EP2354751B1 - Conteneur pour missile à réaction - Google Patents

Conteneur pour missile à réaction Download PDF

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Publication number
EP2354751B1
EP2354751B1 EP11000643.4A EP11000643A EP2354751B1 EP 2354751 B1 EP2354751 B1 EP 2354751B1 EP 11000643 A EP11000643 A EP 11000643A EP 2354751 B1 EP2354751 B1 EP 2354751B1
Authority
EP
European Patent Office
Prior art keywords
container
jet
missile
deflection device
wedge face
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
EP11000643.4A
Other languages
German (de)
English (en)
Other versions
EP2354751A3 (fr
EP2354751A2 (fr
Inventor
Stefan Höhn
Roland Waschke
Peter Gerd Fisch
Ulrich Hochstein
Dominik Herrmann
Ferdinand Solfrank
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence 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.)
Filing date
Publication date
Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2354751A2 publication Critical patent/EP2354751A2/fr
Publication of EP2354751A3 publication Critical patent/EP2354751A3/fr
Application granted granted Critical
Publication of EP2354751B1 publication Critical patent/EP2354751B1/fr
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Classifications

    • 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
    • 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
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems

Definitions

  • the invention relates to a container for jet-propelled missiles.
  • Such containers are usually used for the transport, protection and launch of jet-propelled missiles, in particular of vertically launched missiles.
  • Jet-propelled missiles such as rockets
  • the launch takes place aboard a ship or on land from the ground.
  • a propulsion jet of a jet-propelled missile usually has large impulses and high temperatures, it is often necessary to redirect the propulsion jet such that neither the starting missile is impaired in its function nor undesirable damage to the environment of the starting missile occurs.
  • the propulsion jet of a missile starting vertically is not deflected, it strikes the ground at high pressure and spreads there in all directions. Loose parts, such as stones, are thrown uncontrollably through the area and can damage the missile itself or other objects.
  • too high a temperature load can occur.
  • the environment is contaminated by chemically aggressive residues of the drive jet.
  • a jet deflector has hitherto been attached to the starting device, often referred to as the launch platform, which as a rule consists of a steel plate.
  • the beam deflector is aligned in this way the propulsion jets from missiles fired from the launching device strike the beam deflector without being deflected beforehand, deflected by the latter and thus guided away from the starting device.
  • the beam deflector is obviously designed to withstand the pulses and heat loads of missile launchers. This requires a construction with a comparatively large weight, which is expensive to position. Even if starting device and beam deflector, as exemplified in FIG. 1 represented, are integrated in a truck, the repositioning of the starting device is therefore cumbersome.
  • the beam deflector is usually used multiple times, resulting in contamination and damage, so that a regular repair of the beam deflector is required.
  • the DE 41 12 287 A1 shows a container with which two missiles can be enclosed. At the center of this container is known a device for releasing the drive jets of the missiles, which comprises two doors and one or two angled walls in connection with two openings.
  • the EP 2 090 859 A2 deals with a starter equipped with a gas generator. At the end of the starting pipe is a Laval nozzle with downstream Laval nozzle arrangement, which serves to exit the gas flow of the gas generator.
  • the Laval nozzle arrangement comprises at its end two hinged Strahlablenk vom for the derivation of the gas flow rate.
  • the JP 2010 007948 A discloses a launch tube for a missile, in the interior of which a rail for retracting the missile from the launch tube and a configuration device are arranged.
  • the configuration device is formed by a rectangular box, which is arranged on the inner wall of the launch tube.
  • a "channeling" component in the form of a Wedge arranged.
  • the JP 2001 007948 A deals with a launcher, which has a main part, at the top of one or more downwardly open canisters for missiles are vertically attachable. Also located vertically on the top of the main part is a chimney, which serves to dissipate the reaching into the interior drive jets shot down from the canisters missile.
  • the present invention is therefore based on the object to provide a low-cost option for deflecting the drive beam of the missile available.
