EP0114602A2 - Missile - Google Patents

Missile Download PDF

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Publication number
EP0114602A2
EP0114602A2 EP84100124A EP84100124A EP0114602A2 EP 0114602 A2 EP0114602 A2 EP 0114602A2 EP 84100124 A EP84100124 A EP 84100124A EP 84100124 A EP84100124 A EP 84100124A EP 0114602 A2 EP0114602 A2 EP 0114602A2
Authority
EP
European Patent Office
Prior art keywords
missile
payload
axis
hollow body
missile according
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.)
Granted
Application number
EP84100124A
Other languages
German (de)
English (en)
Other versions
EP0114602B1 (fr
EP0114602A3 (en
Inventor
Werner Dipl.-Ing. Grosswendt
Dieter Dipl.-Ing. Böder
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0114602A2 publication Critical patent/EP0114602A2/fr
Publication of EP0114602A3 publication Critical patent/EP0114602A3/de
Application granted granted Critical
Publication of EP0114602B1 publication Critical patent/EP0114602B1/fr
Expired 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
    • 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
    • F42B12/56—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 for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • the invention relates to a missile for transporting a plurality of payloads according to the preamble of patent claim 1.
  • a hollow profile 34 In the center of this payload space there is a hollow profile 34 with end plates 30, 32 which can be fastened on both sides at the ends via nuts 36, 38.
  • the end plates are supported against one another by reinforcing rods 18, 20, the reinforcing rods being arranged one behind the other in the radial direction and evenly distributed in the circumferential direction, parallel to the missile axis.
  • a partition wall 16 consisting of thin sheet metal and thin in the form of a wall is wound in a star shape, which results in uniform individual chambers reaching as far as the shell, in which submunitions can be accommodated in multiple arrangements.
  • the partition 16 lies in the area of the inner turning points tangentially against a pipe 50, in the interior of which the inner space delimited by the pipe 34 propellant is arranged.
  • the reinforcing rods are not able to transmit loads in the direction of the missile axis because they have only a low kink stability due to their high degree of slenderness. Because of this, the payload space in question is unable to meet the growing need for high flight accuracy requirements, as is required for swing-out tails of steerable payloads to maintain precise steering functions.
  • the invention has for its object to provide a missile of the type mentioned, in which the area of the payload space at the start and during the flight, a clear division of in the direction of flight k örperachse from the payload resulting pressure-tensile loads from the circumferential direction from the Payload resulting torsional loads on different assemblies is possible and while maintaining an easy to assemble and compact design with simple, low-mass mechanisms, the benefit load space is to be characterized by a high degree of dimensional stability and the mechanisms also fulfill their function reliably when the cover is removed, so that when the payloads are ejected, a high level of flight accuracy can be achieved without hindrance.
  • the invention makes it possible that in a payload space of a missile, which is to be used to transport a plurality of payloads, which only absorbs the shell and transmits it to the missile during the rotational accelerations during the starting process and torques occurring on the flight path, while the The take-off process and any mass longitudinal forces of the payload occurring on the trajectory when the missile is braked are taken up by separate support elements which are designed as hollow bodies and are displaceable in relation to the envelope in the missile axis direction.
  • the hollow bodies are movable in a star shape via guides with the shell connected to the base plate in the axis-parallel direction and positively connected in the circumferential direction, on the one hand a uniform transmission in the longitudinal and circumferential direction of the load resulting from the torsion from the hollow bodies to the shell is achieved and on the other hand, by supporting the hollow body on a largely torsion-proof shell, which due to its closed outer skin and its small wall thickness is particularly characterized by a favorable ratio of polar section modulus to mass, a payload space with high dimensional stability is achieved, with negative effects advantageously due to this composite Effects of the torsional stress with regard to a hindrance of the payload can be avoided.
  • the shape of the hollow bodies designed as support elements offers, due to their isosceles triangular, Form, for the payload rooms to be provided, the advantages of being able to distinguish themselves with a high pressure absorption capacity through a small space requirement, an optimal use of space, a low mass and a high buckling stability.
  • the arrangement of prestressable tensioning elements within the hollow body has a particularly advantageous effect in terms of a favorable use of space by the fact that the prestressing forces are safely and stably supported by the respective hollow body, on the other hand, the advantages of a releasable connection can be sensibly applied, particularly on one simple assembly and high manufacturing accuracy, while straightening work, as is common with non-detachable connections, can be omitted.
