EP2754989B1 - Device and method for aiming a rocket launcher container - Google Patents
Device and method for aiming a rocket launcher container Download PDFInfo
- Publication number
- EP2754989B1 EP2754989B1 EP14150441.5A EP14150441A EP2754989B1 EP 2754989 B1 EP2754989 B1 EP 2754989B1 EP 14150441 A EP14150441 A EP 14150441A EP 2754989 B1 EP2754989 B1 EP 2754989B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- lifting element
- height
- container
- directing part
- rocket
- 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.)
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- 238000000034 method Methods 0.000 title claims description 12
- 230000005484 gravity Effects 0.000 claims description 20
- 238000010304 firing Methods 0.000 claims description 17
- 235000015842 Hesperis Nutrition 0.000 claims description 4
- 235000012633 Iberis amara Nutrition 0.000 claims description 4
- 230000006735 deficit Effects 0.000 description 7
- 230000002411 adverse Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000003028 elevating effect Effects 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 4
- 239000012080 ambient air Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000007788 roughening Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000008685 targeting Effects 0.000 description 1
Images
Classifications
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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
- F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
- F41A23/20—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles for disappearing guns
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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
- F41A23/00—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
- F41A23/34—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles
- F41A23/42—Gun mountings, e.g. on vehicles; Disposition of guns on vehicles on wheeled or endless-track vehicles for rocket throwers
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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
- F41A27/22—Traversing gear
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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
- F41A27/24—Elevating gear
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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
- F41A27/26—Fluid-operated systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
Definitions
- the invention relates to a device for directing a missile launching container with a side straightening member and a height-straightening member arranged on the side straightening member for receiving the rocket launching container. Further objects of the invention are a launching device with such a device and a method for straightening a rocket launching container with a side straightening part and a height straightening part arranged on the side straightening part for receiving the rocket launching container.
- Such a device for directing a rocket launcher, as well as a method for directing the rocket launcher are from the DE 1 259 737 B known.
- mobile missile launcher containers are used which are arranged, for example, on chain or wheeled transport vehicles.
- the rocket launcher containers are initially roughly aligned from a more compact transport position until a directional position is reached, in which the rocket launcher and thus the rockets stored in it are in a certain advance direction. If, for example, a target to be combated is detected via a radar sensor, the rocket launching container is again finely directed out of this directional position until a precisely aligned firing position is reached. This type of coarse alignment followed by fine tuning is widely used to reduce the time between detection and targeting.
- the straightening devices used for this purpose have a side straightening part and a height straightening part arranged on the side straightening part.
- the side facing part is usually arranged on a transport platform of a transport vehicle and can be aligned laterally about a substantially vertically extending azimuth aiming axis.
- the height-adjusting part is mounted elevably on the side-facing part about an elevation-straightening axis extending substantially horizontally and serves to receive the rocket-launching container.
- the elevation aiming axis is usually arranged in the rear end region of the elevation direction part or of the rocket launching container arranged on the elevation direction part near the transport platform. At low elevation angles can thereby be reach a compact transport position. At the same time resulting in the firing of, for example, unguided missile exhaust jets can be guided laterally past the transport platform, whereby greater impairment of the transport platform can be avoided.
- the rocket launcher on the elevating part relative to the elevation axis to accommodate movable.
- the straightening device can be converted with relatively little effort from the transport position in the directional position.
- the rocket launcher is initially moved axially.
- the center of gravity of the rocket launcher is approximately in the area of the elevation directional axis, the elevation direction part and with it the rocket launcher is raised with comparatively little effort.
- the rocket launcher is moved back axially, after which then the directional position of the rocket launcher is reached.
- This directing position forms a kind of pre-alignment, from which the missile launching container can now be fine-tuned in the case of target recognition.
- the object of the present invention is to specify an apparatus and a method for aligning a rocket launcher, which are characterized by good transport properties and low firing impairments with simultaneously improved orientation properties.
- the lifting element By arranged on the side straightening lifting element can be easily realized good transport properties and low launching impairments at the same time low directional moments. By operating the lifting element, it is possible to convert the straightening device for transport purposes in a compact transport position. At the same time, the elevation aiming axis can be located near the center of gravity of the rocket launcher, resulting in good directional properties throughout the aiming process. In addition, by raising themaynrichtteils the adverse effects of rocket firing can be minimized.
- the lifting element is designed as a pivotable setting lever.
- the straightening device By pivoting the lifting element designed as a lifting lever, the straightening device can be transferred by simple means from its more compact transport position in the straightening position, from which the rocket launcher then with low Force can be directed to a target to be combated.
- the satisfactionnrichtteil can be raised not only by setting up the deployment lever relative to the transport platform, but also displaced laterally, whereby the risk of adverse effects on the transport platform during the firing drops further.
- the side facing part has an azimuth straightening platform.
- the free space above the azimuth straightening platform can be used, for example, for pivoting the launching container.
- the remaining components of the device above the azimuth straightening platform can be folded folded to achieve a compact transport position.
- one end of the lifting element is articulated on the azimuth straightening platform and the other end of the lifting element on the elevation direction part.
- the device can be by Jacobverschwenken of the lifting element and thedoinrichtteils spend in a compact, in particular folded position.
- the lifting element can be pivoted via a linear drive.
- a linear drive in particular electromotive drives can be used.
- the linear drive is articulated at one end to the azimuth straightening platform and at the other end to the lifting element.
- the articulation of the linear drive on the lifting element can in the range between the articulation of the lifting element on the azimuth straightening platform and the articulation of the lifting element on theCNnrichtteil respectively. Due to the leverage ratios Hubelement facede the end of the linear drive should be as high as possible attack on the lifting element, ie as far away from the articulation of the lifting element on the azimuth straightening platform.
- the articulated connection of the linear drive allows pivoting relative to the lifting element and the azimuth straightening platform, whereby in the transport position, a compact, in particular folded position can be achieved.
- the lifting element is designed to be telescopic.
- a pivoting stroke and a Teleskopierhub be added to a larger total stroke, wherein the pivoting and Teleskopierfest the lifting element either superimposed or can be performed sequentially.
- the lifting element can be telescoped via a linear drive.
- the lifting element may have two telescopic rods, wherein the linear drive is connected at one end to one telescopic rod and at the other end to the other telescopic rod.
- two lifting elements are provided, which together form a fork receptacle for the height-adjusting part. Due to the parallel arrangement of two lifting elements results in a fork with a free center area for the height-elevation part, in which thestinrichtteil and on theNOnrichtteil arranged missile launchers can pivot freely, so that there is a large elevation directing range. Also results in a symmetrical power dissipation over the arranged on both sides of the elevating part lifting elements.
