EP0679861B1 - Schiessvorrichtung für drahtgelenkte Munition aus einem mobilen Werfer - Google Patents

Schiessvorrichtung für drahtgelenkte Munition aus einem mobilen Werfer Download PDF

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Publication number
EP0679861B1
EP0679861B1 EP19950400899 EP95400899A EP0679861B1 EP 0679861 B1 EP0679861 B1 EP 0679861B1 EP 19950400899 EP19950400899 EP 19950400899 EP 95400899 A EP95400899 A EP 95400899A EP 0679861 B1 EP0679861 B1 EP 0679861B1
Authority
EP
European Patent Office
Prior art keywords
launch tube
reel
pivoting
installation according
axis
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
EP19950400899
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English (en)
French (fr)
Other versions
EP0679861A1 (de
Inventor
Frédérick Donnaint
Eric Droz-Bartholet
Isabelle Charruyer
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.)
Airbus Group SAS
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Airbus Group SAS
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Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0679861A1 publication Critical patent/EP0679861A1/de
Application granted granted Critical
Publication of EP0679861B1 publication Critical patent/EP0679861B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
    • 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
    • F41G7/30—Command link guidance systems
    • F41G7/32—Command link guidance systems for wire-guided missiles

Definitions

  • the invention relates to an installation designed to fire wire-guided ammunition such as a missile, from a mobile launcher such as a ship or an aircraft.
  • the filiform connecting member can in particular be made up of several conductors electrical or optical fiber. Because the transmission capacity of optical fiber is very far superior to that of drivers electrical connections over distances of several tens of kilometers can be insured when using an optical fiber, while these connections are limited to approximately 12 km in the case of electrical conductors. The flight time of the ammunition is considerably increased and reached several minutes.
  • the use of a coil linked to the launcher mobile is also illustrated in the document EP-A-0 443 623.
  • the coil linked to the mobile launcher is either attached directly to the latter so that its axis is oriented vertically, either mounted on the launcher via a gimbal type joint.
  • the angle formed between the axis of unwinding of the organ of filiform connection and the axis of the coil limits the maximum permissible unwinding speed.
  • the second configuration is incompatible with shooting a ammunition from a launch tube since the loop which forms between the ammunition and the coil linked to the launcher would then pass through the launch tube. In indeed, any significant change in focus of the launch tube resulting from displacement of the launcher mobile would exert significant mechanical stress on the filiform connecting member already unrolled since ammunition.
  • the subject of the invention is precisely a wire-fired munition firing installation, from a launch tube on board a mobile launcher, do not not having the disadvantages of the installations existing and in particular allowing the mobile launcher to follow any trajectory after firing the ammunition with a higher speed than in the existing facilities and without any part of the filiform connecting member is exposed and risks to be damaged at any time.
  • this result is obtained through an ammunition firing facility guided by a mobile launcher, comprising a tube launch ammunition normally housed in the launch tube, and a threadlike connecting member able to unwind from a first reel linked to the ammunition and a second coil linked to the tube launch, characterized by the fact that the launch has a front door, normally closed, the second coil being normally mounted in the launch tube, between the ammunition and the front door, through a means of tilting this second coil outside the launch tube, able to be activated before firing the ammunition.
  • the connecting member threadlike that connects the ammunition to the launch tube is completely placed inside the latter before firing.
  • the housing of the linked coil to the mobile launcher at the front of the ammunition and the tilting of this coil outside the tube launch just before firing allow practically cancel the angle formed between the axis of unwinding and axis of the reel when the launcher makes a U-turn and moves away from the ammunition after firing.
  • the second coil is fixed on an internal face of the front door, the means of tilting being interposed between the latter and the launch tube.
  • a buffer length of the filiform connecting member located between parts of this organ normally wound on the first and the second coil, is normally associated with the second coil.
  • means for ejecting this buffer length capable of being actuated after a actuation of the tilting means and before putting ammunition fire, are mounted in the second coil. This feature initiates the unwinding of the coil linked to the launcher, whereas this the latter has not yet completed his turn, without the filiform connecting member is not subjected to mechanical constraints too severe.
  • the second coil comprises a core in which the buffer length of the organ is housed of filiform connection and the ejection means.
  • the buffer length of the filiform connecting member advantageously supports means for increasing the drag coefficient.
  • this section is reinforced by protective sheathing.
  • the tilting means controls a about 270 ° pivoting of the second coil between a normal position, internal to the launch tube, in which the axis of the second coil is substantially orthogonal to the axis of the launch tube, and a firing position, external to the tube launch, in which the axis of the second coil is substantially parallel to the axis of the tube launch.
