EP0013422A1 - Device for supporting and aiming an indirect firing weapon - Google Patents

Device for supporting and aiming an indirect firing weapon Download PDF

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Publication number
EP0013422A1
EP0013422A1 EP79105363A EP79105363A EP0013422A1 EP 0013422 A1 EP0013422 A1 EP 0013422A1 EP 79105363 A EP79105363 A EP 79105363A EP 79105363 A EP79105363 A EP 79105363A EP 0013422 A1 EP0013422 A1 EP 0013422A1
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EP
European Patent Office
Prior art keywords
weapon
rods
drive shaft
carrier
aiming
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
EP79105363A
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German (de)
French (fr)
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EP0013422B1 (en
Inventor
Cornelius Mayer
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Rheinmetall Air Defence AG
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Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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Publication of EP0013422A1 publication Critical patent/EP0013422A1/en
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Publication of EP0013422B1 publication Critical patent/EP0013422B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
    • F41A27/06—Mechanical systems

Definitions

  • the invention relates to a device for storing and aiming an indirectly firing weapon, in particular a rocket launcher, with a bearing support supported on a carrier, to which the weapon is articulated and with a rod which is adjustable in length and which on the one hand is connected to a front part of the Gun and on the other hand is articulated on the carrier.
  • a device of this type for a rocket launcher is known from US Pat. No. 2,800,836, in which the rod is telescopic and is provided with a number of transverse bores into which a pin can be inserted for positioning a desired elevation of the rocket launcher.
  • This aiming of the weapon is cumbersome and imprecise. This solution does not provide a possibility of aiming the weapon sideways.
  • the invention as characterized in the claims solves the problem of both a fast and accurate H öhenonne as well as a fast and precise page directing the gun in a certain angular range to allow.
  • a rocket launcher 1 is shown as an example of an indirectly firing weapon, which has two support tubes 2 (FIG. 3) and a plurality of interchangeable tubes 3, each in a front region 1 a and in a rear region 1 b of the weapon are held together in a frame 4, 5 parallel to each other.
  • the rear frame 5 is provided with two downwardly directed lugs 6, 7, each of which has a bore 8, 9 which is coaxial with one another.
  • the elevation pins 12, 13 are arranged in the bores 8, 9 of the lugs 6, 7 and form an elevation bearing 15 of the rocket launcher 1 with them.
  • the column 11 is supported in a bearing support 18 via a ball joint 16.
  • the bearing support 18 according to the illustrated embodiment consists of two identical triangular walls 18a which are positioned at an angle to one another and which coincide with one side 18b, whereby a roof-shaped structure is formed which is open to the rear.
  • the bearing support 18 could also have a different shape, for example as one Three-legged frame are formed.
  • the bearing support 18 is supported on a carrier 20 which, depending on the use, is formed, for example, by a vehicle, a vehicle trailer or a platform supported on the ground.
  • a support plate 21 is fastened in the walls 18a of the bearing support 18 parallel to the carrier 20 and perpendicular to the longitudinal center plane of the weapon (FIGS. 1 and 3).
  • a cross table 22, which functions in a manner known per se, is mounted on the support plate 21, the column 11 protruding longitudinally into the upper slide 23 thereof.
  • a distribution gear 30 (FIGS. 1 and 4) is attached to the front frame 4 and comprises three intermeshing bevel gears 31, 32, 33, of which the central bevel gear 31 of a first drive shaft 34, the other two bevel gears 32, 33 each an adjustable rod 35, 36 arranged between the rocket launcher 1 and the carrier 20.
  • the central bevel gear 31 is connected via a front universal joint 37 to a central, telescopic part 38 of the first drive shaft 34, which on the other hand is connected via a rear universal joint 39 to a part 40 of the first drive shaft 34 mounted in a bore 14 in the head 10 of the column 11 connected is.
  • the part 40 is provided with a crank 41.
  • the rods 35, 36 each have a nut part 43 or 45 and a threaded spindle 44 or 46, which are designed to be self-locking. Both rods 35, 36 are, for example, right-handed and have the same slope. 4 is connected to the bevel gears 32, 33 of the transfer gear 30 via a front universal joint 47, 48, respectively are, the threaded spindles 44, 46 via a rear universal joint 49, 50 each with a rear bevel gear 51, 52 in drive connection. These bevel gears 51, 52 forming the rear ends of the rods 35, 36 are mounted in a gear box 53 arranged on the carrier 20.
  • the gearbox 53 there is also a second drive shaft 54 associated with the two rear ends of the rods 35, 36, and two bevel gears 55, 56 are engaged with the respective rear bevel gear 51, 52 (FIG. 4).
  • the gear box 53 with the second drive shaft 54 is guided according to FIGS. 1 to 3 through the walls 18a of the bearing support 18.
  • the second drive shaft 54 is connected to a crank 59 via a further right-angled pair of bevel gears 57, 58 (FIG. 4).
  • the drive shaft 54 could also be driven by a servo motor 62 via a pair of bevel gears 57, 60 and a clutch 61.
  • a motor drive of the first drive shaft 34 could also be implemented, but this is not shown in the drawing for the sake of simplicity.
  • the column 11 carrying the rocket launcher 1 and serving to straighten the rocket launcher 1 is first placed vertically with the help of the aiming attachment 17 and the cross table 22.
  • the column 11 supported in the ball joint 16 is pivoted by adjusting the cross table 22 from the central position according to FIGS. 1 and 3 until it is again in the vertical position.
  • the rocket launcher 1 is set in this way, the true size of the side and height can then be read on the alignment attachment 17.
  • the first drive shaft 34 is driven on via the crank 41 (or possibly via the servomotor (not shown in more detail)).
  • the middle bevel gear 31 in the distribution gear 30 the other two bevel gears 32, 33 in the same direction.
  • the rocket launcher 1 is pivoted about the elevation pins 12, 13 of the elevation bearing 15 in the region of the angle ⁇ , as can be seen from FIG. 1.
  • the telescopic design only makes the distance between the universal joints 37, 39, which changes slightly when the rocket launcher 1 is pivoted about the elevation pins 12, 13, one of which 39 the stationary column 11 is assigned, compensated.
  • the directional angle can also be changed in a specific angular range] ⁇ .
  • the second drive shaft 54 is driven via the crank 59 or via the servo motor 62.
  • the rocket launcher 1 is pivoted in the sense shown in FIG. 2 from the central position laterally about the axis of the column 11 in the range of the angle ⁇ / 2.