- the Elevationsrichtachse extends near the center of gravity of the aufmunition vigilant rocket launcher. In the optimal case, the Elevationsrichtachse extends through the center of gravity of the aufmunition entertaining rocket launcher. However, this will not always be possible in practice due to different missile launchers and ammunition types. Therefore, an embodiment is preferred in which the elevation directional axis of the elevation direction part extends through a center of gravity corridor of the rocket launching container enclosing the center of gravity of the ammunition launching missile launching container, which extends transversely to its launch direction.
- the width of the launcher corridor corresponds to the height of the rocket launcher, preferably three quarters of the height of the launcher launcher, and more preferably half the height of the launcher launcher. Due to the course of the elevation directing axis through this gravity corridor, the directional moments during elevation of the rocket launching container during the entire straightening process can be kept comparatively low.
- the side facing part is arranged on a transport platform, wherein the lifting element the side directing part is arranged such that an exhaust jet resulting from missile firing passes past the transport platform at an elevation angle of the elevation portion of up to 45 degrees, preferably up to 60 degrees, more preferably up to 70 degrees.
- the exhaust jet for example, when shooting short-range missiles, will not be kept completely away from the transport platform in practice due to its rearwardly widening exhaust angle and the turbulence occurring in the ambient air, etc. in practice.
- the exhaust gas jet in the sense of the present invention is understood to mean the geometric extension of the rocket launching container counter to the firing direction, as a result of which the essential parts of the exhaust gas jet are also guided past the transport platform in practice.
- the object of the independent method claim 11 is proposed to solve the above-mentioned problem.
- FIG. 1 shows in perspective view a launcher 50 for firing missiles from a rocket having multiple rocket launcher 20.
- the missiles to be fired from the launching container 20 are missiles with their own drive, which can be designed differently, for example as steered or unguided missiles, as short-range missiles or similar missiles.
- Such launchers 50 are often used in crisis areas, in which they are often used at different locations, and consist essentially of a arranged on a transport platform 51 straightening device 1 for straightening the rocket launcher 20th
- the launching device 50 is arranged within a transport container 52, which consists of a removable hood 53 and a container floor 51 forming the transport platform 51 of the straightening device. It is a standardized transport container 52, which can be transported with very different transport vehicles, such as trucks, airplanes, ships, etc.
- the launching device can be used either directly on the transport vehicle, so for example a truck or a ship, or in this remote position after transport to their place of use.
- Fig. 1 shows the transport position of the launching device 50, in which the straightening device 1 occupies a more compact position so that it can be accommodated within the container 52.
- a self-propelled gun directly on a transport vehicle, such as a chain or wheel-driven military vehicle.
- the straightening device according to the invention 1 is characterized in particular by good transport properties, low launching impact on the missile missile and simultaneously improved directional properties, including a lifting element 4 is provided for raising and lowering the rocket launcher 20. This will be explained below with reference to the figures in detail.
- the rocket launching container 20 designed as a replaceable launching container is in a substantially horizontal position in the interior of the container 52.
- the straightening device 1 assumes a very compact position, so that both the Straightening device 1 as well as the replaceable arranged on this rocket launcher 20 can be accommodated within the container 52.
- the hood 53 of the container is first removed from the container floor serving as a transport platform 51.
- the rocket launcher 20 is in this position still in a horizontal orientation within the contour of the container 51.
- a storage space 54 within the container 52. This is approximately in cross section L-shaped geometry and as well as the straightening device 1 arranged on the transport platform 51.
- various devices for operating the launcher 50 such as an aggregate for power generation, electrical control and regulation components for the leveling system, electronic components, etc., or other objects such as tools, lubricants or the like, are arranged.
- the straightening device 1 In the area between the transport platform 51 and the rocket launcher 20, the straightening device 1 can be seen in a compact folded position.
- the straightening device 1 has as its essential components a side straightening part 2 and a height straightening part 3.
- the side-facing part 2 is around the in Fig. 3 schematically drawn, vertically extending azimuth straightening axis A side aligned.
- the side straightening part 2 has a plate-shaped or frame-shaped azimuth straightening platform 5 and at this two lifting elements 4.
- the lifting elements 4 are pivotally coupled in the region of one end 4.1 with the azimuth straightening platform 5 and in the region of its other end 4.2 with the elevation direction part 3.
- the height-adjusting part 3 is around the in Fig. 3 also schematically drawn Elevationsrichtachse E Bibnrichtbar arranged on the side facing part 2.
- the elevation part 3 serves to receive the rocket rocket launcher 20 and is of approximately U-shaped cross-section.
- the height-straightening part 3 forms a kind of cradle-shaped receptacle for the rocket launching container 20, which in the exemplary embodiment is of approximately cuboid or box-shaped geometry and serves for receiving a plurality of rockets, which are not shown in detail in the figures.
- the Elevationsrichtachse E ofstates 3 runs through the center of gravity of the aufmunition striv rocket launcher 20, resulting in a favorable directional response with only small directional moments.
- the lifting elements 4 are for this purpose designed as active lifting elements 4, which can be transferred automatically under supply of electrical energy in a stroke position.
- the lifting elements 4 are formed as a pivotable raising lever, which are coupled to a first pivot axis S 1 on the azimuth straightening platform 5 and about a second pivot axis S 2 pivotally connected to the elevation direction part 3.
- pivoting the lifting elements 4 takes the height-adjusting part 3 and with this the rocket launcher 20 in the FIGS. 5 and 6 shown, compared to the previously described transport position elevated intermediate position.
- Each lifting element 4 is assigned its own linear actuator 6.
- the one end 6.1 of the linear drives 6 is hinged to the azimuth straightening platform 5.
- the other end 6.2 of the linear drives 6 is articulated on the lifting element 4.
- the position of the hub element-side linkage is chosen such that it acts as high as possible on the lifting element 4, resulting in favorable leverage ratios.
- the lifting elements 4 are pivoted in a substantially vertical position.
- the rocket launcher 20 is laterally displaced in the direction of the edge of the transport platform 51, whereby the adverse effects of the transport platform 51 can be kept low during rocket launch.
- the lifting elements 4 are also designed to be telescopic.
- the lifting elements 4 have two telescopic elements 4.3, 4.4 arranged telescopically relative to one another.
- the telescopic element 4.3 as a rod
- the lifting element 4.4 designed as a male element.
- the lifting element 4 serve linear actuators 7, which are arranged mitschwenkend on the lifting elements 4.
- Each lifting element 4 is associated with a linear drive 7 for telescoping.