  • the second coil has then a cover, advantageously covered with a fairing, surrounding the part of the connecting member filiform normally wound on the second coil.
  • This cover has a circular outlet opening from the filiform connecting member, centered on the axis of the second coil and oriented upwards respectively or backwards depending on whether the second coil occupies its normal position or its firing position.
  • the launch On its outer surface, the launch then advantageously includes means of locking the second coil in its position Firing.
  • the tilting means comprises at minus a tilt control system and a articulation hinge of the second coil on the launch tube.
  • the hinge may include, either a single pivot axis orthogonal to the axis of the launch tube, i.e. two pivot axes parallel, orthogonal to the axis of the launch tube.
  • at least one piece of link able to pivot relative to the launching tube around a first of the pivot axes and by how the second coil can rotate around the second of the pivot axes.
  • the launch tube further includes a rear door, normally closed, as well as means opening of this door, capable of being actuated during the firing of the ammunition.
  • the reference 10 designates a helicopter on which several are on board firing installations 12 in accordance with the invention. Each of these shooting installations includes a tube of launch 14 (Fig. 2), a guided missile 16 and a fiber optic 18 permanently connecting missile 16 to launch tube 14. More specifically, Figure 1 depicts helicopter 10 making a U-turn after the firing of one of the missiles 16.
  • the invention does not not only applies in case the mobile launcher consists of a helicopter 10, but concerns also the case where this launcher is constituted by an aircraft of a different nature, a surface ship or submarine, or even a land vehicle.
  • missile 16 can be replaced by any ammunition wire-guided adapted to the launcher concerned.
  • the fiber optics can be replaced by any other threadlike connection such as a set of conductors electric.
  • a second section 18b of the optical fiber 18 comes out of missile 16 at the back of it and runs inside the launch tube 14, along missile 16, to connect the first section 18a mounted in the missile to a second coil 22 placed in the launch tube 14, in front of missile 16. More precisely, the second coil 22 is fixed on the inner face of a front door 24 of the launch tube 14, which normally closes the front end of this tube. The second coil 22 is thus interposed between missile 16 and front door 24, inside of the launch tube 14, when the firing installation 12 occupies its normal storage position.
  • the section 18b of the optical fiber, which connects coils 20 and 22, is reinforced by cladding of protection which allows it to resist attacks produced by the missile propellant 16, during ejecting the latter from the launch tube 14.
  • the second coil 22 includes a core 26, generally cylindrical or frustoconical in shape, eventually ended with flared ends. In the normal storage position illustrated in the figure 2, the axis of this core 26 is oriented substantially vertically, its lower end being connected to the front door 24 by a support 27.
  • the core 26 In its part turned upwards when the coil 22 occupies its storage position, the core 26 forms a housing, open upwards, in which a buffer length 18c of the optical fiber is stored 18, for example in the form of a winding.
  • the part of the core 26 adjacent to the buffer length 18c of optical fiber is used to house ejection means 28 which function, as we will see later, to expel the buffer length 18c from optical fiber outside the housing formed in the core 26, just before firing missile 16.
  • ejection means 28 can be constituted either by a spring mechanism, either by a pneumatic system or pyrotechnic.
  • buffer length 18c optical fiber supports means (not shown) to artificially increase the coefficient of aerodynamic drag of this part of the fiber when it is outside the tube of launch 14.
  • the buffer length 18c of the optical fiber connects the section 18b of this fiber to a section 18d of optical fiber, wound together in several layers on the core 26 of the coil 22.
  • the length of the section 18d wound on the coil 22 is generally less than or at most equal to the length of the section 18a wound on the reel 20.
  • a suitable adhesive ensures unrolling progressive and regular fiber optic from coils 20 and 22.
  • the end of the optical fiber 18 coming out coil 22 opposite the buffer length 18b is connected by a fiber section 18th to a connector optic 30 mounted on the launch tube 14 so as to allow the connection of optical fiber with a control system (not shown) installed on the helicopter 10.
  • the end of the optical fiber leaving the coil 22 enters a case (not shown) allowing transform in one direction the light signal into a signal electrical and in reverse the electrical signal in light signal.
  • the 18th fiber optic segment is then replaced by an electrical conductor and the optical connector 30 is itself replaced by a electrical connector.
  • the second coil 22 further includes a cover 32, which surrounds the optical fiber wound on the core 26.
  • This cover 32 is arranged coaxially to the core 26 and its inside diameter is slightly higher the diameter of the outermost fiber layer wound on the core 26, so as to leave a space allowing the fiber to unwind easily, account due to the bloating phenomenon that occurs during of this unfolding.
  • the cover 32 extends beyond the end of the core 26 facing upwards in the normal storage position of the coil 22 and its diameter then decreases to present a circular opening 32a, centered on the axis of the core 26 and by which the fiber leaves the reel 22.