Abstract

1. Device for mounting and for aiming an indirectly firing weapon, especially a rocket launcher (1), with a mounting support (18) which rests on a carrier (20) and on which the weapon is articulated, and with a longitudinally adjustable rod (35 and 36 respectively) which is articulated, at one end, on a front part (1a) of the weapon and, at the other end, on a carrier (20), characterized in that, apart from the one rod (35 or 36), a further longitudinally adjustable rod (35, 36) is articulated on the front part (1a) of the weapon, in that the rear ends of the two rods (35, 36) are articulated on the carrier (20) at a distance from one another, in that the two rods (35, 36) each have, in a manner known per se, a threaded spindle (44 and 46 respectively), and a nut part (43 and 45 respectively), in that the two rods (35, 36) are longitudinally adjustable simultaneously in the same direction, via a first drive device (34, 30), for changing the vertical aiming angle of the weapon, and in that the two rods (35, 36) are longitudinally adjustable simultaneously in the opposite direction, via a second drive device (54, 51, 52), for changing the lateral aiming angle of the weapon.

Description

Die Erfindung betrifft eine Vorrichtung zur Lagerung und zum Richten einer indirekt schiessenden Waffe, insbesondere eines Raketenwerfers, mit einer sich an einem Träger abstützenden Lagerstütze, an welcher die Waffe angelenkt ist und mit einer in ihrer Länge verstellbaren Stange, die einerseits an einem vorderen Teil der Waffe und anderseits am Träger angelenkt ist.The invention relates to a device for storing and aiming an indirectly firing weapon, in particular a rocket launcher, with a bearing support supported on a carrier, to which the weapon is articulated and with a rod which is adjustable in length and which on the one hand is connected to a front part of the Gun and on the other hand is articulated on the carrier.