  • the hollow bodies are furthermore advantageously characterized in that during the separation process of the casing by the firing of the explosive and the resulting explosion shock, the parts of the hollow bodies which protrude in the radial direction and which are adjacent to the explosive can plastically deform under the action of the explosive. thereby preventing an adverse hindrance to the payload.
  • the star-like connection of the hollow bodies also makes it possible in a simple manner to provide a direct line at the connection points of two adjacent hollow bodies from a central compressed gas line to the bags which are inflatable for the ejection process with compressed gas for ejecting the respective payload.
  • the hollow body can be connected to one another in one piece or releasably via webs, it being possible advantageously to use specifically lightweight cast parts made of an aluminum alloy with only minimal mechanical processing.
  • the connected hollow bodies and webs can also be used in divided directions in the axis-parallel direction, intermediate shelves being provided at the points of contact of the hollow bodies, which are fastened in a space-saving manner by means of preloaded expansion screws can.
  • the subject of the application is particularly advantageous in that the side of the hollow profile facing the shell performs a multiple function, this side of the hollow profile forming a form-fitting connection with the shell in the circumferential direction, which is designed as a sliding guide in the axial direction and additionally in its interior is also equipped with an axially parallel groove for receiving the blasting agent that can be used to divide the shell, which in addition to the clear separation of the torques to be transmitted from the axial thrust forces, on the one hand creates a payload space that is easy to assemble due to the shape, distribution and preload of the hollow body, yet is compact and dimensionally stable and, on the other hand, by the deformability of the side of the hollow profile facing the casing, it is prevented that the explosion shock adversely affects the payload after firing up the explosive.
  • a payload space 5 designed as a partial region of a missile 13 support elements 1 designed as a hollow body 2 are arranged between a front base plate 6 and a rear side base plate 7, the means producing means between the base plates 6, 7 via train connections 4 can be preloaded and, in cooperation with the casing 12, not only enable a plurality of payloads 16 to be in positionally stable transport positions, but also permit trouble-free ejection of the payloads 16 from the payload space 5 at a predeterminable point in the trajectory perpendicular to the missile axis 8.
  • Fig. 1 three support elements 1 are shown as a one-piece star-shaped hollow body 2, each forming closed triangular profiles 21.
  • the connection points 17 of the hollow bodies 2 are formed in their common center as a compressed gas line 20 running around the missile axis 8. Starting from this compressed gas line 20, they run symmetrically to Central axis 43 disposed outer side surfaces 3 6 egg ne s each hollow body 2 up to that of the missile axis 8 equidistant each and reaching to the sheath 12 and arranged perpendicular to the central axis 43 outer casing 3 of the triangular profile 21 in the radial direction.
  • the inner sides of the hollow triangular profile 21 are arranged parallel to the outer side surfaces 36 and the outer jacket 3, while the area of the hollow body 2 between the triangular profile 21 and the connection point 17 is designed as a web 22 tapering towards the missile axis 8.
  • an expansion screw 27 is provided within each triangular profile 21 as a means 4 for a train connection, so that not only the hollow bodies 2 relative to the base plates 6, 7 are arranged via centering pieces 30 also arranged within the respective triangular profile 21 (Fig. 2) are centered, but also by the bias of the expansion screw 27 a dimensionally stable connection between the base plates 6,7 (Fig. 2) and the hollow bodies 2 can be produced.
  • Each jacket 3 of the hollow body 2 contains, parallel to the missile axis direction, along the entire length a centrally arranged outward extension 34, which is closely enclosed on the guide surfaces 35 arranged on both sides by guide elements 33 of the same length and which together with these point in parallel to the missile axis 8 Direction forms a slidable guide 11, which, however, represents a positive connection of the hollow body 2 with the sleeve 12 in the circumferential direction. Due to the rotational movement generated at the launch of the missile 13 about its missile axis 8, which can possibly be maintained or reinforced during flight by additionally arranged engines, torsional loads arise in the area of the payload space 5 (FIG. 2 ) from the payload 16 in the circumferential direction .
  • these torsional loads are received separately in the guides 11 of the largely non-rotatable sleeve 12 and on the rear base plate 7 (FIG. 2) transferred, the sleeve 12 is only able to transmit the loads generated in the circumferential direction due to the axial displacement of the extension 34 in the guide members 33.
  • the extension 34 is provided on its radially outwardly limited side with a groove 14 arranged symmetrically to the central axis 43, which is used to receive an explosive 15 required for dividing the casing 12.
  • the outer shell 3 of the hollow body 2 is also designed such that it can plastically deform under the explosion of the explosive 15 and thereby the payload 16 and the tail wings 49 are not adversely affected.
  • the space-saving design of the star-shaped support elements 1 permit optimal utilization of the payload space 5 (FIG. 2), in which, for example, three steerable payloads can be accommodated next to one another with tailplane wings 49 already pivoted out in a partial area for transport.