  • the diameter of this opening 32a is for example close the outside diameter of the core 26.
  • the cover 32 is covered with a fairing 34 which extends below the support 27, in the normal storage position of the reel 22 illustrated in solid lines in Figure 2.
  • the front door 24 and the coil 22 fixed on this door are linked to the launch tube 14 by tilting means allowing this set of come and stand outside the launch tube, in a firing position that fully clears the front end of the launch tube.
  • This position of firing is illustrated in dashed lines on the Figure 2 and in solid lines in Figure 3C.
  • tilting means include a hinge 36, through which the front door 24 is articulated on the front end of the launch tube 14, and a tilt control system 38, which normally locks the front door 24 on the tube launch 14.
  • the tilt control system 38 may in particular be constituted by a gas generator pyrotechnic mounted in the top of the launch tube 14, at the front of the latter. This system 38 ensures normally keeping the front door 24 in its closed position and propels door 24 forward, around the hinge 36, when actuated.
  • the hinge 36 has a single axis 40, substantially horizontal, located at the bottom and in front of the launch tube 14. More precisely, the axis 40 is orthogonal to the axis of the launch tube and slightly offset forward and outward relative to this launch tube, so as to allow a 270 ° pivoting of the assembly formed by the door front 24 and reel 22, clockwise of a watch considering figure 2. This pivoting ends when the outer face of the front door 24 abuts against the underside of the tube launch 14. The axis of the coil 22 is then substantially parallel to the axis of the launch tube 14 and the circular opening 32a through which the fiber optic 18 comes out of the cover 32 is oriented towards the back.
  • the launch tube 14 bears on its outer surface of the locking means 42 which cooperate with the front door 24 when it has tilted 270 °.
  • the locking means 42 thus immobilize the second coil 22 in its firing position.
  • the locking means 42 can consist of a blocking system any mechanical.
  • the launching tube 14 In the normal storage position of the firing installation 12, the launching tube 14 also has a rear door 44 which closes the rear end of this tube.
  • Means of opening 46 mounted inside the launch tube 14 cooperate with the rear door 44 to maintain it normally closed and order the opening when firing the missile 16.
  • These opening means 46 can be any means, for example pyrotechnic, electrical, etc.
  • the firing installation 12 occupies its normal storage position illustrated in solid lines in FIG. 2, the front end of the installation does not has no protuberance likely to prohibit stacking or increasing the master-couple.
  • the installation forms a set which can be integrated on the launcher without other intervention than that required by fixing and installation connection.
  • the entire length of the optical fiber is housed in the launch tube, handling operations are facilitated and the missile is protected against attack by all kinds (mechanical, fluids or atmospheric agents such as hail, sand, etc.) encountered during handling and carrying phases on the launcher mobile.
  • the fiber link optic between the launcher and the missile is protected from assaults in the same way as the missile itself.
  • this configuration makes any mechanism useless fiber blocking to prevent unwinding spontaneous of one or the other of the coils under the effect of the aerodynamic drive generated by the moving the launcher.
  • the fiber output axes from the two coils are oriented towards the rear of the mobiles that constitute missile 16 and helicopter 10, which allows high travel speeds for each of them.
  • FIG. 2 The implementation of the shooting facility illustrated in FIG. 2 will now be described in referring successively to FIGS. 3A to 3C.
  • the tilt control system 38, the means ejection 28, the opening means 46 and the missile 16 thrusters are activated sequentially, with time intervals predetermined, as follows.
  • the system 38 of tilt control is activated, which effect of propelling the front door 24 forwards, around its pivot axis 40, as illustrated in Figure 3A.
  • the opening means 46 are actuated ( Figure 3C) so as to release the rear door 44 and missile 16 is fired. From then on, the helicopter can start a U-turn and move away missile speed, since the fiber exit axis unwinding from the reel 22 is oriented towards the rear compared to helicopter 10.
  • FIGS. 4A to 4C there is illustrated a alternative embodiment of the hinge 36.
  • the hinge has two horizontal and parallel axes 40a and 40b, oriented in a direction orthogonal to the axis of the tube launch 14. These axes 40a and 40b are linked launch tube 14 and door respectively rear 24.
  • the hinge further comprises one or more several connecting pieces constituted by levers 48, substantially C-shaped, the ends of which are articulated on axes 40a and 40b. All formed by the axes 40a and 40b and by the levers 48 is normally housed inside the launch tube 14, in the storage position of the firing installation ( Figure 4A).
  • the tilting means may include an electric actuator or a spring mechanism, to control the rotation of the front door 24 and levers 48 around the axis 40a, as well as torsion bars to then ensure the rotation of the front door 24 about the axis 40b.
  • the coil 22 can be directly supported by the launch tube 14, at instead of being fixed on the inside of the front door 24. Releasing the front door and tilting to the outside of the coil then intervene sequentially.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (14)

