 to 19 are attached to the pivotal arms 14 to 16 as shown in Fig. 1.
  • a target nose loop 23 is secured to the common apex of the front panels 17 to 19 for attachment of a tow line.
  • the rectangular rear panels 20 to 22 are attached along their foremost short sides to the pivotal arms 14 to 16 so that when the target is deployed they take up a streaming configuration to the rear of the frame 11 as shown in Fig. 1.
  • the adjacent long sides of the rear panels 20 to 22 are connected together over an intermediate part 24 of their length but are free from each other in a region 25 immediately to the rear of the frame 11 and in a region 26 at the rear end of the target.
  • the rear panels 20, 21, 22 extend when deployed rearwardly of the pivotal arms 14,15,16 by an amount greater than that by which the front panels 17, 18, 19 extend forwardly of the pivotal arms 14, 15, 16, whereby the support frame 11 takes up a forward disposition in the deployed target.
  • the pivotal arms 14, 15 and 16 are pivotally mounted on the pivot block 13 in a manner best illustrated in Fig. 3.
  • the pivotal arm 14 is pivotally mounted between lugs 27 and 28 on a shouldered bolt 29 which passes through aligned bores in the lugs 27 and 28 and through a transverse bore in the arm 14 and which is held in place by a lock nut 30.
  • the pivotal arms 15 and 16 are pivotally mounted between lugs of the pivot block 13 in the same manner as the pivotal arm 14.
  • the mounting bar 12 extends forwardly from the pivot block 13 to which it is rigidly connected and carries a ring 31 of a highly resilient material.
  • the ring 31 is fitted on to the bar 12 by passing it over the forward end of the bar and is held in the position shown in Fig. 2 by an interference fit with the bar 12.
  • the ring 31 is shown in Fig. 2 compressed by the arms 14, 15 and 16 illustrated in Fig. 2.
  • the pivotal arm 16 is made from a rigid tube portion 32 closed at its forward end by a cap 33 and mounted at its rear end in a mounting block 34 fitted with a lug 35 by which the arm 16 is pivotally mounted in the pivot block 13.
  • the pivotal arms 14 and 15 are constructed in the same manner as the arm 16.
  • the mounting bar 12 likewise comprises a rigid metal tube portion 36 closed at its forward end by a cap 37 and mounted at its rearward end in the pivot block 13.
  • An aluminium alloy radar reflector 41 is secured to the rear of the pivot block 13 by a centrally located bolt (not shown) and held in position by an appropriately cut-away spacer tube 42.
  • the pivotal arms 14 to 16 are pivoted forwardly to bring them to their collapsed dispositions adjacent the mounting bar 12 as shown in Figures 2 and 3.
  • the pivotal arms 14 to 16 in moving to their collapsed dispositions engage the resilient ring 31 and a substantial force is required to compress the ring and bring the pivotal arms to their final collapsed dispositions adjacent the bar 12, where they are held together by a temporary tie.
  • Each of the triangular front panels 17 to 19 is then pulled out to form a folded sheet.
  • the rear panels 20 to 22 are next folded so as to bring the outer long side of each panel to the centre and then folded again in this way to reduce the panel width to one quarter of that of the original panel.
  • the rear panels 20 to 22 as folded are then brought forward and flaked to and fro over the collapsed frame and the flaked material then rolled up round the collapsed frame.
  • the rolled up target is then bound in this disposition by temporary ties and the tie holding the pivotal arms 14 to 16 in their collapsed dispositions removed.
  • the target thus folded up and bound is then placed in a quick release valise in which is also placed an intermediate tow line attached at its rear end to the towing loop 23 and projecting at its forward end from the valise.
  • the valise is closed by quick-release ties and the temporary ties binding the rolled up target removed.
  • the valise containing the folded up target is housed in a launch container provided on the towing aircraft, with the forward end of the intermediate tow line secured to the end of a main tow line which is paid out from the aircraft when the target is launched.
  • the towing aircraft is positioned for air launching the target and the target in its valise 40 then ejected from its launch container 38 on the end of the main tow line 39 so that it takes up a trailing position behind the aircraft as shown in Fig. 4.
  • the pull exerted by it is applied to quick-release cords on the valise which release the closure ties for the valise, whereupon the valise opens out and falls away from the collapsed target.
  • the biasing ring 31 becomes effective to force the pivotal arms 14 to 16 out into their extended dispositions and bring the triangular front panels 17, 18 and 19 into their open configuration.
  • the intermediate tow line commences to pay out and when fully paid out brings the target undertow by its connection to the target nose loop 23.
  • the rear panels 20 to 22 also rapidly unfold and take up a streaming configuration behind the pivotal arms 14 to 16.
  • biasing means for biasing the pivotal arms 14 to 16 to their extended dispositions immediately upon release of the folded target into the airstream prevents asymmetrical loading on the arms.
  • the rear panels 20 to 22 can therefore be of considerable size without giving rise to distortion of the frame 11 and by virtue of their size can present a better visual image for use in practice air combat.
  • the increased panel size furthermore provides for better assessment of hits produced in practice.
  • the target may readily be released from the towing aircraft following a practice session and recovered on the ground for subsequent use, without the need for replacement or repair of the frame.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Prostheses (AREA)
  • Feedback Control In General (AREA)
  • Aerials With Secondary Devices (AREA)
  • Tents Or Canopies (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (6)