  • the Strahlumlenkvoriques with the container for the jet-propelled missile which is often referred to as a canister, a unit forms, it is disposed of as well as the container after the launch of the missile.
  • the beam deflection device can thus be designed in its strength for a single use, in contrast to the beam deflector described above. This allows a lightweight construction of the beam deflecting device. In addition, no time-consuming cleaning of contaminated components or repair of components is required. In addition, starting devices with containers or missiles arranged therein can be more easily positioned or repositioned. The handling is further facilitated by a reduction of the installation space, which enables the container according to the invention over a system with the beam deflector described above.
  • the invention enables increased reliability compared to a mobile system with beam deflector, since a hydraulically or mechanically driven complex facial expressions can be dispensed with for the beam deflector to be folded away for transport.
  • the respective Strahlumlenkvoriques can be easily adapted in the container according to the invention to the arranged in the container missile.
  • a missile of a different type is already arranged in the course of production in a container with another, for this missile optimized Strahlumlenkvortechnisch.
  • different types of missile can be easily launched with the same starting device without a Strahlabweiser or the like must be adjusted.
  • An embodiment variant of the invention provides that the jet inlet opening and the jet outlet opening are arranged on different sides of the beam deflecting device, preferably on opposite sides. As a result, the mechanical load on the beam deflecting device can be reduced, thereby reducing its mass.
  • a wedge surface arranged in the flow channel is provided for the at least partial deflection of a drive jet of the missile.
  • the wedge surface engages at a defined angle over a predetermined length and up to a predetermined position, which is referred to as engagement, in the output beam and changed in this way, inter alia, the direction of the drive beam.
  • the engagement can be partially or completely within the drive beam or even extend beyond. If the intervention is only partially within the drive beam, only a part of the drive beam is deflected by the partial surface. In this way, a larger expansion of the drive jet can be achieved, which in turn has a reduced interaction with the environment result, so that, for example, with unconsolidated ground looser soil or loose stones are thrown to a lesser extent.
  • a wedge surface has proven to form a cutting angle of 10 ° to 50 ° with a longitudinal axis of the container.
  • a wedge surface has proven to be advantageous, which extends in the longitudinal direction of the container measured over a length of 20 cm to 50 cm, preferably over a length of 30 cm to 35 cm.
  • two side surfaces spaced apart from each other and adjacent to the wedge surface are provided, which form a cutting angle of 0 ° to 20 ° with the longitudinal axis of the container, preferably providing a cutting angle of 0 ° is. If, on the other hand, a cutting angle different from 0 ° is provided, the side surfaces are aligned such that their distance from the longitudinal axis increases in the direction of the jet outlet opening. Since the deflection of the drive beam is based on an interaction of all boundary surfaces of the flow channel, an overpressure area and a negative pressure area in the beam deflecting device can be generated with the aid of the side surfaces and the deflection effect can be improved by combining the overpressure area with the pressure area. To form the negative pressure region, it can be provided that the side surfaces open into a widening space, which has an enlarged cross-section compared with a space delimited by the side surfaces.
  • plug-in connections for contacting the container, a pressure relief valve, a moisture indicator or a crank access known per se may be provided on the beam deflecting device, and there preferably on the side of the jet outlet opening.
  • the Strahlumschvortechnisch is hermetically sealed from the environment of the container.
  • the materials used for the beam deflecting device are obviously to be chosen so that they withstand the prevailing at the start of a missile temperatures.
  • At least the deflection devices for example wedge surfaces or wall surfaces of the flow channel, are preferably made of a refractory material. Should a malfunction occur, such as a hangfire where a missile remains in the vessel, the use of refractory material is particularly well-suited to prevent major damage.
  • Fig. 1 shows a schematic representation of a arranged on a truck launch device 70 for jet-propelled missile according to the prior art.