Es ist eine Vorrichtung dieser Art für einen Raketenwerfer aus der US-PS 2 800 836 bekannt, bei welcher die Stange teleskopisch ausgebildet und mit einer Anzahl von Querbohrungen versehen ist, in welche ein Stift hineinschiebbar ist zum Positionieren einer gewünschten Elevation des Raketenwerfers. Dieses Richten der Waffe ist umständlich und ungenau. Eine Möglichkeit des Seitenrichtens der Waffe ist bei dieser Lösung nicht vorgesehen.A device of this type for a rocket launcher is known from US Pat. No. 2,800,836, in which the rod is telescopic and is provided with a number of transverse bores into which a pin can be inserted for positioning a desired elevation of the rocket launcher. This aiming of the weapon is cumbersome and imprecise. This solution does not provide a possibility of aiming the weapon sideways.

Die Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, löst die Aufgabe, sowohl ein schnelles und präzises Höhenrichten als auch ein schnelles und präzises Seitenrichten der Waffe in einem bestimmten Winkelbereich zu ermöglichen.The invention, as characterized in the claims solves the problem of both a fast and accurate H öhenrichten as well as a fast and precise page directing the gun in a certain angular range to allow.

Die durch die Erfindung erzielten Vorteile sind insbesondere darin zu erblicken, dass keine'zusätzliche Blockierung der Vorrichtung in'der gewünschten Stellung erforderlich ist, so dass die Präzision der Positionierung gegenüber der bekannten stufenweisen Verstellung wesentlich erhöht wird.The advantages achieved by the invention can be seen in particular in the fact that no additional blocking of the device in the desired position is required, so that the precision of the positioning is significantly increased compared to the known stepwise adjustment.

Ein Ausführungsbeispiel der Erfindung ist in der Zeichnung dargestellt und im folgenden näher beschrieben.An embodiment of the invention is shown in the drawing and described in more detail below.

Es zeigen:

  • Fig. 1 eine schematische Darstellung einer erfindungsgemässen Vorrichtung an einem Raketenwerfer in Ansicht und teilweise im Schnitt;
  • Fig. 2 eine Aufsicht der in Fig. 1 dargestellten Vorrichtung;
  • Fig. 3 eine Seitenansicht der in Fig. 1 dargestellten Vorrichtung, von hinten betrachtet;
  • Fig. 4 ein Antriebsschema der erfindungsgemässen Vorrichtung.
Show it:
  • Figure 1 is a schematic representation of an inventive device on a rocket launcher in view and partially in section.
  • Fig. 2 is a plan view of the device shown in Fig. 1;
  • Fig. 3 is a side view of the device shown in Fig. 1 viewed from the rear;
  • Fig. 4 is a drive diagram of the device according to the invention.

In Fig. 1 bis 3 ist als Beispiel für eine indirekt schiessende Waffe ein Raketenwerfer 1 dargestellt, der zwei Tragrohre 2 (Fig. 3) sowie mehrere auswechselbare Rohre 3 aufweist, die in einem vorderen Bereich la sowie in einem hinteren Bereich lb der Waffe jeweils in einem Spant 4, 5 parallel zueinander zusammengehalten werden. Das hintere Spant 5 ist gemäss Fig. 3 mit zwei nach unten gerichteten Ansätzen 6, 7 versehen, die je eine zueinander koaxiale Bohrung 8, 9 aufweisen. Zwischen die Ansätze 6, 7 ragt ein Kopf 10 einer vertikalen Säule 11 hinein, der mit zwei Elevationszapfen 12, 13 versehen ist. Die Elevationszapfen 12, 13 sind in den Bohrungen 8, 9 der Ansätze 6, 7 angeordnet und bilden mit diesen ein Elevationslager 15 des Raketenwerfers 1.1 to 3, a rocket launcher 1 is shown as an example of an indirectly firing weapon, which has two support tubes 2 (FIG. 3) and a plurality of interchangeable tubes 3, each in a front region 1 a and in a rear region 1 b of the weapon are held together in a frame 4, 5 parallel to each other. 3, the rear frame 5 is provided with two downwardly directed lugs 6, 7, each of which has a bore 8, 9 which is coaxial with one another. A head 10 of a vertical column 11, which is provided with two elevation pins 12, 13, protrudes between the lugs 6, 7. The elevation pins 12, 13 are arranged in the bores 8, 9 of the lugs 6, 7 and form an elevation bearing 15 of the rocket launcher 1 with them.