  1. Schießvorrichtung (1) für drahtgelenkte Munition aus einem mobilen Werfer, ein auf den Werfer (10) montiertes Abschußrohr (14), eine normalerweise in dem Abschußrohr befindliche Munition (16) und ein drahtförmiges Verbindungsorgan (18) umfassend, das sich von einer ersten, mit der Munition verbundenen Spule (20) und einer zweiten, mit dem Abschußrohr verbundenen Spule (22) abwickelt,
    dadurch gekennzeichnet,
    daß das Abschußrohr (14) eine normalerweise geschlossene vordere Tür (24) umfaßt, wobei die zweite Spule (22) normalerweise in dem Abschußrohr (14) zwischen der Munition (16) und der vorderen Tür (24) angebracht ist, um diese zweite Spule mittels einer Kippeinrichtung (36, 38), die vor dem Zünden der Munition betätigt werden kann, auf die Außenseite des Abschußrohrs zu schwenken.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die zweite Spule (22) auf einer Innenfläche der vorderen Tür (24) befestigt ist und die Kippeinrichtung (36, 38) eingefügt ist zwischen diese letztere und das Startrohr (14).
  3. Vorrichtung nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß eine Pufferlänge (18c) des drahtförmigen Verbindungsorgans, die sich zwischen Teilen dieses Organs befindet, die normal auf die erste und die zweite Spule (20, 22) gewickelt sind, normalerweise mit der zweiten Spule verbunden ist, wobei Ausstoßeinrichtungen (28) dieser Pufferlänge, die nach einer Betätigung der Kippeinrichtungen (36, 38) und vor dem Zünden der Munition (16) betätigt werden können, in die zweite Spule (22) montiert sind.
  4. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, daß die zweite Spule (22) einen Kern (26) umfaßt, in dem sich die genannte Pufferlänge (18c) und die Außstoßeinrichtungen (28) befinden.
  5. Vorrichtung nach einem der Ansprüche 3 und 4, dadurch gekennzeichnet, daß die genannte Pufferlänge (18c) des drahtförmigen Verbindungsorgans Einrichtungen zur Erhöhung des Luftwiderstandsbeiwert tragen.
  6. Vorrichtung nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß ein Teilstück (18b) des drahtförmigen Verbindungsorgans, das normalerweise in dem Abschußrohr (14) zwischen der ersten (20) und zweiten Spule (22) verläuft, durch eine Schutzhülle verstärkt ist.
  7. Vorrichtung nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß die Kippeinrichtungen (36, 38) eine Schwenkbewegung der zweiten Spule (22) um ca. 270° betätigen, zwischen einer Normalstellung im Innern des Abschußrohrs (14), bei dem die Achse der zweiten Spule im wesentlichen senkrecht ist zur Achse des Abschußrohrs, und einer Zündungsstellung außerhalb des Abschußrohrs (14), bei dem die Achse der zweiten Spule im wesentlichen parallel ist zur Achse des Abschußrohrs.
  8. Vorrichtung nach Anspruch 7, dadurch gekennzeichnet, daß die zweite Spule eine Haube (32) umfaßt, die den Teil des drahtförmigen Organs umgibt, der normalerweise auf die zweite Spule gewickelt ist, wobei diese Haube eine kreisrunde Ausgangsöffnung (32a) des drahtförmigen Verbindungsorgans aufweist, die zentriert ist auf die Achse der zweiten Spule und nach oben beziehungsweise nach hinten gerichtet ist, wenn die zweite Spule ihre Normalstellung beziehungsweise ihre Zündungsstellung einnimmt.
  9. Vorrichtung nach Anspruch 8, dadurch gekennzeichnet, daß die Haube (32) mit einer Verkleidung (34) bedeckt ist.
  10. Vorrichtung nach einem der Ansprüche 7 bis 9, dadurch gekennzeichnet, daß das Startrohr (14) Verriegelungseinrichtungen (42) der zweiten Spule (22) in ihrer Zündungsstellung umfaßt.
  11. Vorrichtung nach einem der Ansprüche 7 bis 10, dadurch gekennzeichnet, daß die Kippeinrichtungen wenigstens ein System (38) zur Betätigung der Kippbewegung und ein Gelenk (36) zum Schwenken der zweiten Spule (22) auf dem Startrohr (14) umfassen.
  12. Vorrichtung nach Anspruch 11, dadurch gekennzeichnet, daß das Gelenk (36) eine einzige zur Achse des Abschußrohrs (14) rechtwinklige Schwenkachse (40) umfaßt.
  13. Vorrichtung nach Anspruch 11, dadurch gekennzeichnet, daß das Gelenk (36) zwei zum Abschußrohr (14) rechtwinklige Schwenkachsen (40a, 40b) und wenigstens ein Verbindungsstück (48) umfaßt, das bezogen auf das Startrohr um eine erste dieser Schwenkachsen herum schwenken kann und bezogen auf das die zweite Spule um die zweite dieser Schwenkachsen herum schwenken kann.
  14. Vorrichtung nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß das Startrohr (14) eine normalerweise verschlossene hintere Tür (44) sowie Öffnungseinrichtungen (46) dieser Tür umfaßt, die bei der Zündung der Munition betätigt werden können.
EP19950400899 1994-04-25 1995-04-21 Schiessvorrichtung für drahtgelenkte Munition aus einem mobilen Werfer Expired - Lifetime EP0679861B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9404947 1994-04-25
FR9404947A FR2719111B1 (fr) 1994-04-25 1994-04-25 Installation de tir de munition filoguidée depuis un lanceur mobile.