  • the starting device 70 is designed for a vertical launch of arranged in conventional containers 72a, 72b, jet-propelled missiles.
  • the propulsion jet exits below from the container 72a, 72b and strikes a jet deflector 74, which redirects the propulsion jet to the rear and in this way an impairment of the containers 72a, 72b by spin-on objects , Heat or chemical contamination in the manner described above.
  • FIGS. 2 and 3 show in a schematic partial perspective view, or a schematic partial section, a container 1.
  • the beam deflection device 5 has a jet entry opening 23 which, as in FIG Fig. 3 can be seen, a nozzle of a arranged in the container 1 missile 3 faces.
  • a jet outlet opening 25 is on one of the jet inlet opening 23 opposite side of the Strahlumlenkvortechnik 5 is arranged.
  • the jet inlet opening 23 and the jet outlet opening 25 are connected to one another via a flow channel 27.
  • the flow channel 27 is curved, so that a wall surface 29 of the flow channel forms a deflection device for a drive jet of the missile 3.
  • the drive beam through the wall surface 29 of the flow channel 27 in the representation of Fig. 3 be deflected upwards.
  • the wall surface 29 of the flow channel 27 is formed in the present example of a refractory material.
  • the jet outlet opening 25 is provided with a cover 13, which has predetermined breaking points 15. At a start of the missile 3 thus the lid 13 is opened by the drive beam, so that it can escape. As a safety measure, a pressure relief valve is provided on the beam deflection device 5.
  • centering pins 19 and a locking pin 21 are provided in the present embodiment.
  • a moisture indicator 7 and a known crank 9 is arranged on the side of the beam outlet opening 25. In this way, the moisture indicator and the crank access remain accessible or visible during assembly of the container 1 in a starting device.
  • Fig. 4 shows an embodiment of the container according to the invention in a schematic representation.
  • a missile 3 is again arranged in the illustrated container 51.
  • a Strahlumschvorraum 50 is flanged to the right end of the container turn a Strahlumschvorraum 50.
  • Fig. 5 schematically shows an enlarged projection view of this Strahlumlenkvortechnisch 50 Fig. 4
  • a schematic sectional view through this Strahlumlenkvortechnisch 50 along the line AA Fig. 5 is in Fig. 6 played.
  • a wedge surface 52 is arranged, which forms a cutting angle ⁇ with a longitudinal axis 60 of the container 51, which is preferably in the range of 10 ° to 50 °.
  • a nozzle of the missile 3 indicated.
  • the wedge surface Accordingly, 52 projects into a drive beam emitted by the missile 3, namely by a so-called engagement 55.
  • this engagement only partially engages the drive beam. In principle, however, it is also conceivable that this engagement extends beyond the drive beam.
  • the propulsion jet passes through a jet inlet opening 56 into the flow channel 27, where it is partially deflected by the wedge surface 52 and emerges from the beam deflecting device 50 through the jet outlet opening 58.
  • the partial engagement of the wedge surface 52 in the drive beam causes in this case a strong expansion of the drive beam, which has a reduced interaction of the drive beam with the environment result.
  • loose ground is thrown up less like stones. The risk of damaging the container 51 or other surrounding objects is thus reduced.
  • the Strahlumschvoretti 50 two spaced apart side surfaces 54, which in the present case extend parallel to the longitudinal axis 60 of the container 51. Furthermore, the side surfaces 54 in the present embodiment extend perpendicular to the wedge surface 52. The side surfaces 54 open into a widening space 53, which has an enlarged cross section with respect to the space bounded by the side surfaces. If the drive jet flows through the flow channel 27, this results in a combination of an overpressure area with a negative pressure area, whereby the deflection effect is improved. In addition, can be effected with the described embodiment of the Strahlumlenkvoroplasty that the drive jet emerges from the Strahlumlenkvortechnik with a maximum outflow cross section.
  • the beam deflection device 50 of the embodiment of FIG 4 to 6 be provided at the beam exit opening 58 with a predetermined breaking points having lid.
  • plug connections, a pressure relief valve, a humidity indicator or a crank access can be provided in an analogous manner.
  • the Container 51 are provided with suitable centering pins and / or locking pin.
  • this can be achieved by providing a bearing surface or holder in the starting device for the beam deflection device, or a part of it.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Load-Engaging Elements For Cranes (AREA)