Die Säule 11 ist gemäss Fig. 1 und 3 über ein Kugelgelenk 16 in einer Lagerstütze 18 gelagert. Die Lagerstütze 18 nach dem dargestellen Ausführungsbeispiel besteht aus zwei gleichen, schräg zueinander gestellten, dreieckförmigen Wänden 18a, die mit ihrer einen Seite 18b zusammenfallen, wodurch ein dachförmiges, nach hinten offenes Ge-bilde entsteht. Selbstverständlich könnte jedoch die Lagerstütze 18 auch eine andere Form besitzen, z.B. als ein Dreibeingestell ausgebildet werden. Abgestützt ist die Lagerstütze 18 auf einem Träger 20, der - je nach Gebrauch - beispielsweise durch ein Fahrzeug, einen Fahrzeuganhänger oder eine am Boden abgestützte Plattform gebildet wird.1 and 3, the column 11 is supported in a bearing support 18 via a ball joint 16. The bearing support 18 according to the illustrated embodiment consists of two identical triangular walls 18a which are positioned at an angle to one another and which coincide with one side 18b, whereby a roof-shaped structure is formed which is open to the rear. Of course, however, the bearing support 18 could also have a different shape, for example as one Three-legged frame are formed. The bearing support 18 is supported on a carrier 20 which, depending on the use, is formed, for example, by a vehicle, a vehicle trailer or a platform supported on the ground.

In den Wänden 18a der Lagerstütze 18 ist parallel zum Träger 20 und senkrecht zur Längsmittelebene der Waffe eine Tragplatte 21 befestigt (Fig. 1 und 3). Auf der Tragplatte 21 ist ein in an sich bekannter Weise funktionierender Kreuztisch 22 angebracht, in dessen oberen Schlitten 23 die Säule 11 längsverschieblich hineinragt.A support plate 21 is fastened in the walls 18a of the bearing support 18 parallel to the carrier 20 and perpendicular to the longitudinal center plane of the weapon (FIGS. 1 and 3). A cross table 22, which functions in a manner known per se, is mounted on the support plate 21, the column 11 protruding longitudinally into the upper slide 23 thereof.

Auf dem hinteren Spant 5 des Raketenwerfers 1 ist ein Richtaufsatz 17 befestigt, der mit einer Elevationslibelle sowie mit einer Horizontierlibelle versehen ist (nicht näher dargestellt). Am vorderen Spant 4 ist ein Verteilgetriebe 30 angebracht (Fig. 1 und 4), das drei miteinander im Eingriff stehende Kegelräder 31, 32, 33 umfasst, von denen das mittlere Kegelrad 31 einer ersten Antriebswelle 34, die übrigen zwei Kegelräder 32, 33 je einer zwischen dem Raketenwerfer 1 und dem Träger 20 angeordneten verstellbaren Stange 35, 36 zugeordnet sind. Das mittlere Kegelrad 31 ist über ein vorderes Kardangelenk 37 mit einem mittleren, teleskopisch ausgebildeten Teil 38 der ersten Antriebswelle 34 verbunden, der anderseits über ein hinteres Kardangelenk 39 mit einem in einer Bohrung 14 im Kopf 10 der Säule 11 gelagerten Teil 40 der ersten Antriebswelle 34 verbunden ist. Der Teil 40 ist mit einer Kurbel 41 versehen.On the rear frame 5 of the rocket launcher 1, a leveling head 17 is attached, which is provided with an elevation level and with a leveling level (not shown in more detail). A distribution gear 30 (FIGS. 1 and 4) is attached to the front frame 4 and comprises three intermeshing bevel gears 31, 32, 33, of which the central bevel gear 31 of a first drive shaft 34, the other two bevel gears 32, 33 each an adjustable rod 35, 36 arranged between the rocket launcher 1 and the carrier 20. The central bevel gear 31 is connected via a front universal joint 37 to a central, telescopic part 38 of the first drive shaft 34, which on the other hand is connected via a rear universal joint 39 to a part 40 of the first drive shaft 34 mounted in a bore 14 in the head 10 of the column 11 connected is. The part 40 is provided with a crank 41.

