EP2754989B1 - Dispositif et procédé de pointage d'un conteneur lanceur de missiles - Google Patents

Dispositif et procédé de pointage d'un conteneur lanceur de missiles Download PDF

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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.)
Active
Application number
EP14150441.5A
Other languages
German (de)
English (en)
Other versions
EP2754989A2 (fr
EP2754989A3 (fr
Inventor
Eric Prummenbaum
Karl Lieberum
Bernhard Lorenz
Frank Dieling
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Krauss Maffei Wegmann GmbH and Co KG
Original Assignee
Krauss Maffei Wegmann GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication of EP2754989A2 publication Critical patent/EP2754989A2/fr
Publication of EP2754989A3 publication Critical patent/EP2754989A3/fr
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Publication of EP2754989B1 publication Critical patent/EP2754989B1/fr
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Classifications

    • 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
    • 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
    • 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
    • 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
    • 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
    • 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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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)

Claims (11)

  1. Dispositif pour dresser un conteneur de lancement de fusées (20), comprenant une partie de dressage latérale (2) et une partie de dressage en hauteur (3) disposée sur la partie de dressage latérale (2) et destinée à accueillir le conteneur de lancement de fusées (20), la partie de dressage latérale (2) possédant un élément de va-et-vient (4) de configuration télescopique destiné à lever et à abaisser la partie de dressage en hauteur (3),
    caractérisé en ce que
    l'élément de va-et-vient (4) est réalisé sous la forme d'un levier de mise en place pivotant et une course de pivotement (SH) et une course télescopique (TH) de l'élément de va-et-vient (4) peuvent s'additionner pour former une course totale (GH) plus grande, les mouvements de pivotement et télescopique de l'élément de va-et-vient (4) pouvant être accomplis soit en superposition, soit l'un après l'autre.
  2. Dispositif selon la revendication 1, caractérisé en ce que la partie de dressage latérale (2) possède une plate-forme de dressage en azimut (5).
  3. Dispositif selon la revendication 2, caractérisé en ce qu'une extrémité (4.1) de l'élément de va-et-vient (4) est fixée de manière articulée à la plate-forme de dressage en azimut (5) et l'autre extrémité (4.2) à la partie de dressage en hauteur (3).
  4. Dispositif selon l'une des revendications 1 à 4, caractérisé en ce que l'élément de va-et-vient (4) peut être amené à pivoter par le biais d'un mécanisme d'entraînement linéaire (6).
  5. Dispositif selon la revendication 4, caractérisé en ce que le mécanisme d'entraînement linéaire (6) est fixé de manière articulée par une extrémité (6.1) à la plate-forme de dressage en azimut (5) et par l'autre extrémité (6.2) à l'élément de va-et-vient (4).
  6. Dispositif selon l'une des revendications précédentes, caractérisé en ce que l'élément de va-et-vient (4) peut être amené à effectuer un mouvement télescopique par le biais d'un mécanisme d'entraînement linéaire (7).
  7. Dispositif selon l'une des revendications précédentes, caractérisé par deux éléments de va-et-vient (4) qui forment ensemble un logement en fourche pour la partie de dressage en hauteur (3).
  8. Dispositif selon l'une des revendications précédentes, caractérisé en ce que l'axe de dressage en élévation (E) de la partie de dressage en hauteur (3) passe par corridor de centre de gravité (K) du conteneur de lancement de fusées (20) incluant le centre de gravité du conteneur de lancement de fusées (20) chargé en munitions, lequel s'étend transversalement à sa direction de tir (S) et dont la largeur (B) correspond à la hauteur (H) du conteneur de lancement de fusées (20), de préférence aux trois quarts de la hauteur (H) du conteneur de lancement de fusées (20), et encore de préférence à la moitié de la hauteur (H) du conteneur de lancement de fusées (20).
  9. Dispositif de tir comprenant un dispositif (1) selon l'une des revendications 1 à 8.
  10. Dispositif de tir selon la revendication 9, caractérisé en ce que la partie de dressage latérale (2) est disposée sur une plate-forme de transport (51), l'élément de va-et-vient (4) de la partie de dressage latérale (2) étant disposé de telle sorte qu'un jet de gaz d'échappement (A) qui se produit lors du tir de fusées passe à côté de la plate-forme de transport (51) en présence d'un angle d'élévation de la partie de dressage en hauteur jusqu'à 45°, de préférence jusqu'à 60°, encore de préférence jusqu'à 70°.
  11. Procédé pour dresser un conteneur de lancement de fusées (20) au moyen d'un dispositif pour dresser le conteneur de lancement de fusées selon l'une des revendications 1 à 8,
    caractérisé en ce que
    l'élément de va-et-vient (4) est réalisé sous la forme d'un levier de mise en place pivotant et une course de pivotement (SH) et une course télescopique (TH) de l'élément de va-et-vient (4) sont additionnées pour former une course totale (GH) plus grande, les mouvements de pivotement et télescopique de l'élément de va-et-vient (4) étant accomplis soit en superposition, soit l'un après l'autre.
EP14150441.5A 2013-01-15 2014-01-08 Dispositif et procédé de pointage d'un conteneur lanceur de missiles Active EP2754989B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013100392.3A DE102013100392A1 (de) 2013-01-15 2013-01-15 Vorrichtung und Verfahren zum Richten eines Raketenabschussbehälters

Publications (3)

Publication Number Publication Date
EP2754989A2 EP2754989A2 (fr) 2014-07-16
EP2754989A3 EP2754989A3 (fr) 2016-03-23
EP2754989B1 true EP2754989B1 (fr) 2018-06-27

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EP (1) EP2754989B1 (fr)
DE (1) DE102013100392A1 (fr)
ES (1) ES2685245T3 (fr)

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FR3052550B1 (fr) * 2016-06-09 2018-05-25 Nexter Systems Dispositif lanceur de projectile et tourelle equipee d'un tel dispositif
WO2019033182A1 (fr) 2017-08-17 2019-02-21 Mac Jee Indústria Comério E Representação Comercial Ltda. Module de lancement de fusées et véhicule de lancement de fusées
FR3079023B1 (fr) * 2018-03-16 2021-04-09 Naval Group Vehicule terrestre comprenant au moins un module de lancement de missiles
CN111086772A (zh) * 2020-03-11 2020-05-01 衡阳泰豪通信车辆有限公司 一种可快速分离集装箱
CN111735345B (zh) * 2020-06-23 2021-12-10 西北工业大学 一种便携式自动化调姿发射器
CN114754625B (zh) * 2022-03-29 2023-09-29 鲁东大学 一种火箭起竖装置及起竖方法
CN114909952B (zh) * 2022-04-20 2023-08-18 北京航天试验技术研究所 一种可折叠移动式液体火箭发射架
CN114719678B (zh) * 2022-05-09 2023-09-19 鲁东大学 一种六集装箱式海上发射火箭起竖装置
CN115200407B (zh) * 2022-08-01 2023-08-18 东方空间技术(山东)有限公司 一种海上悬浮式火箭发射平台、火箭发射装置及发射方法
FR3139193A1 (fr) * 2022-08-30 2024-03-01 Naval Group Système modulaire et polyvalent de lancement de munitions et plateforme navale comportant au moins un tel système

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Also Published As

Publication number Publication date
EP2754989A2 (fr) 2014-07-16
ES2685245T3 (es) 2018-10-08
DE102013100392A1 (de) 2014-07-17
EP2754989A3 (fr) 2016-03-23

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