  • the payload space 5 (FIG. 2)
  • three steerable payloads can be accommodated next to one another with tailplane wings 49 already pivoted out in a partial area for transport.
  • two of the four empennage wings 49 are advantageously arranged at a minimal parallel distance, while the space between the casing 12 and the payload 16 is sufficiently dimensioned to accommodate the two outer empennage wings 49, which means that the empennage wings 49 after leaving the payload space 5 (FIG.
  • a bag 18 which is inflatable with compressed gas is fastened in recesses 42 of the webs 22 and is connected directly to the central pressure gas line 20 via the connection line 19 passing through the connection point 17.
  • a bag 18 which is inflatable with compressed gas is fastened in recesses 42 of the webs 22 and is connected directly to the central pressure gas line 20 via the connection line 19 passing through the connection point 17.
  • extending floor plates 6, 7 are provided, which on the inwardly directed surfaces 38, after the prestressing by the expansion screws 27, on the end faces 9 and 10 of the support elements 1 designed as hollow bodies 2 can be pressed in a vertically supporting manner.
  • the inertia forces of the payload 16 resulting from the longitudinal acceleration or longitudinal deceleration of the missile 13 are either directly onto the base plate 6 or 7 or via transmission means 25 arranged perpendicular to the missile axis 8 to the hollow bodies 2 and webs 22 for subsequent direct transmission to the base plates 6 or 7 transferable.
  • this transmission means 25 can be designed as a disk-like intermediate floor 48, the hollow body 2 and webs 22, for example divided into two halves in the aircraft body direction, receiving the intermediate floor 48 at the connection points 24 and also being supported vertically under the force of the expansion screws 27 on the surfaces 26 of the intermediate floor 48 press on.
  • the two halves of the support elements 1 and the intermediate base 48 are centered in the radial direction by guides 44 of the expansion screw 27 provided with a multi-stepped shaft, the guides 44 in the bores 31 of the centering pieces 30 and in the bores 28 of the intermediate base 48 in the axial direction are movably introduced.
  • the expansion screw 27 is provided with an external thread on both ends at the ends 47, the expansion screw 27 advantageously being inserted directly into the rear base plate 7 for ease of installation is screwed and the base plate 6 is held on the front by bleeding 50 by the expansion screws 27. Because the nuts 50 are arranged on the side of the base plate 6 facing away from the usable space 5, the guide 44 of the expansion screw 27 can be inserted directly centering into the bore 31 of the base plate 6, as a result of which the front of the hollow body 2 in the radial direction relative to the base plate 6 can be fixed, while the end of the hollow body 2 resting on the side 38 of the rear base plate 7 is locked in the radial direction by a bushing 29 which is fastened in aligned bores 31 of the centering piece 30 and the base plate 7.
  • the sleeve 12 is only fixed on one side in the direction parallel to the axis in order to avoid stresses in relation to the hollow body 2 which is exposed to elastic compressions in the direction of the missile axis, the rear end of the sleeve 12 being impacted, inserted or in the radial direction from the outside via the radial surface 41 rotatable means 37 is attached.
  • the grooves 14 FIG. 1
  • the grooves 40 arranged in the same continuation of the grooves 14 (FIG. 1), which open into a groove 39 arranged in the circumferential direction in the base plate 7, filled by the explosive 15, which can be ignited by an external or internal command in the event of an operation.
  • the bags 18 are in the axial direction over the entire length at the connection point in each sub-parcel of the payload space 5 17 (FIG. 1), each bag 18 being connected directly to the compressed gas line 20 by a plurality of connecting lines 19, as a result of which the bags 18 can be filled up evenly with compressed gas and thus also a rapid ejection of the payload 16 into a perpendicular to the missile axis 8 Ensure direction.
  • connection 23 is established by positive locking of a spring 45 arranged on each separate hollow body 2 with a groove 46 directed radially outward at the end of each web 22 via connecting means, not shown. In the region of the groove 46, the web 22, which has a uniformly thin wall thickness, is fork-shaped.
  • the guide 11 is formed directly by both side surfaces 36 of the hollow profile 2 adjoining the jacket 3 and by two angle profiles each formed as guide elements 33, which are firmly connected to the sleeve 12 on both sides in a sliding manner.
  • an expansion screw 27 is provided analogously to FIG. 1 as a prestressable means 4 for a train connection.
  • the jacket 3 is designed in such a way that it has a groove 14 directed radially outward in the center for receiving the explosive 15 required for disassembling the casing 12, the groove base being able to be plastically deformed under the action of the explosion and thereby avoiding an adverse influence on the payload 16 .
  • the support elements 1, the base plates 6, 7 (FIG. 2) and the intermediate base 48 (FIG. 2) can also be on the support elements, l-fastened brackets are secured during the flight, but they lose their holding function when the payloads 16 are ejected under the pressure of the inflating bags 18.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
EP84100124A 1983-01-21 1984-01-09 Missile Expired EP0114602B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833301873 DE3301873A1 (de) 1983-01-21 1983-01-21 Flugkoerper
DE3301873 1983-01-21