Die Stangen 35, 36 weisen jeweils einen Mutterteil 43 bzw. 45 und eine Gewindespindel 44 bzw. 46 auf, die selbsthemmend ausgebildet sind. Beide Stangen 35, 36 sind beispielsweise rechtsgängig ausgebildet und weisen die gleiche Steigung auf. Während die Mutterteile 43 bzw. 45 gemäss Fig. 4 über je ein vorderes Kardangelenk 47, 48 mit den Kegelrädern 32, 33 des Verteilgetriebes 30 verbunden sind, stehen die Gewindespindeln 44, 46 über je ein hinteres Kardangelenk 49, 50 mit je einem hinteren Kegelrad 51, 52 in Antriebsverbindung. Diese die hinteren Enden der Stangen 35, 36 bildenden Kegelräder 51, 52 sind in einem am Träger 20 angeordneten Getriebekasten 53 gelagert. Im Getriebekasten 53 ist ferner eine den beiden hinteren Enden cer Stangen 35, 36 zugeordnete zweite Antriebswelle 54 gelagert, ceren zwei Kegelräder 55, 56 mit dem jeweiligen hinteren Kegelrad 51, 52 im Eingriff stehen (Fig. 4). Der Getriebekasten 53 mit der zweiten Antriebswelle 54 ist nach Fig. 1 bis 3 durch die Wände 18a der Lagerstütze 18 geführt. Ueber ein weiteres rechtwinkliges Kegelradpaar 57, 58 (Fig. 4) ist die zweite Antriebswelle 54 mit einer Kurbel 59 verbunden. Wie in Fig. 4 schematisch strichpunktiert dargestellt, könnte die Antriebselle 54 über ein Kegelradpaar 57, 60 und eine Kupplung 61 auch von einem Servomotor 62 angetrieben werden. Aehnlich könnte auch ein motorischer Antrieb der ersten Antriebswelle 34 realisiert werden, was jedoch einfachheitshalber in der Zeichnung nicht näher dargestellt wird.The rods 35, 36 each have a nut part 43 or 45 and a threaded spindle 44 or 46, which are designed to be self-locking. Both rods 35, 36 are, for example, right-handed and have the same slope. 4 is connected to the bevel gears 32, 33 of the transfer gear 30 via a front universal joint 47, 48, respectively are, the threaded spindles 44, 46 via a rear universal joint 49, 50 each with a rear bevel gear 51, 52 in drive connection. These bevel gears 51, 52 forming the rear ends of the rods 35, 36 are mounted in a gear box 53 arranged on the carrier 20. In the gearbox 53 there is also a second drive shaft 54 associated with the two rear ends of the rods 35, 36, and two bevel gears 55, 56 are engaged with the respective rear bevel gear 51, 52 (FIG. 4). The gear box 53 with the second drive shaft 54 is guided according to FIGS. 1 to 3 through the walls 18a of the bearing support 18. The second drive shaft 54 is connected to a crank 59 via a further right-angled pair of bevel gears 57, 58 (FIG. 4). As shown schematically in dot-dash lines in FIG. 4, the drive shaft 54 could also be driven by a servo motor 62 via a pair of bevel gears 57, 60 and a clutch 61. Similarly, a motor drive of the first drive shaft 34 could also be implemented, but this is not shown in the drawing for the sake of simplicity.

Aus dem beschriebenen Aufbau ergibt sich folgende Wirkungsweise.The following mode of operation results from the structure described.

