EP2354751B1 - Container for a jet propelled missile - Google Patents
Container for a jet propelled missile Download PDFInfo
- 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
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- 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.)
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- 239000007789 gas Substances 0.000 description 5
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- 239000011819 refractory material Substances 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 230000008921 facial expression Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
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- 230000001681 protective effect Effects 0.000 description 1
- 239000002689 soil Substances 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
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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
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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
- F41F3/0413—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.
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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)
- Load-Engaging Elements For Cranes (AREA)
Description
Die Erfindung geht aus von einem Behälter für strahlgetriebene Flugkörper. Derartige Behälter dienen üblicherweise dem Transport, Schutz und Abschuss von strahlgetriebenen Flugkörpern insbesondere von vertikal startenden Flugkörpern.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.
Strahlgetriebene Flugkörper, beispielsweise Raketen, werden auf unterschiedliche Weise abgeschossen. Beispielsweise erfolgt der Abschuss an Bord eines Schiffes oder an Land vom Boden aus. Da ein Antriebsstrahl eines strahlgetriebenen Flugkörpers in der Regel große Impulse und hohe Temperaturen aufweist, ist es häufig erforderlich, den Antriebsstrahl derart umzulenken, dass weder der startende Flugkörper in seiner Funktion beeinträchtigt wird noch eine unerwünschte Schädigung des Umfeldes des startenden Flugkörpers eintritt. Wird beispielsweise der Antriebsstrahl eines vertikal startenden Flugkörpers nicht umgelenkt, so trifft dieser mit hohem Druck auf den Boden auf und breitet sich dort in alle Richtungen aus. Dabei werden lose Teile, wie beispielsweise Steine, unkontrolliert durch die Gegend geschleudert und können den Flugkörper selbst oder andere Gegenstände beschädigen. Zudem kann es aufgrund der heißen Abgase des Antriebsstrahls zu einer zu hohen Temperaturbelastung kommen. Ferner wird die Umgebung durch chemisch aggressive Rückstände des Antriebsstrahles kontaminiert.Jet-propelled missiles, such as rockets, are launched in different ways. For example, the launch takes place aboard a ship or on land from the ground. Since 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. If, for example, 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. In addition, due to the hot exhaust gases of the drive jet, too high a temperature load can occur. Furthermore, the environment is contaminated by chemically aggressive residues of the drive jet.
Da Flugkörper häufig aus einer Startvorrichtung abgeschossen werden, welche mehr als einen Behälter mit darin angeordnetem Flugkörper enthält, besteht zudem die Gefahr, dass beim Start eines Flugkörpers die umliegenden Behälter durch unkontrolliert durch die Gegend geschleuderte Gegenstände, die Hitzeeinwirkung oder chemische Rückstände des Antriebstrahles beeinträchtigt werden.Since missiles are often fired from a launching device containing more than one container with missile disposed therein, there is also the danger that the surrounding containers are affected by uncontrolled thrown by the area objects, the effect of heat or chemical residues of the drive beam at the start of a missile ,
Vor dem Hintergrund der oben geschilderten Sachverhalte wurde bislang an die häufig als Startplattform bezeichnete Startvorrichtung ein Strahlabweiser angebracht, der in der Regel aus einer Stahlplatte besteht. Der Strahlabweiser wird derart ausgerichtet, dass die Antriebsstrahlen von aus der Startvorrichtung heraus abgeschossenen Flugkörpern ohne vorherige Ablenkung auf den Strahlabweiser treffen, von diesem umgelenkt werden und in dieser Weise von der Startvorrichtung weggeführt werden. Der Strahlabweiser ist offensichtlich derart auszulegen, dass er den Impulsen und Hitzebelastungen bei Flugkörperabschüssen standhält. Dies bedingt eine Konstruktion mit vergleichsweise großem Gewicht, welche aufwändig zu positionieren ist. Selbst wenn Startvorrichtung und Strahlabweiser, wie beispielhaft in
Zudem wird der Strahlabweiser in der Regel mehrfach verwendet, was Kontaminationen und Beschädigungen nach sich zieht, sodass eine regelmäßige Instandsetzung des Strahlabweisers erforderlich ist.In addition, the beam deflector is usually used multiple times, resulting in contamination and damage, so that a regular repair of the beam deflector is required.