- the one end 7.1 of the linear drive 7 is coupled to the one telescopic element 4.4 and the other end 7.2 of the linear drive 7 with the other telescopic element 4.3, so that the two telescopic elements 4.3, 4.4 by pressing the linear drive 7 against each other are telescoped.
- the telescopic elements are 4.3, 4.4 extended against each other, so that in addition to the swing stroke SH results in a Teleskopierhub TH, which add up to a total lift GH, as in Fig. 8 is illustrated.
- the leveling member 3 is raised and the rocket launcher 20 has reached its upper stroke position.
- the rocket-launching container 20 is then brought into its directional position.
- the Richt ein is in the FIGS. 9 and 10 shown.
- the straightening device 1 is already in a rough direction corresponding to the expected destination. If, for example, such a target is detected, for example via a radar sensor or similar means of reconnaissance, and it is decided that this target is to be combated, the fine-tuning of the rocket launching container 20 is likewise carried out via the straightening device 1 in a further step.
- the gravity center K extends from one side of the rocket launcher 20 to the opposite and includes the center of gravity of the ammunition launch missile 20 so that the elevation aiming axis is near the center of gravity.
- the Elevationsrichtachse E passes through the center of gravity of the aufmunition convinced rocket launcher 20, resulting in a balanced arrangement with correspondingly favorable directional properties. Since this is difficult to implement in practice with ultimate precision, especially in the case of replaceable rocket launcher 20 with different types of Rakten, it is provided that the Elevationsrichtachse E extends at least within the center of gravity corridor K.
- the centroid corridor K of the rocket launcher 20 is that area which is in Fig. 10 is bordered by a dashed line.
- the center of gravity corridor K extends transversely to the firing direction S of the rocket launcher 20.
- the width B of the center of gravity K in the embodiment is selected such that it corresponds to the height H of the rocket launcher 20.
- the width of the center of gravity corridor K can also be made narrower, so that the width B preferably corresponds to three quarters of the height H, more preferably half the height H or even lower portions of the height H of the rocket launcher.
- the side straightening member 2 is formed and arranged on the transport platform 51, that even at elevation angles of theginanrichtteils of up to 45 degrees, more preferably up to 60 degrees and more preferably up to 70 degrees, the geometric exhaust jet A is guided past the transport platform 51, whereby In practice, appreciable parts of the exhaust gas jet are passed to this.
- the straightening device 1 has an elevation adjustment range of 0 ° to 90 °.
- the two lifting elements 4 of the side directing part 2 form between them a kind of fork receptacle, within which the elevation-straightening part 3 and the rocket-launching container 20 arranged on it are arranged so as to be virtually freely rotatable.
- the straightening device according to the invention is characterized by a compact transport position, low influences the transport platform and favorable directional properties, which is achieved by the arranged on the side facing part 2 lifting element 4.
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- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Toys (AREA)
Description
Die Erfindung betrifft eine Vorrichtung zum Richten eines Raketenabschussbehälters mit einem Seitenrichtteil und einem an dem Seitenrichtteil angeordneten Höhenrichtteil zur Aufnahme des Raketenabschussbehälters. Weitere Gegenstände der Erfindung bilden eine Abschussvorrichtung mit einer solchen Vorrichtung sowie ein Verfahren zum Richten eines Raketenabschussbehälters mit einem Seitenrichtteil und einem an dem Seitenrichtteil angeordneten Höhenrichtteil zur Aufnahme des Raketenabschussbehälters.The invention relates to a device for directing a missile launching container with a side straightening member and a height-straightening member arranged on the side straightening member for receiving the rocket launching container. Further objects of the invention are a launching device with such a device and a method for straightening a rocket launching container with a side straightening part and a height straightening part arranged on the side straightening part for receiving the rocket launching container.
Eine solche Vorrichtung zum Richten eines Raketenabschussbehälters, sowie ein Verfahren zum Richten des Raketenabschussbehälters sind aus der
Vor dem Verschießen werden die Raketenabschussbehälter aus einer kompakteren Transportstellung zunächst grob gerichtet bis eine Richtstellung erreicht ist, in welcher sich der Raketenabschussbehälter und damit die in diesem bevorrateten Raketen in einer bestimmten Vorausrichtung befinden. Wird nun beispielsweise über einen Radarsensor ein zu bekämpfendes Ziel erkannt, wird der Raketenabschussbehälter aus dieser Richtstellung heraus noch einmal fein gerichtet bis eine exakt ausgerichtete Abschussstellung erreicht ist. Diese Art des Grobrichtens mit anschließendem Feinrichten ist zur Reduktion der Zeit zwischen der Erkennung und der Bekämpfung eines Ziels weit verbreitet.Before firing, the rocket launcher containers are initially roughly aligned from a more compact transport position until a directional position is reached, in which the rocket launcher and thus the rockets stored in it are in a certain advance direction. If, for example, a target to be combated is detected via a radar sensor, the rocket launching container is again finely directed out of this directional position until a precisely aligned firing position is reached. This type of coarse alignment followed by fine tuning is widely used to reduce the time between detection and targeting.
Die hierzu verwendeten Richtvorrichtungen weisen ein Seitenrichtteil und ein an dem Seitenrichtteil angeordnetes Höhenrichtteil auf. Das Seitenrichtteil ist üblicherweise auf einer Transportplattform eines Transportfahrzeugs angeordnet und um eine sich im Wesentlichen vertikal erstreckende Azimutrichtachse seitlich richtbar. Das Höhenrichtteil ist an dem Seitenrichtteil um eine sich im Wesentlichen horizontal erstreckende Elevationsrichtachse elevierbar gelagert und dient zur Aufnahme des Raketenabschussbehälters.The straightening devices used for this purpose have a side straightening part and a height straightening part arranged on the side straightening part. The side facing part is usually arranged on a transport platform of a transport vehicle and can be aligned laterally about a substantially vertically extending azimuth aiming axis. The height-adjusting part is mounted elevably on the side-facing part about an elevation-straightening axis extending substantially horizontally and serves to receive the rocket-launching container.
Da die Richtvorrichtung während des Transports eine möglichst kompakte Stellung einnehmen soll und Beeinträchtigungen der Transportplattform beim Verschießen der Raketen möglichst vermieden werden sollen, wird die Elevationsrichtachse zumeist im hinteren Endbereich des Höhenrichtteils bzw. des auf dem Höhenrichtteil angeordneten Raketenabschussbehälters nahe der Transportplattform angeordnet. Bei geringen Elevationswinkeln lässt sich hierdurch eine kompakte Transportstellung erreichen. Gleichzeitig können die sich beim Verschießen von beispielsweise ungelenkten Raketen ergebenden Abgasstrahlen seitlich an der Transportplattform vorbei geführt werden, wodurch größere Beeinträchtigung der Transportplattform vermieden werden.Since the straightening device should occupy as compact a position as possible during transport and impairments of the transport platform should be avoided as far as possible when launching the missiles, the elevation aiming axis is usually arranged in the rear end region of the elevation direction part or of the rocket launching container arranged on the elevation direction part near the transport platform. At low elevation angles can thereby be reach a compact transport position. At the same time resulting in the firing of, for example, unguided missile exhaust jets can be guided laterally past the transport platform, whereby greater impairment of the transport platform can be avoided.