Vor dem Schiessen wird zuerst mit Hilfe des Richtaufsatzes 17 und des Kreuztisches 22 die den Raketenwerfer 1 tragende und zum Richten des Raketenwerfers 1 dienende Säule 11 ins Lot gelegt.Before firing, the column 11 carrying the rocket launcher 1 and serving to straighten the rocket launcher 1 is first placed vertically with the help of the aiming attachment 17 and the cross table 22.

Die im Kugelgelenk 16 gelagerte Säule 11 wird dabei durch Verstellen des Kreuztisches 22 aus der zentralen Lage nach Fig. 1 und 3 geschwenkt, bis sie.sich wieder im Lot befindet. Bei derart eingestelltem Raketenwerfer 1 sind dann Seite und Höhe am Richtaufsatz 17 in wahrer Grösse ablesbar.The column 11 supported in the ball joint 16 is pivoted by adjusting the cross table 22 from the central position according to FIGS. 1 and 3 until it is again in the vertical position. When the rocket launcher 1 is set in this way, the true size of the side and height can then be read on the alignment attachment 17.

Zum Einstellen eines gewissen Höhenrichtwlnkels wird die erste Antriebswelle 34 über die Kurbel 41 (oder eventuell über den nicht näher dargestellten Servomotor) angetrleben. Das mittlere kegelrad 31 im Verteilgetriebe 30

Figure imgb0001
die beiden übrigen Kegelräder 32, 33 im gleichen Drehsinn an. Ueber die vorderen Kardangelenke 47, 43 werden auch die Mutterteile 43, 45 der beiden Stangen 35, 36 im gleichen Sinne gedreht, was bei der gleichen Steigung der beiden Stangen 35, 36 eine gleichzeitige Längenvergrösserung oder eine gleichzeitige Längenverkärzung derseiben bedeutet - je nach der Drehrichtung der ersten Antriebswelle 34. Dabei wird der Raketenwerfer 1 um die Elevationszapfen 12, 13 des Elevationslagers 15 im Bereich des Winkels λ geschwenkt, wie aus Fig. 1 ersichtlich ist. Die Länge des mittleren Teiles 38 der Welle 34 bleibt im wesentlichen unverändert, durch die teleskopische Ausbildung wird lediglich der sich bei der Schwenkung des Raketenwerfers 1 um die Elevationszapfen 12, 13 leicht verändernde Abstand beider Kardangelenke 37, 39, von denen eins 39 der stehenbleibenden Säule 11 zugeordnet ist, kompensiert. Bei jeder beliebigen Elevation innerhalb des Winkelbereiches λ kann zusätzlich noch der aeitenrichtwinkel in einem bestimmten Winkelbereich ]δ geändert werden. Dazu wird die zweite Antriebswelle 54 über die Kurbel 59 oder über den Servomotor 62 angetrieben. Währene das Drehen der zweiten Antriebswelle 54 im einen Drehsina über die Kegelräder 55, 51 und das hintere Kardangelenk 49 ein Drehen der einen Gewindespincel 44 in einem die Längenvergrösserung der Stange 35 bedeutenden Sinne bewirkt, wird gleichzeitig die Gewindespindel 46 der anderen Stange über die Kegelräder 56, 52 und das Kardangelenk 50 im umgekehrten Drehsinn angetrieben, d.h. die Länge der Stange 36 wird verkürzt. Demzufolge wird der Raketenwerfer 1 in einem in Fig. 2 dargestellten Sinne aus der zentralen Stellung seitlich um die Achse der Säule 11 im Bereich des Winkels β/2 geschwenkt.In order to set a certain height directional angle, the first drive shaft 34 is driven on via the crank 41 (or possibly via the servomotor (not shown in more detail)). The middle bevel gear 31 in the distribution gear 30
Figure imgb0001
the other two bevel gears 32, 33 in the same direction. About the front universal joints 47, 43, the nut parts 43, 45 of the two rods 35, 36 are rotated in the same sense, which means a simultaneous increase in length or a simultaneous lengthening of the disks at the same slope of the two rods 35, 36 - depending on the direction of rotation the first drive shaft 34. The rocket launcher 1 is pivoted about the elevation pins 12, 13 of the elevation bearing 15 in the region of the angle λ, as can be seen from FIG. 1. The length of the middle part 38 of the shaft 34 remains essentially unchanged, the telescopic design only makes the distance between the universal joints 37, 39, which changes slightly when the rocket launcher 1 is pivoted about the elevation pins 12, 13, one of which 39 the stationary column 11 is assigned, compensated. With any elevation within the angular range λ, the directional angle can also be changed in a specific angular range] δ. For this purpose, the second drive shaft 54 is driven via the crank 59 or via the servo motor 62. While the rotation of the second drive shaft 54 in one rotation via the bevel gears 55, 51 and the rear universal joint 49 causes the one threaded spindle 44 to rotate in a manner that is significant in terms of the length increase of the rod 35, the threaded spindle 46 of the other rod becomes simultaneously via the bevel gears 56 , 52 and the universal joint 50 driven in the opposite direction, ie the length of the rod 36 is shortened. Accordingly, the rocket launcher 1 is pivoted in the sense shown in FIG. 2 from the central position laterally about the axis of the column 11 in the range of the angle β / 2.