Aus dem Stand der Technik sind diverse Behälter für Flugkörper bzw. Strahlumlenkeinheiten für Antriebsstrahlen bekannt:Various containers for missiles or beam deflecting units for propulsion jets are known from the prior art:
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Der vorliegenden Erfindung liegt daher die Aufgabe zugrunde, eine aufwandsgünstige Möglichkeit zur Umlenkung des Antriebsstrahls des Flugkörpers zur Verfügung zu stellen.The present invention is therefore based on the object to provide a low-cost option for deflecting the drive beam of the missile available.
Diese Aufgabe wird gelöst durch einen Behälter für einen strahlgetriebenen Flugkörperentsprechend den Merkmalen des Patentanspruchs 1.This object is achieved by a container for a jet-propelled missile according to the features of
Da die Strahlumlenkvorrichtung mit dem Behälter für den strahlgetriebenen Flugkörper, welcher häufig auch als Kanister bezeichnet wird, eine Einheit bildet, wird sie genauso wie der Behälter nach dem Abschuss des Flugkörpers entsorgt. Die Strahlumlenkvorrichtung kann somit im Gegensatz zu dem oben beschriebenen Strahlabweiser in seiner Festigkeit für einen einmaligen Gebrauch ausgelegt werden. Dies erlaubt eine Leichtbauweise der Strahlumlenkvorrichtung. Zudem entfällt eine aufwändige Reinigung kontaminierter Bauteile oder eine Reparatur von Bauteilen. Zudem können Startvorrichtungen mit darin angeordneten Behältern beziehungsweise Flugkörpern einfacher positioniert oder umpositioniert werden. Die Handhabung wird ferner erleichtert durch eine Reduktion des Bauraums, den der erfindungsgemäße Behälter gegenüber einem System mit dem oben beschriebenen Strahlabweiser ermöglicht.Since the Strahlumlenkvorrichtung 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.
Im Hinblick auf mobile Systeme hat sich gezeigt, dass die Erfindung gegenüber einem mobilen System mit Strahlabweiser eine erhöhte Betriebssicherheit ermöglicht, da eine hydraulisch oder mechanisch angetriebene komplexe Mimik für den zum Transport weg zu klappenden Strahlabweiser entfallen kann.With regard to mobile systems, it has been shown that 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.
Die jeweilige Strahlumlenkvorrichtung kann bei dem erfindungsgemäßen Behälter einfach an den in dem Behälter angeordneten Flugkörper angepasst werden. Ein Flugkörper eines anderen Typs wird bereits im Zuge der Fertigung in einem Behälter mit einer anderen, für diesen Flugkörper optimierten Strahlumlenkvorrichtung angeordnet. Infolgedessen können bei Verwendung des erfindungsgemäßen Behälters verschiedene Flugkörpertypen einfach mit derselben Startvorrichtung abgeschossen werden, ohne dass ein Strahlabweiser oder ähnliches angepasst werden muss.The respective Strahlumlenkvorrichtung 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 Strahlumlenkvorrichtung. As a result, when using the container according to the invention different types of missile can be easily launched with the same starting device without a Strahlabweiser or the like must be adjusted.
Eine Ausführungsvariante der Erfindung sieht vor, dass die Strahleintrittsöffnung und die Strahlaustrittsöffnung auf verschiedenen Seiten der Strahlumlenkvorrichtung angeordnet sind, vorzugsweise auf gegenüberliegenden Seiten. Hierdurch kann die mechanische Belastung auf die Strahlumlenkvorrichtung verringert und damit deren Masse reduziert werden.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.