Durch die weit hinten liegende Anordnung der Elevationsrichtachse ergibt sich bei herkömmlichen Richtvorrichtungen jedoch der Nachteil, dass zum Richten des Raketenabschussbehälters vergleichsweise große Richtmomente zu überwinden sind. Insoweit sind die zum Elevieren verwendeten Motor- und Getriebekomponenten vergleichsweise groß zu dimensionieren und es ergeben sich zudem vergleichsweise lange Richtzeiten.Due to the arrangement of the elevation aiming axis, which is located far to the rear, however, the disadvantage arises in conventional straightening devices that comparatively large straightening moments have to be overcome for straightening the rocket launching container. In that regard, the engine and transmission components used for lifting are to be dimensioned comparatively large and it also results in comparatively long shot times.
Aus der
Bei dieser Richtvorrichtung werden durch die in der Abschussstellung weit hinten liegende Elevationsrichtachse Beeinträchtigungen der Transportplattform zwar vermieden und der Kraftaufwand beim Grobrichten gering gehalten, als nachteilig hat sich jedoch erwiesen, dass die Richtmomente beim Feinrichten vergleichsweise groß und die entsprechenden Richtzeiten vergleichsweise lang sind.In this straightening device impairments of the transport platform are caused by the elevation pointing axis, which is located far behind in the firing position Although avoided and kept the effort required for coarse roughening low, but has proved to be disadvantageous that the directional moments when fine tuning comparatively large and the corresponding set times are relatively long.
Aufgabe der vorliegenden Erfindung ist es, eine Vorrichtung und ein Verfahren zum Richten eines Raketenabschussbehälters anzugeben, welche sich durch gute Transporteigenschaften und geringe Abschussbeeinträchtigungen bei gleichzeitig verbesserten Richteigenschaften auszeichnen. The object of the present invention is to specify an apparatus and a method for aligning a rocket launcher, which are characterized by good transport properties and low firing impairments with simultaneously improved orientation properties.
Diese Aufgabe wird bei einer Vorrichtung der eingangs genannten Art durch die Merkmale des unabhängigen Anspruches 1 gelöst. Durch das an dem Seitenrichtteil angeordnete Hubelement lassen sich auf einfache Art und Weise gute Transporteigenschaften und geringe Abschussbeeinträchtigungen bei gleichzeitig geringen Richtmomenten realisieren. Durch Betätigung des Hubelements ist es möglich, die Richtvorrichtung zu Transportzwecken in eine kompakte Transportstellung zu überführen. Gleichzeitig kann die Elevationsrichtachse nahe dem Schwerpunkt des Raketenabschussbehälters angeordnet werden, wodurch sich während des gesamten Richtvorgangs gute Richteigenschaften ergeben. Zudem lassen sich durch das Anheben des Höhenrichtteils die Beeinträchtigungen beim Verschießen der Raketen gering halten. Nach unabhängigem Anspruch 1 ist das Hubelement als schwenkbarer Aufstellhebel ausgebildet. Durch Verschwenken des als Aufstellhebel ausgebildeten Hubelements kann die Richtvorrichtung mit einfachen Mitteln aus deren kompakterer Transportstellung in die Richtstellung überführt werden, aus welcher der Raketenabschussbehälter dann mit geringem Kraftaufwand auf ein zu bekämpfendes Ziel gerichtet werden kann. Zudem kann das Höhenrichtteil durch Aufstellen des Aufstellhebels gegenüber der Transportplattform nicht nur angehoben, sondern auch seitlich verlagert werden, wodurch die Gefahr von Beeinträchtigungen der Transportplattform während der Schussabgabe weiter sinkt.This object is achieved in a device of the type mentioned by the features of independent claim 1. By arranged on the side straightening lifting element can be easily realized good transport properties and low launching impairments at the same time low directional moments. By operating the lifting element, it is possible to convert the straightening device for transport purposes in a compact transport position. At the same time, the elevation aiming axis can be located near the center of gravity of the rocket launcher, resulting in good directional properties throughout the aiming process. In addition, by raising the Höhenrichtteils the adverse effects of rocket firing can be minimized. According to independent claim 1, the lifting element is designed as a pivotable setting lever. By pivoting the lifting element designed as a lifting lever, the straightening device can be transferred by simple means from its more compact transport position in the straightening position, from which the rocket launcher then with low Force can be directed to a target to be combated. In addition, the Höhenrichtteil can be raised not only by setting up the deployment lever relative to the transport platform, but also displaced laterally, whereby the risk of adverse effects on the transport platform during the firing drops further.
Von konstruktivem Vorteil ist ferner eine Ausgestaltung, bei welcher das Seitenrichtteil eine Azimut-Richtplattform aufweist. Durch die in vertikaler Richtung vergleichsweise flache Ausbildung der Azimut-Richtplattform kann der Freiraum oberhalb der Azimut-Richtplattform beispielsweise zum Verschwenken des Abschusscontainers genutzt werden. Auch können die übrigen Bauteile der Vorrichtung oberhalb der Azimut-Richtplattform zusammengeklappt angeordnet werden, um eine kompakte Transportstellung zu erreichen.Of constructive advantage is also an embodiment in which the side facing part has an azimuth straightening platform. By virtue of the comparatively flat design of the azimuth straightening platform in the vertical direction, the free space above the azimuth straightening platform can be used, for example, for pivoting the launching container. Also, the remaining components of the device above the azimuth straightening platform can be folded folded to achieve a compact transport position.
In diesem Zusammenhang ist es ferner von Vorteil, wenn ein Ende des Hubelements an der Azimut-Richtplattform und das andere Ende des Hubelements an dem Höhenrichtteil angelenkt ist. Auf diese Weise lässt sich die Vorrichtung durch Gegeneinanderverschwenken des Hubelements und des Höhenrichtteils in eine kompakte, insbesondere zusammengeklappte Stellung verbringen.In this context, it is also advantageous if one end of the lifting element is articulated on the azimuth straightening platform and the other end of the lifting element on the elevation direction part. In this way, the device can be by Gegeneinanderverschwenken of the lifting element and the Höhenrichtteils spend in a compact, in particular folded position.