Claims (5)

  1. Récipient (51) pour un missile (3) propulsé par jet, comprenant
    a) un dispositif déviateur de jet (50) pourvu d'une ouverture d'entrée de jet (56) et d'une ouverture de sortie de jet (58), lesquelles sont reliées ensemble par le biais d'un canal d'écoulement (27),
    b) une surface cunéiforme (52) disposée dans le canal d'écoulement (27), la surface cunéiforme (52) s'étendant à l'intérieur du dispositif déviateur de jet (50), en référence à l'axe longitudinal (60) du récipient (51), en commençant par un côté intérieur du récipient et étant inclinée en direction du côté intérieur opposé du récipient en vue de dévier au moins partiellement un jet de propulsion du missile (3), et
    c) deux surfaces latérales (54) mutuellement espacées et juxtaposées à la surface cunéiforme (52), se trouvant à l'intérieur du dispositif déviateur de jet (50), lesquelles forment avec l'axe longitudinal (60) du récipient (51) un angle d'attaque de 0° à 20°,
    caractérisé en ce que
    les surfaces latérales (54) débouchent dans un espace d'élargissement (53) qui se trouve à l'intérieur du dispositif déviateur de jet (50), lequel espace présente une section transversale agrandie par rapport à un espace délimité par les surfaces latérales (54) à l'intérieur du dispositif déviateur de jet (50).
  2. Récipient (51) selon la revendication 1, caractérisé en ce que l'ouverture d'entrée de jet (56) et l'ouverture de sortie de jet (58) sont disposées sur des côtés différents du dispositif déviateur de jet (50), de préférence sur des côtés opposés.
  3. Récipient (51) selon la revendication 1 ou 2, caractérisé en ce que la surface cunéiforme (52) forme avec un axe longitudinal (60) du récipient (51) un angle d'attaque (α) de 10° à 50°.
  4. Récipient (51) selon l'une des revendications précédentes, avec lequel la surface cunéiforme (52), mesurée dans le sens longitudinal du récipient (51), s'étend sur une longueur de 20 cm à 50 cm, notamment de 30 cm à 35 cm.
  5. Récipient (51) selon l'une des revendications précédentes, avec lequel les deux surfaces latérales (54) s'étendent sensiblement perpendiculairement à la surface cunéiforme (52).
EP11000643.4A 2010-02-02 2011-01-27 Conteneur pour missile à réaction Active EP2354751B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201010006493 DE102010006493B4 (de) 2010-02-02 2010-02-02 Behälter für einen strahlgetriebenen Flugkörper

Publications (3)

Publication Number Publication Date
EP2354751A2 EP2354751A2 (fr) 2011-08-10
EP2354751A3 EP2354751A3 (fr) 2014-10-29
EP2354751B1 true EP2354751B1 (fr) 2016-05-25

Family

ID=43902838

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11000643.4A Active EP2354751B1 (fr) 2010-02-02 2011-01-27 Conteneur pour missile à réaction

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EP (1) EP2354751B1 (fr)
DE (1) DE102010006493B4 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2543439C1 (ru) * 2013-10-09 2015-02-27 Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Устройство для запуска ракет

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01124494A (ja) * 1987-11-07 1989-05-17 Brother Ind Ltd ワンタッチ糸掛け可能なミシン
DE4112287A1 (de) * 1991-04-15 1992-10-22 Israel Aircraft Ind Ltd Behaelter
US5153367A (en) * 1991-09-17 1992-10-06 Fmc Corporation Cocoon launcher and storage system
JP3396449B2 (ja) * 1999-09-17 2003-04-14 三菱重工業株式会社 飛昇体発射装置および飛昇体のキャニスタ
JP2001124494A (ja) * 1999-10-25 2001-05-11 Mitsubishi Electric Corp 飛しょう体の発射装置
ITRM20050166A1 (it) * 2005-04-07 2005-07-07 Mbda italia spa Lanciatore terrestre per missili a lancio verticale.
DE102008009638B3 (de) * 2008-02-18 2009-09-03 Lfk-Lenkflugkörpersysteme Gmbh Werfer mit mindestens einem Startrohr für raketengetriebene Flugkörper
JP2010007948A (ja) * 2008-06-26 2010-01-14 Toshiba Corp 飛翔体発射筒

Also Published As

Publication number Publication date
EP2354751A3 (fr) 2014-10-29
EP2354751A2 (fr) 2011-08-10
DE102010006493B4 (de) 2012-04-26
DE102010006493A1 (de) 2011-08-04

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