Publications (3)

Publication Number Publication Date
EP0114602A2 true EP0114602A2 (fr) 1984-08-01
EP0114602A3 EP0114602A3 (en) 1986-02-05
EP0114602B1 EP0114602B1 (fr) 1988-01-07

Family

ID=6188797

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84100124A Expired EP0114602B1 (fr) 1983-01-21 1984-01-09 Missile

Country Status (3)

Country Link
US (1) US4558645A (fr)
EP (1) EP0114602B1 (fr)
DE (2) DE3301873A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0195854A2 (fr) * 1985-02-27 1986-10-01 Dynamit Nobel Aktiengesellschaft Missile
EP0293280A1 (fr) * 1987-05-26 1988-11-30 Thomson-Brandt Armements Dispositif de fermeture étanche et éjectable, notamment pour roquettes à sous-munitions
EP0297992A1 (fr) * 1987-07-03 1989-01-04 Thomson-Brandt Armements Dispositif de fermeture éjectable, notamment pour roquettes à sous-munitions
EP0395520A1 (fr) * 1989-04-27 1990-10-31 GIAT Industries Projectile porteur muni d'un dispositif d'éjection pour des sous-munitions
FR2648902A1 (fr) * 1989-06-26 1990-12-28 Olin Corp Vessie gonflable et dispositif de dispersion la comportant pour systeme d'armes

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3523769A1 (de) * 1985-07-03 1987-01-08 Diehl Gmbh & Co Submunitions-flugkoerper mit ausstellbaren gleitfluegeln
ES2000853A6 (es) * 1986-08-08 1988-03-16 Esperanza & Cie Sa Proyectil portador para mortero
DE3630083A1 (de) * 1986-09-04 1988-03-10 Bayern Chemie Gmbh Flugchemie Vorrichtung zum ausstossen von behaeltern, insbesondere von munition
DE3630082A1 (de) * 1986-09-04 1988-03-10 Bayern Chemie Gmbh Flugchemie Vorrichtung zum ausstossen von behaeltern, insbesondere von munition
DE3730019C1 (de) * 1987-09-08 1988-12-22 Diehl Gmbh & Co Submunitions-Flugkoerper
DE3809177C1 (fr) * 1988-03-18 1989-06-22 Buck Chemisch-Technische Werke Gmbh & Co, 7347 Bad Ueberkingen, De
FR2641858B1 (fr) * 1989-01-17 1991-03-15 Thomson Brandt Armements Dispositif de deverrouillage pneumatique pour munitions largables a partir d'un vecteur
DE3915585A1 (de) * 1989-05-12 1990-11-15 Diehl Gmbh & Co Submunitions-flugkoerper
US5107767A (en) * 1989-06-26 1992-04-28 Olin Corporation Inflatable bladder submunition dispensing system
FR2656414B1 (fr) * 1989-12-22 1993-01-22 Thomson Brandt Armements Systemes de retenue de sous-munitions embarquees dans un vecteur.
US5211358A (en) * 1991-05-13 1993-05-18 General Dynamics Corporation Airfoil deployment system for missile or aircraft
US6416018B2 (en) 1996-09-17 2002-07-09 The Boeing Company Satellite dispenser
US6138951A (en) * 1998-08-10 2000-10-31 Mcdonnell Douglas Corporation Spacecraft dispensing system
US6296206B1 (en) 1999-12-01 2001-10-02 The Boeing Company Cantilever, bi-level platform satellite dispenser
US6357698B1 (en) 2000-02-02 2002-03-19 The Boeing Company Twin lobe spacecraft dispenser apparatus and method
US6672220B2 (en) 2001-05-11 2004-01-06 Lockheed Martin Corporation Apparatus and method for dispersing munitions from a projectile
WO2010038061A1 (fr) * 2008-10-01 2010-04-08 Bae Systems Plc Appareil pour manipuler les munitions
BRPI0919594A2 (pt) * 2008-10-01 2015-12-08 Bae Systems Plc recipiente para uma munição