Claims (5)

triebe (30) aufweist, in welchem drei miteinander im Eingriff stehende Kegelräder (31, 32, 33) gelagert sice, von denen zwei (32, 33) über je ein vorderes Fardangelenk (47 bzw. 48) mit dem jeweiligen Mutterteil (42 bzw. 45) verbunden sind und das mittlere Kegelrad (31) über ein vorderes Kardangelenk (37) mit einer erster Antriebswelle (34) verbanden ist.has drives (30), in which three intermeshing bevel gears (31, 32, 33) are mounted, of which two (32, 33) each have a front joint (47 or 48) with the respective nut part (42 or . 45) are connected and the central bevel gear (31) is connected to a first drive shaft (34) via a front universal joint (37). 5. Vorrichting nach Ansprun 3, dadurch gekennzeichnet, dass die zweite Antriebsvorrichtung (54, 51, 52) eine den hinteren Enden der beiden Stangen (35, 36) zugeordnete zweite Antriebswelle (54) aufweist, die mit zwei Kegelrädern (55, 56) versehen ist, die jeweils mit einem über ein hinteres Kardangelenk (49, 50) mit der jeweiligen Gewindespindel (44 bzw. 46) verbundenen Hinteren Kegelrad (51, 52) im Eingriff sind.5. Device according to Claim 3, characterized in that the second drive device (54, 51, 52) has a second drive shaft (54) assigned to the rear ends of the two rods (35, 36), which has two bevel gears (55, 56) is provided, which are each in engagement with a rear bevel gear (51, 52) connected to the respective threaded spindle (44 or 46) via a rear universal joint (49, 50). 6. Vorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass die Lagerstütze (18) eine Kugelgelenklagerung (16) für eine einen Elevationszapfen (12, 13) tragende Säule (11) aufweist, die mit einer Bohrung (14) versehen ist, in welcher ein Teil (40) der ersten Antriebswelle (34) gelagert ist.6. The device according to claim 4, characterized in that the bearing support (18) has a ball and socket bearing (16) for an elevation pin (12, 13) carrying column (11) which is provided with a bore (14) in which a Part (40) of the first drive shaft (34) is mounted. 7. Vorrichtung nach Anspruch 5, dadurch gekennzeichnet, dass die zweite Antriebswelle (54) sowie die hinteren Kegelräder (51, 52) der Stangen (35, 36) in einem am Träger (20) angeordneten, durch die Lagerstütze (18) geführten Getriebekasten (53) gelagert sind.7. The device according to claim 5, characterized in that the second drive shaft (54) and the rear bevel gears (51, 52) of the rods (35, 36) in a arranged on the carrier (20) through the bearing support (18) guided gear box (53) are stored. 8. Vorrichtung nach Anspruch 6, dadurch gekennzeichnet, dass in der Lagerstütze (18) parallel zum Träger (20) eine Tragplatte (21) mit einem verstellbaren Kreuztisch (22) angeordnet ist, in den die Säule (11) hineinragt.8. The device according to claim 6, characterized in that in the bearing support (18) parallel to the carrier (20), a support plate (21) is arranged with an adjustable cross table (22) into which the column (11) protrudes.
EP19790105363 1979-01-11 1979-12-24 Device for supporting and aiming an indirect firing weapon Expired EP0013422B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH24979 1979-01-11
CH249/79 1979-01-11