Ferner wird vorgeschlagen, dass das Hubelement über einen Linearantrieb verschwenkbar ist. Als Linearantrieb können insbesondere elektromotorische Antriebe verwendet werden.It is also proposed that the lifting element can be pivoted via a linear drive. As a linear drive in particular electromotive drives can be used.
In diesem Zusammenhang ist es von Vorteil, wenn der Linearantrieb mit einem Ende an der Azimut-Richtplattform und mit dem anderen Ende an dem Hubelement angelenkt ist. Die Anlenkung des Linearantriebs an dem Hubelement kann im Bereich zwischen der Anlenkung des Hubelements an der Azimut-Richtplattform und der Anlenkung des Hubelements an dem Höhenrichtteil erfolgen. Aufgrund der Hebelverhältnisse sollte das hubelementseitige Ende des Linearantriebs möglichst hoch an dem Hubelement angreifen, d. h. möglichst weit entfernt von der Anlenkung des Hubelements an der Azimut-Richtplattform. Die gelenkige Anbindung des Linearantriebs erlaubt ein Verschwenken gegenüber dem Hubelement und der Azimut-Richtplattform, wodurch in der Transportstellung eine kompakte, insbesondere zusammengeklappte Stellung erreichbar ist. Nach unabhängigem Anspruch 1 ist das Hubelement teleskopierbar ausgebildet. Durch Teleskopieren des Hubelements lassen sich auch größere Hübe überwinden, so dass das Höhenrichtteil in der Richt- bzw. Abschussstellung eine Position vergleichsweise hoch über der Transportplattform einnehmen kann. Nach unabhängigem Anspruch 1 werden ein Schwenkhub und ein Teleskopierhub zu einem größeren Gesamthub addiert, wobei die Schwenk- und Teleskopierbewegung des Hubelements entweder überlagert oder nacheinander durchgeführt werden können.
In diesem Zusammenhang ist es ferner von Vorteil, wenn das Hubelement über einen Linearantrieb teleskopierbar ist. Das Hubelement kann zwei Teleskopstangen aufweisen, wobei der Linearantrieb mit einem Ende an der einen Teleskopstange und mit dem anderen Ende mit der anderen Teleskopstange angebunden ist.In this context, it is advantageous if the linear drive is articulated at one end to the azimuth straightening platform and at the other end to the lifting element. The articulation of the linear drive on the lifting element can in the range between the articulation of the lifting element on the azimuth straightening platform and the articulation of the lifting element on the Höhenrichtteil respectively. Due to the leverage ratios Hubelementseitige the end of the linear drive should be as high as possible attack on the lifting element, ie as far away from the articulation of the lifting element on the azimuth straightening platform. The articulated connection of the linear drive allows pivoting relative to the lifting element and the azimuth straightening platform, whereby in the transport position, a compact, in particular folded position can be achieved. According to independent claim 1, the lifting element is designed to be telescopic. By telescoping the lifting element, even larger strokes can be overcome, so that the height-reflecting part can assume a position comparatively high above the transport platform in the directional or firing position. According to independent claim 1, a pivoting stroke and a Teleskopierhub be added to a larger total stroke, wherein the pivoting and Teleskopierbewegung the lifting element either superimposed or can be performed sequentially.
In this context, it is also advantageous if the lifting element can be telescoped via a linear drive. The lifting element may have two telescopic rods, wherein the linear drive is connected at one end to one telescopic rod and at the other end to the other telescopic rod.
Vorteilhafterweise sind zwei Hubelemente vorgesehen, die gemeinsam eine Gabelaufnahme für das Höhenrichtteil bilden. Durch die parallele Anordnung zweier Hubelemente ergibt sich eine Gabelaufnahme mit einem freien Mittelbereich für das Höhenrichtteil, in welchem das Höhenrichtteil und der auf dem Höhenrichtteil angeordnete Raketenabschussbehälter frei schwenken können, so dass sich ein großer Elevationsrichtbereich ergibt. Auch ergibt sich eine symmetrische Kraftableitung über die auf beiden Seiten des Höhenrichtteils angeordneten Hubelemente.Advantageously, two lifting elements are provided, which together form a fork receptacle for the height-adjusting part. Due to the parallel arrangement of two lifting elements results in a fork with a free center area for the height-elevation part, in which the Höhenrichtteil and on the Höhenrichtteil arranged missile launchers can pivot freely, so that there is a large elevation directing range. Also results in a symmetrical power dissipation over the arranged on both sides of the elevating part lifting elements.
Zur Minimierung der erforderlichen Richtmomente ist es vorteilhaft, wenn sich die Elevationsrichtachse nahe dem Schwerpunkt des aufmunitionierten Raketenabschussbehälters erstreckt. Im optimalen Fall erstreckt sich die Elevationsrichtachse durch den Schwerpunkt des aufmunitionierten Raketenabschussbehälters. Dies wird sich in der Praxis aufgrund unterschiedlicher Raketenabschussbehälter und Munitionstypen jedoch nicht immer realisieren lassen. Bevorzugt ist daher eine Ausgestaltung, bei welcher die Elevationsrichtachse des Höhenrichtteils durch einen den Schwerpunkt des aufmunitionierten Raketenabschussbehälters einschließenden Schwerpunktkorridor des Raketenabschussbehälters verläuft, der sich quer zu dessen Abschussrichtung erstreckt. Bevorzugt entspricht die Breite des Abschusskorridors der Höhe des Raketenabschussbehälters, bevorzugt drei Vierteln der Höhe des Raketenabschussbehälters und noch bevorzugter der halben Höhe des Raketenabschussbehälters. Durch den Verlauf der Elevationsrichtachse durch diesen Schwerpunktkorridor lassen sich die Richtmomente beim Elevieren des Raketenabschussbehälters während des gesamten Richtvorgangs vergleichsweise gering halten.To minimize the necessary directional moments, it is advantageous if the Elevationsrichtachse extends near the center of gravity of the aufmunitionierten rocket launcher. In the optimal case, the Elevationsrichtachse extends through the center of gravity of the aufmunitionierten rocket launcher. However, this will not always be possible in practice due to different missile launchers and ammunition types. Therefore, an embodiment is preferred in which the elevation directional axis of the elevation direction part extends through a center of gravity corridor of the rocket launching container enclosing the center of gravity of the ammunition launching missile launching container, which extends transversely to its launch direction. Preferably, the width of the launcher corridor corresponds to the height of the rocket launcher, preferably three quarters of the height of the launcher launcher, and more preferably half the height of the launcher launcher. Due to the course of the elevation directing axis through this gravity corridor, the directional moments during elevation of the rocket launching container during the entire straightening process can be kept comparatively low.