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH78373A (de) * 1916-01-21 1918-07-16 Bischoff Gredinger Carl Geschoß, insbesondere zum Beschießen von Flugzeugen
FR1553052A (fr) * 1967-11-28 1969-01-10
US3461801A (en) * 1968-01-25 1969-08-19 Us Navy Multi-canister ejecting device
US3726223A (en) * 1970-02-16 1973-04-10 Us Navy Adaptive warhead
US3938439A (en) * 1974-06-21 1976-02-17 The United States Of America As Represented By The Secretary Of The Army Charge deployment device
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern
DE3048617A1 (de) * 1980-12-23 1982-07-22 Dynamit Nobel Ag, 5210 Troisdorf Gefechtskopf mit sekundaerkoerpern als nutzlast

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3865034A (en) * 1971-12-20 1975-02-11 Us Air Force Submissible air-to-surface warhead with propellant-diaphragm deployment mechanism
DE3026159C2 (de) * 1980-07-10 1984-05-30 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Gasdrucksystem zum Ausstoßen von Munition aus einem Gefechtskopf oder dergleichen Munitionsbehältnis

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH78373A (de) * 1916-01-21 1918-07-16 Bischoff Gredinger Carl Geschoß, insbesondere zum Beschießen von Flugzeugen
FR1553052A (fr) * 1967-11-28 1969-01-10
US3461801A (en) * 1968-01-25 1969-08-19 Us Navy Multi-canister ejecting device
US3726223A (en) * 1970-02-16 1973-04-10 Us Navy Adaptive warhead
US3938439A (en) * 1974-06-21 1976-02-17 The United States Of America As Represented By The Secretary Of The Army Charge deployment device
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern
DE3048617A1 (de) * 1980-12-23 1982-07-22 Dynamit Nobel Ag, 5210 Troisdorf Gefechtskopf mit sekundaerkoerpern als nutzlast

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0195854A2 (fr) * 1985-02-27 1986-10-01 Dynamit Nobel Aktiengesellschaft Missile
EP0195854A3 (fr) * 1985-02-27 1987-01-14 Dynamit Nobel Aktiengesellschaft Missile
EP0293280A1 (fr) * 1987-05-26 1988-11-30 Thomson-Brandt Armements Dispositif de fermeture étanche et éjectable, notamment pour roquettes à sous-munitions
FR2615825A1 (fr) * 1987-05-26 1988-12-02 Thomson Brandt Armements Dispositif de fermeture etanche et ejectable, notamment pour roquettes a sous-munitions
US4930422A (en) * 1987-05-26 1990-06-05 Thomson-Brandt Armements Ejectable, imperviously sealing device especially for rockets with munitions
EP0297992A1 (fr) * 1987-07-03 1989-01-04 Thomson-Brandt Armements Dispositif de fermeture éjectable, notamment pour roquettes à sous-munitions
FR2617464A1 (fr) * 1987-07-03 1989-01-06 Thomson Brandt Armements Dispositif de fermeture ejectable, notamment pour roquettes a sous-munitions
US4879941A (en) * 1987-07-03 1989-11-14 Thomson-Brandt Armements Ejectable closing device, especially for rockets with munitions
EP0395520A1 (fr) * 1989-04-27 1990-10-31 GIAT Industries Projectile porteur muni d'un dispositif d'éjection pour des sous-munitions
FR2646503A1 (fr) * 1989-04-27 1990-11-02 France Etat Armement Dispositif d'ejection de conteneurs sur trajectoire
FR2648902A1 (fr) * 1989-06-26 1990-12-28 Olin Corp Vessie gonflable et dispositif de dispersion la comportant pour systeme d'armes

Also Published As

Publication number Publication date
US4558645A (en) 1985-12-17
DE3468527D1 (en) 1988-02-11
EP0114602B1 (fr) 1988-01-07
EP0114602A3 (en) 1986-02-05
DE3301873A1 (de) 1984-07-26

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