1. Cible aérienne remorquée apte à être lancée d'un avion et pouvant être arrimée dans une configuration repliée à un avion de remorquage et pouvant être déployée dans une configuration ouverte, dans laquelle la cible est remorquée par l'avion au moyen d'une ligne de remorquage, et comportant un cadre de support (11) possédant une barre de montage (12) et une pluralité de bras pivotants (14,15, 16) raccordés de façon à pouvoir pivoter à l'extrémité arrière de la barre de montage (12) et pouvant pivoter à partir de positions repliées, dans lesquelles ils sont situés au voisinage de la barre de montage (12), et dans des positions déployées, dans lesquelles ils s'étendent radialement à partir de l'extrémité arrière de la barre (12), des panneaux avant (17, 18, 19) réalisés en un matériau flexible et raccordés aux bras pivotants (14, 15, 16) et à la barre de montage (12), et des panneaux arrière (20, 21, 22) réalisés en un matériau flexible, chacun des panneaux arrière (20, 21, 22) comportant un côté long et un côté court et ces panneaux arrière (20, 21, 22) étant raccordés le long de leurs côtés courts aux bras pivotants (14, 15, 16), à partir desquels ils prennent une position de vol derrière les bras (14,15,16) lorsque la cible est déployée et que les bras pivotants sont dans leurs positions déployées, caractérisée en ce que lorsqu'ils sont déployés, les panneaux arrière (20, 21, 22) s'étendent en arrière des bras pivotants (14,15,16) sur une distance plus grande que celle sur laquelle les panneaux avant (17, 18, 19) s'étendent en avant des bras pivotants (14, 15, 16), ce qui a pour effet que le cadre de support (11) prend une position située en avant dans la cible déployée et que des moyens de sollicitation agissent pendant ou après le lancement de la cible de manière à solliciter les bras depuis leurs positions repliées vers leurs positions déployées.
2. Cible selon la revendication 1, caractérisée en ce que les moyens de sollicitation possèdent la forme d'une bague élastique (31) montée sur la barre de montage (12) et pouvant être comprimée par les bras pivotants (14, 15, 16) lorsque ces derniers sont amenés dans leurs positions repliées au voisinage de la barre de montage (12), et que les bras pivotants (14, 15, 16) sont maintenus d'une manière détachable dans leurs positions repliées avant le lancement de la cible et sont libérés après le lancement de sorte que ces bras (14, 15, 16) sont ouverts dans leurs positions déployées sous l'action de sollicitation de la bague (31).
3. Cible selon la revendication 1 ou 2, caractérisée en ce que les côtés longs des panneaux arrière (20, 21, 22), qui sont adjacents les uns aux autres, sont raccordés entre eux sur une partie au moins de leur longueur.
4. Ensemble de cible caractérisée en ce qu'elle comporte une cible selon la revendication 2 ou selon la revendication 3 considérée comme dépendante de la revendication 2, et une enveloppe (40) servant à loger la cible dans une configuration repliée, que l'enveloppe (40) sert à maintenir la cible dans sa configuration repliée à l'encontre de l'action de sollicitation de la bague élastique (31) et que l'enveloppe est maintenue fermée au moyen d'attaches à libération rapide qui, lors de leur libération après le lancement de l'ensemble à partir d'un avion, permettent à l'enveloppe (40) de s'ouvrir et de tomber à partir de la cible, qui se déploie alors sous l'action de la bague élastique (31).
5. Ensemble de cible selon la revendication 4, caractérisé en ce que l'enveloppe (40) contenant la cible dans sa configuration repliée est raccordée, au niveau de son extrémité avant, à une ligne principale de remorquage (39) déroulée à partir de l'avion de remorquage lorsque la cible est lancée, et que la ligne principale de remorquage est agencée, lorsqu'elle est déroulée, de manière à provoquer la libération des attaches à libération rapide prévues sur l'enveloppe (40).
6. Ensemble de cible selon la revendication 5, caractérisé en ce que la ligne principale de remorquage (39) est raccordée au niveau de son extrémité déroulée, à une extrémité d'une ligne intermédiaire de remorquage qui est logée dans l'enveloppe (40) et qui commence à se dérouler lorsque l'enveloppe (40) tombe et que la cible commence à se déployer, et que la ligne intermédiaire de remorquage est raccordée, au niveau de son autre extrémité, à un élément en forme de nez (23) de la cible de manière à remorquer la cible déployée.
EP83303024A 1982-05-26 1983-05-25 Cible aérienne remorquée Expired EP0095387B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83303024T ATE29582T1 (de) 1982-05-26 1983-05-25 Geschlepptes luftziel.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8215312 1982-05-26
GB8215312 1982-05-26