Publications (2)

Publication Number Publication Date
EP0679861A1 EP0679861A1 (de) 1995-11-02
EP0679861B1 true EP0679861B1 (de) 1998-12-30

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EP19950400899 Expired - Lifetime EP0679861B1 (de) 1994-04-25 1995-04-21 Schiessvorrichtung für drahtgelenkte Munition aus einem mobilen Werfer

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EP (1) EP0679861B1 (de)
DE (1) DE69506940T2 (de)
ES (1) ES2128005T3 (de)
FR (1) FR2719111B1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007005254B4 (de) 2007-02-02 2009-01-29 Lfk-Lenkflugkörpersysteme Gmbh Abwurfvorrichtung und Abwurfverfahren für einen Flugkörper
DE102009011447B9 (de) * 2009-03-03 2012-08-16 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Zünden eines Gefechtskopfs einer Granate und Fahrzeug
FR3022881B1 (fr) * 2014-06-30 2016-11-04 Dcns Engin sous-marin comportant des moyens de lancement d'un vehicule sous-marin
DE102018207712A1 (de) * 2018-05-17 2019-11-21 Thyssenkrupp Ag Waffenrohrmodul zum Ausstoß von zwei hintereinander angeordneten geführten Waffen
DE102022001553B4 (de) 2022-05-04 2024-07-18 Bundesrepublik Deutschland, vertr. durch das Bundesministerium der Verteidigung, vertr. durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr Messverfahren und -vorrichtung zur Kontrolle des sicheren Einsatzes von Flugkörpern an Hubschraubern

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4860968A (en) * 1988-04-15 1989-08-29 The Boeing Company Communication link between moving bodies
US5005930A (en) * 1990-02-23 1991-04-09 Hughes Aircraft Company Multi-directional payout fiber optic canister
DE4112016C1 (en) * 1991-04-12 1992-08-06 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre

Also Published As

Publication number Publication date
EP0679861A1 (de) 1995-11-02
DE69506940D1 (de) 1999-02-11
DE69506940T2 (de) 1999-07-01
FR2719111A1 (fr) 1995-10-27
FR2719111B1 (fr) 1996-07-12
ES2128005T3 (es) 1999-05-01

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