Bei einer Abschussvorrichtung der eingangs genannten Art wird zur Lösung der vorstehenden Aufgabe vorgeschlagen, dass diese in der zuvor beschriebenen Weise ausgebildet ist, wodurch sich die sich die im Zusammenhang mit der Vorrichtung beschrieben Vorteile ergeben.In a launcher of the type mentioned is proposed to solve the above problem that this is formed in the manner described above, resulting in the advantages described in connection with the device.
In Weiterbildung dieser Abschussvorrichtung wird vorgeschlagen, dass das Seitenrichtteil auf einer Transportplattform angeordnet ist, wobei das Hubelement des Seitenrichtteils derart angeordnet ist, dass ein sich beim Verschießen von Raketen ergebender Abgasstrahl bei einem Elevationswinkel des Höhenrichtteils von bis zu 45 Grad, bevorzugt bis zu 60 Grad, noch bevorzugter bis zu 70 Grad an der Transportplattform vorbeiführt. Der Abgasstrahl, beispielsweise beim Verschießen von Kurzstreckenraketen, wird sich aufgrund dessen nach hinten aufweitenden Abgaswinkels und der in der Umgebungsluft auftretenden Verwirbelungen usw. in der Praxis nicht vollständig von der Transportplattform fern halten lassen. Unter dem Abgasstrahl im Sinne der vorliegenden Erfindung wird daher erfindungsgemäß die geometrische Verlängerung des Raketenabschussbehälters entgegen der Abschussrichtung verstanden, wodurch dann die wesentlichen Teile des Abgasstrahls auch in der Praxis an der Transportplattform vorbeigeführt werden.
Bei einem Verfahren der eingangs genannten Art wird zur Lösung der vorstehend genannten Aufgabe der Gegenstand des unabhängigen Verfahrensanspruch 11 vorgeschlagen. Durch Anheben des Höhenrichtteils lassen sich auf einfache Art und Weise gute Transporteigenschaften und geringe Abschussbeeinträchtigungen bei gleichzeitig geringen Richtmomenten realisieren. Durch Absenken des Höhenrichtteils ist es möglich, die Richtvorrichtung zu Transportzwecken in eine kompakte Transportstellung zu überführen. Gleichzeitig kann die Elevationsrichtachse nahe dem Schwerpunkt des Raketenabschussbehälters angeordnet werden, wodurch sich während des gesamten Richtvorgangs gute Richteigenschaften ergeben. Zudem lassen sich durch das Anheben des Höhenrichtteils die Beeinträchtigungen beim Verschießen der Raketen gering halten.In a further development of this launcher, it is proposed that the side facing part is arranged on a transport platform, wherein the lifting element the side directing part is arranged such that an exhaust jet resulting from missile firing passes past the transport platform at an elevation angle of the elevation portion of up to 45 degrees, preferably up to 60 degrees, more preferably up to 70 degrees. The exhaust jet, for example, when shooting short-range missiles, will not be kept completely away from the transport platform in practice due to its rearwardly widening exhaust angle and the turbulence occurring in the ambient air, etc. in practice. According to the invention, the exhaust gas jet in the sense of the present invention is understood to mean the geometric extension of the rocket launching container counter to the firing direction, as a result of which the essential parts of the exhaust gas jet are also guided past the transport platform in practice.
In a method of the type mentioned, the object of the
Weitere Einzelheiten und Vorteile einer Vorrichtung wie auch eines Verfahrens zum Richten eines Raketenabschussbehälters sowie einer eine solche Vorrichtung aufweisenden Abschussvorrichtung werden nachfolgend anhand der Darstellungen eines Ausführungsbeispiels in den beigefügten Zeichnungen erläutert. Darin zeigen:
- Fig. 1
- in perspektivischer Ansicht eine Abschussvorrichtung in deren Transportstellung,
- Fig. 2
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 1 , - Fig. 3
- eine der Ansicht in
Fig. 1 entsprechende Darstellung, in welcher eine Transporthaube entfernt wurde, - Fig. 4
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 3 , - Fig. 5
- eine perspektivische Ansicht der Abschussvorrichtung in einer Zwischenstellung, in welcher der Raketenabschussbehälter etwas angehoben wurde,
- Fig. 6
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 5 , - Fig. 7
- eine perspektivische Ansicht der Abschussvorrichtung in einer weiteren Zwischenstellung, in welcher der Raketenabschussbehälter maximal angehoben wurde,
- Fig. 8
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 7 , - Fig. 9
- eine perspektivische Ansicht, der Abschussvorrichtung in der Richtstellung,
- Fig. 10
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 9 , - Fig. 11
- zur Veranschaulichung des Richtbereichs der Richtvorrichtung eine Darstellung, in welcher der Raketenabschussbehälter den maximalen Elevationswinkel von 90 Grad einnimmt,
- Fig. 12
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 11 , - Fig. 13
- eine perspektivische Ansicht, der Abschussvorrichtung in der Abschussstellung und
- Fig. 14
- eine seitliche Ansicht gemäß der Darstellung in
Fig. 13 .
- Fig. 1
- in a perspective view of a launching device in its transport position,
- Fig. 2
- a side view as shown in
Fig. 1 . - Fig. 3
- one of the view in
Fig. 1 corresponding representation in which a transport hood has been removed, - Fig. 4
- a side view as shown in
Fig. 3 . - Fig. 5
- a perspective view of the launcher in an intermediate position in which the rocket launcher was raised slightly,
- Fig. 6
- a side view as shown in
Fig. 5 . - Fig. 7
- a perspective view of the launcher in a further intermediate position in which the rocket launcher was raised maximum,
- Fig. 8
- a side view as shown in
Fig. 7 . - Fig. 9
- a perspective view of the launcher in the directional position,
- Fig. 10
- a side view as shown in
Fig. 9 . - Fig. 11
- to illustrate the directional range of the straightening device a representation in which the rocket launcher occupies the maximum elevation angle of 90 degrees,
- Fig. 12
- a side view as shown in
Fig. 11 . - Fig. 13
- a perspective view of the launching device in the firing position and
- Fig. 14
- a side view as shown in
Fig. 13 ,
Die Darstellung in
Derartige Abschussvorrichtungen 50 werden häufig in Krisengebieten eingesetzt, in welchen sie oftmals an unterschiedlichen Einsatzorten eingesetzt werden, und bestehen im Wesentlichen aus einer auf einer Transportplattform 51 angeordneten Richtvorrichtung 1 zum Richten des Raketenabschussbehälters 20.