Publications (2)

Publication Number Publication Date
EP0013422A1 true EP0013422A1 (en) 1980-07-23
EP0013422B1 EP0013422B1 (en) 1982-05-26

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19790105363 Expired EP0013422B1 (en) 1979-01-11 1979-12-24 Device for supporting and aiming an indirect firing weapon

Country Status (3)

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EP (1) EP0013422B1 (en)
DE (1) DE2962973D1 (en)
ES (1) ES487581A0 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2609331A1 (en) * 1987-01-07 1988-07-08 Soucaze Soudat Jean Adjustable launcher mount for avalanche-inducing projectiles
GB2249823A (en) * 1990-11-08 1992-05-20 Horstman Defence Syst Gun elevation mechanism
FR2698438A1 (en) * 1992-11-26 1994-05-27 Bofors Ab Multi-tube mortar - has tubes pivoted so support, capable of being aimed separately and fired together or in sequence
EP1113239A3 (en) * 1999-12-29 2002-07-17 Ordnance Development & Engineering Company of Singapore (1996) Pte Ltd. Improvements to artillery firing system
WO2009136135A1 (en) * 2008-04-14 2009-11-12 Bae Systems Plc. Field gun
US8291809B2 (en) 2008-04-14 2012-10-23 Bae Systems Plc Field gun

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR575488A (en) * 1923-02-13 1924-07-30 Schneider & Cie Dismountable artillery equipment for accompanying infantry troops
US1723623A (en) * 1926-04-14 1929-08-06 William Q Kennedy Self-centered, nonsighted, second-of-time gun
US2208015A (en) * 1937-10-29 1940-07-16 Cecil P Caulkins Gun mounting
US2380024A (en) * 1941-08-15 1945-07-10 Edward F Chandler Rocket gun
FR2112910A5 (en) * 1970-08-06 1972-06-23 Sarmac Sa

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR575488A (en) * 1923-02-13 1924-07-30 Schneider & Cie Dismountable artillery equipment for accompanying infantry troops
US1723623A (en) * 1926-04-14 1929-08-06 William Q Kennedy Self-centered, nonsighted, second-of-time gun
US2208015A (en) * 1937-10-29 1940-07-16 Cecil P Caulkins Gun mounting
US2380024A (en) * 1941-08-15 1945-07-10 Edward F Chandler Rocket gun
FR2112910A5 (en) * 1970-08-06 1972-06-23 Sarmac Sa

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2609331A1 (en) * 1987-01-07 1988-07-08 Soucaze Soudat Jean Adjustable launcher mount for avalanche-inducing projectiles
GB2249823A (en) * 1990-11-08 1992-05-20 Horstman Defence Syst Gun elevation mechanism
FR2698438A1 (en) * 1992-11-26 1994-05-27 Bofors Ab Multi-tube mortar - has tubes pivoted so support, capable of being aimed separately and fired together or in sequence
EP1113239A3 (en) * 1999-12-29 2002-07-17 Ordnance Development & Engineering Company of Singapore (1996) Pte Ltd. Improvements to artillery firing system
WO2009136135A1 (en) * 2008-04-14 2009-11-12 Bae Systems Plc. Field gun
US8291809B2 (en) 2008-04-14 2012-10-23 Bae Systems Plc Field gun

Also Published As

Publication number Publication date
ES8102318A1 (en) 1980-12-16
EP0013422B1 (en) 1982-05-26
DE2962973D1 (en) 1982-07-15
ES487581A0 (en) 1980-12-16

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