Publications (3)

Publication Number Publication Date
EP0095387A2 EP0095387A2 (fr) 1983-11-30
EP0095387A3 EP0095387A3 (en) 1984-10-24
EP0095387B1 true EP0095387B1 (fr) 1987-09-09

Family

ID=10530625

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83303024A Expired EP0095387B1 (fr) 1982-05-26 1983-05-25 Cible aérienne remorquée

Country Status (5)

Country Link
EP (1) EP0095387B1 (fr)
AT (1) ATE29582T1 (fr)
DE (1) DE3373532D1 (fr)
GB (1) GB2122964B (fr)
YU (1) YU43732B (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5026073A (en) * 1989-04-26 1991-06-25 Teledyne Industries, Inc. Aerial gunnery target
DE4420206A1 (de) * 1994-06-10 1995-12-14 Dornier Gmbh Auslaß von Sichtbarkeitshilfen aus luftgestützten, harten Schleppkörpern

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3690662A (en) * 1970-01-08 1972-09-12 Joseph Pasqualini Towed aerial target

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2490793A (en) * 1945-10-25 1949-12-13 Floyd L Fleming Gunnery target
US2953377A (en) * 1956-06-08 1960-09-20 Del Mar Eng Lab High speed externally carried tow target
FR1380611A (fr) * 1963-10-14 1964-12-04 Const Electr Soc Et Cible aérienne remorquable
GB2076768A (en) * 1980-05-28 1981-12-09 Prototype Dev Associates Inc Aerial Gunnery Target
FR2505478A1 (fr) * 1981-05-11 1982-11-12 Pda Engineering Cible d'entrainement au tir antiaerien

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3690662A (en) * 1970-01-08 1972-09-12 Joseph Pasqualini Towed aerial target

Also Published As

Publication number Publication date
EP0095387A3 (en) 1984-10-24
GB2122964B (en) 1985-09-11
EP0095387A2 (fr) 1983-11-30
YU43732B (en) 1989-10-31
DE3373532D1 (en) 1987-10-15
YU116583A (en) 1987-08-31
GB2122964A (en) 1984-01-25
ATE29582T1 (de) 1987-09-15

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