Beim Ausführungsbeispiel ist die Abschussvorrichtung 50 innerhalb eines Transportcontainers 52 angeordnet, der aus einer abnehmbaren Haube 53 und einem die Transportplattform 51 der Richtvorrichtung 1 bildenden Containerboden besteht. Es handelt sich um einen standardisierten Transportcontainer 52, welcher mit ganz unterschiedlichen Transportfahrzeugen, wie beispielsweise LKWs, Flugzeugen, Schiffen usw. transportiert werden kann. Die Abschussvorrichtung kann nach dem Transport zu deren Einsatzort wahlweise direkt auf dem Transportfahrzeug, also beispielsweise einem LKW oder einem Schiff, oder in von diesem abgesetzter Stellung eingesetzt werden.In the exemplary embodiment, the launching
Wie nachfolgend im Einzelnen dargelegt werden wird, zeichnet sich die erfindungsgemäße Richtvorrichtung 1 insbesondere durch gute Transporteigenschaften, geringe Abschussbeeinträchtigungen beim Verschuss der Raketen und gleichzeitig verbesserte Richteigenschaften aus, wozu ein Hubelement 4 zum Anheben und Absenken des Raketenabschussbehälters 20 vorgesehen ist. Dies soll nachfolgend anhand der Figuren im Einzelnen erläutert werden.As will be explained in detail below, the straightening device according to the invention 1 is characterized in particular by good transport properties, low launching impact on the missile missile and simultaneously improved directional properties, including a
Die
Um die Abschussvorrichtung 50 in einen Zustand der Kampfbereitschaft zu überführen, wird zunächst die Haube 53 des Containers von dem als Transportplattform 51 dienenden Containerboden entfernt.In order to transfer the
Diese Stellung ist in den
Im Bereich zwischen der Transportplattform 51 und dem Raketenabschussbehälter 20 ist die Richtvorrichtung 1 in einer kompakt zusammengeklappten Stellung zu erkennen.In the area between the
Die Richtvorrichtung 1 weist als wesentliche Bestandteile ein Seitenrichtteil 2 sowie ein Höhenrichtteil 3 auf.The straightening device 1 has as its essential components a
Das Seitenrichtteil 2 ist um die in
Das Höhenrichtteil 3 ist um die in
Nachdem die Containerhaube 53 entfernt wurde, können in einem nächsten Schritt gemäß den Darstellungen in den
Wie der Vergleich beispielsweise zwischen den Darstellungen in den
Zum Betätigen der als Aufstellhebel ausgebildeten Hubelemente 4 dienen beim Ausführungsbeispiel elektromotorisch betriebene Linearantriebe 6. Jedem Hubelement 4 ist ein eigener Linearantrieb 6 zugeordnet. Das eine Ende 6.1 der Linearantriebe 6 ist an der Azimut-Richtplattform 5 angelenkt. Das andere Ende 6.2 der Linearantriebe 6 ist an dem Hubelement 4 angelenkt. Die Position der hubelementseitigen Anlenkung ist dabei derart gewählt, dass diese möglichst hoch an dem Hubelement 4 angreift, wodurch sich günstige Hebelverhältnisse ergeben. Durch Betätigung der Linearantriebe 6 werden die Hubelemente 4 in eine im Wesentlichen vertikale Stellung verschwenkt. Gleichzeitig wird der Raketenabschussbehälter 20 seitlich in Richtung des Randes der Transportplattform 51 verlagert, wodurch sich die Beeinträchtigungen der Transportplattform 51 beim Raketenstart gering halten lassen.To operate the lifting elements designed as raising
Wie die Darstellungen in den
In dieser Position ist das Höhenrichtteil 3 angehoben und der Raketenabschussbehälter 20 hat seine obere Hubstellung erreicht. Durch anschließendes Elevieren des Höhenrichtteils 3 um dessen Elevationsrichtachse E wird der Raketenabschussbehälter 20 dann in dessen Richtstellung gebracht.In this position, the leveling
Die Richtstellung ist in den
Wie die Darstellung in
Darüber hinaus wird anhand der Darstellung in
Gemäß den zur Veranschaulichung dienenden Darstellungen in den
Schließlich zeigen die Darstellungen in den
Wie vorstehend dargelegt wurde, zeichnet sich die erfindungsgemäße Richtvorrichtung durch eine kompakte Transportstellung, geringe Beeinflussungen der Transportplattform sowie günstige Richteigenschaften aus, was durch das an dem Seitenrichtteil 2 angeordnete Hubelement 4 erreicht wird.As stated above, the straightening device according to the invention is characterized by a compact transport position, low influences the transport platform and favorable directional properties, which is achieved by the arranged on the
- 11
- Richtvorrichtungstraightener
- 22
- SeitenrichtteilTraversing part
- 33
- HöhenrichtteilElevating part
- 44
- Hubelementlifting
- 4.14.1
- EndeThe End
- 4.24.2
- EndeThe End
- 4.34.3
- Teleskopelementtelescopic element
- 4.44.4
- Teleskopelementtelescopic element
- 55
- Azimut-RichtplattformAzimuth directional platform
- 66
- Linearantrieblinear actuator
- 6.16.1
- EndeThe End
- 6.26.2
- EndeThe End
- 77
- Linearantrieblinear actuator
- 7.17.1
- EndeThe End
- 7.27.2
- EndeThe End
- 2020
- RaketenabschussbehälterMissile launch container
- 5050
- Abschussvorrichtunglauncher
- 5151
- Transportplattformtransport platform
- 5252
- ContainerContainer
- 5353
- Containerhaubecontainer hood
- 5454
- Stauraumstorage space
- Ee
- ElevationsrichtachseElevation sight axis
- AA
- AzimutrichtachseAzimuth directional axis
- S1 S 1
- Schwenkachseswivel axis
- S2 S 2
- Schwenkachseswivel axis
- KK
- SchwerpunktkorridorPriority Corridor
- SS
- Abschussrichtungfiring direction
- AA
- Abgasstrahljet blast
- SHSH
- SchwenkhubSwing stroke
- THTH
- TeleskopierhubTeleskopierhub
- GHGH
- GesamthubTotal stroke
Claims (11)
- Device for aiming a rocket launching container (20) having a lateral-directing part (2) and a height-directing part (3) which is arranged on the lateral-directing part (2) and intended for receiving the rocket launching container (20), wherein the lateral-directing part (2) has a telescopically designed lifting element (4) for raising and lowering the height-directing part (3), characterized in that the lifting element (4) is designed as a pivotable raising lever and a pivoting stroke (SH) and a telescoping stroke (TH) of the lifting element (4) can be added to give a larger total stroke (GH), wherein the pivoting and telescoping movement of the lifting element (4) can either be superimposed or carried out in succession.
- Device according to Claim 1, characterized in that the lateral-directing part (2) has an azimuth directional platform (5).
- Device according to Claim 2, characterized in that one end (4.1) of the lifting element (4) is articulated on the azimuth directional platform (5) and the other end (4.2) is articulated on the height-directing part (3).
- Device according to one of Claims 1 to 4, characterized in that the lifting element (4) is pivotable via a linear drive (6).
- Device according to Claim 4, characterized in that the linear drive (6) is articulated on the azimuth directional platform (5) by one end (6.1) and on the lifting element (4) by the other end (6.2).
- Device according to one of the preceding claims, characterized in that the lifting element (4) is telescopable via a linear drive (7).
- Device according to one of the preceding claims, characterized by two lifting elements (4) which jointly form a fork mounting for the height-directing part (3).
- Device according to one of the preceding claims, characterized in that the elevation directional axis (E) of the height-directing part (3) runs through a centre of gravity corridor (K) of the rocket launching container (20) which encloses the centre of gravity of the munition-loaded rocket launching container (20), which corridor extends transversely to the launching direction (S) of said container and the width (B) of which corresponds to the height (H) of the rocket launching container (20), preferably to three quarters of the height (H) of the rocket launching container (20), and more preferably to half the height (H) of the rocket launching container (20).
- Launching device having a device (1) according to one of Claims 1 to 8.
- Launching device according to Claim 9, characterized in that the lateral-directing part (2) is arranged on a transport platform (51), wherein the lifting element (4) of the lateral-directing part (2) is arranged in such a way that an exhaust-gas jet (A) which results upon firing rockets is guided past the transport platform (51) at an elevation angle of the height-directing part of up to 45°, preferably up to 60°, more preferably of up to 70°.
- Method for aiming a rocket launching container (20) by means of a device for aiming the rocket launching container according to one of Claims 1 to 8, characterized in that the lifting element (4) is designed as a pivotable raising lever and a pivoting stroke (SH) and a telescoping stroke (TH) of the lifting element (4) are added to give a larger total stroke (GH), wherein the pivoting and telescoping movement of the lifting element (4) can either be superimposed or carried out in succession.
Applications Claiming Priority (1)
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DE102013100392.3A DE102013100392A1 (en) | 2013-01-15 | 2013-01-15 | Apparatus and method for straightening a rocket launcher |
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EP2754989A2 EP2754989A2 (en) | 2014-07-16 |
EP2754989A3 EP2754989A3 (en) | 2016-03-23 |
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DE102015118692A1 (en) * | 2015-11-02 | 2017-05-04 | Krauss-Maffei Wegmann Gmbh & Co. Kg | weapon system |
FR3052550B1 (en) * | 2016-06-09 | 2018-05-25 | Nexter Systems | PROJECTILE LAUNCHER DEVICE AND TURRET EQUIPPED WITH SUCH A DEVICE |
CN110998219A (en) * | 2017-08-17 | 2020-04-10 | 麦可吉国防工业有限公司 | Rocket projectile launching module and rocket projectile launching carrier |
FR3079023B1 (en) * | 2018-03-16 | 2021-04-09 | Naval Group | LAND VEHICLE INCLUDING AT LEAST ONE MISSILES LAUNCH MODULE |
CN111735345B (en) * | 2020-06-23 | 2021-12-10 | 西北工业大学 | Portable automatic posture-adjusting emitter |
CN114754625B (en) * | 2022-03-29 | 2023-09-29 | 鲁东大学 | Rocket erection device and rocket erection method |
CN114909952B (en) * | 2022-04-20 | 2023-08-18 | 北京航天试验技术研究所 | Foldable movable liquid rocket launching frame |
CN114719678B (en) * | 2022-05-09 | 2023-09-19 | 鲁东大学 | Six-container type offshore launching rocket erection device |
CN115200407B (en) * | 2022-08-01 | 2023-08-18 | 东方空间技术(山东)有限公司 | Offshore suspension type rocket launching platform, rocket launching device and launching method |
FR3139193A1 (en) * | 2022-08-30 | 2024-03-01 | Naval Group | Modular and versatile munitions launching system and naval platform comprising at least one such system |
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DE1259737B (en) * | 1964-11-06 | 1968-01-25 | Boelkow Gmbh | Launching and loading device for recoil-propelled missiles, which can be launched individually one after the other or at the same time from adjustable interchangeable magazines |
DE1959548A1 (en) * | 1969-11-27 | 1971-06-03 | Porsche Kg | Armored vehicle, especially Panzerjaeger |
US4282794A (en) * | 1979-04-30 | 1981-08-11 | Miller Avy L | Self-propelled off-road vehicle |
DE29922470U1 (en) * | 1999-12-22 | 2001-05-03 | Krauss-Maffei Wegmann GmbH & Co.KG, 80997 München | Military system module, in particular air defense system module |
DE10046480A1 (en) * | 2000-09-20 | 2002-03-28 | Krauss Maffei Wegmann Gmbh & C | Armored vehicle, in particular combat vehicle |
US6584881B1 (en) * | 2001-03-26 | 2003-07-01 | United Defense Lp | Multi-purpose missile launcher system for a military land vehicle |
JP2003056997A (en) * | 2001-08-09 | 2003-02-26 | Komatsu Ltd | Missile launching machine |
DE102004003476A1 (en) * | 2004-01-22 | 2005-08-18 | Rheinmetall Landsysteme Gmbh | Device for building and holding a weapon station |
ATE464530T1 (en) * | 2007-10-23 | 2010-04-15 | Onuk Tasit Sanayi Ltd Sirketi | COLLAPSIBLE ROCKET LAUNCHER RAMP |
DE102010016542C5 (en) | 2010-04-20 | 2017-08-17 | Krauss-Maffei Wegmann Gmbh & Co. Kg | Apparatus and method for straightening a launching container |
DE202010006199U1 (en) * | 2010-04-28 | 2010-08-12 | Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Wehrtechnik und Beschaffung | Weapon system for artillery rockets |
US8468924B2 (en) * | 2010-12-16 | 2013-06-25 | Lockheed Martin Corporation | Stowable elevating trainable launcher (SETL) |
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2013
- 2013-01-15 DE DE102013100392.3A patent/DE102013100392A1/en not_active Withdrawn
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2014
- 2014-01-08 EP EP14150441.5A patent/EP2754989B1/en active Active
- 2014-01-08 ES ES14150441.5T patent/ES2685245T3/en active Active
Non-Patent Citations (1)
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ES2685245T3 (en) | 2018-10-08 |
DE102013100392A1 (en) | 2014-07-17 |
EP2754989A3 (en) | 2016-03-23 |
EP2754989A2 (en) | 2014-07-16 |
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