Entsprechend der Erfindung ist eine in dem Strömungskanal angeordnete Keilfläche zur mindest teilweisen Ablenkung eines Antriebsstrahles des Flugkörpers vorgesehen. Die Keilfläche greift unter einem definierten Winkel über eine vorgegebene Länge hinweg und bis zu einer vorgegebenen Position, welche als Eingriff bezeichnet wird, in den Abtriebsstrahl ein und verändert in dieser Weise unter anderem die Richtung des Antriebsstrahles. Der Eingriff kann dabei teilweise oder ganz innerhalb des Antriebsstrahles liegen oder sich auch darüber hinaus erstrecken. Liegt der Eingriff nur teilweise innerhalb des Antriebsstrahles, so wird nur ein Teil des Antriebsstrahles durch die Teilfläche abgelenkt. Auf diese Weise kann eine größere Aufweitung des Antriebsstrahles erreicht werden, was wiederum eine verringerte Wechselwirkung mit der Umgebung zur Folge hat, sodass beispielsweise bei unverfestigtem Untergrund lockerer Boden oder gelockerte Steine in geringerem Ausmaß weggeschleudert werden. Die Geometrie der Keilfläche und der durch sie bewirkten Führung des Antriebsstrahls kann dahingehend optimiert werden, dass die Belastung, insbesondere die Druckbelastung und Reaktionskräfte, auf dem Behälter minimiert ist. In der Praxis hat sich eine Keilfläche bewährt, die mit einer Längsachse des Behälters einen Schnittwinkel von 10° bis 50° bildet. Als vorteilhaft hat sich eine Keilfläche erwiesen, die sich in Längsrichtung des Behälters gemessen über eine Länge von 20 cm bis 50 cm, bevorzugt über eine Länge von 30 cm bis 35 cm erstreckt.According to the invention, 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. The geometry of the wedge surface and the guidance of the drive jet caused by it can be optimized to minimize the stress, in particular the pressure load and reaction forces, on the container. In practice, 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.
Erfindungsgemäß sind zwei voneinander beabstandete und an die Keilfläche angrenzende Seitenflächen vorgesehen, welche mit der Längsachse des Behälters einen Schnittwinkel von 0° bis 20° bilden, wobei vorzugsweise ein Schnittwinkel von 0° vorgesehen ist. Ist hingegen ein von 0° verschiedener Schnittwinkel vorgesehen, sind die Seitenflächen derart ausgerichtet, dass deren Abstand von der Längsachse in Richtung auf die Strahlaustrittsöffnung hin zunimmt. Da die Umlenkung des Antriebsstrahles auf einem Zusammenwirken aller Berandungsflächen des Strömungskanales beruht, kann mit Hilfe der Seitenflächen ein Überdruckgebiet und ein Unterdruckgebiet in der Strahlumlenkvorrichtung generiert und durch die Kombination des Überdruckgebiets mit dem Ünterdruckgebiets die Umlenkwirkung verbessert werden. Zur Ausbildung des Unterdruckgebietes kann vorgesehen sein, dass die Seitenflächen in einen Aufweitungsraum münden, welcher einen gegenüber einem von den Seitenflächen begrenzten Raum vergrößerten Querschnitt aufweist.According to the invention, 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.
In der Praxis haben sich Seitenflächen bewährt, welche im Wesentlichen senkrecht zu der Keilfläche verlaufen.In practice, side surfaces have proven to be substantially perpendicular to the wedge surface.
Zweckmäßigerweise können an der Strahlumlenkvorrichtung, und dort vorzugsweise auf der Seite der Strahlaustrittsöffnung, Steckverbindungen für eine Kontaktierung des Behälters, ein Überdruckventil, eine Feuchtigkeitsanzeige oder ein an sich bekannter Kurbelzugang vorgesehen sein.Expediently, 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.
In einer vorteilhaften Ausführungsvariante der Erfindung ist die Strahlumlenkvorrichtung hermetisch gegenüber der Umgebung des Behälters abgedichtet.In an advantageous embodiment of the invention, the Strahlumlenkvorrichtung is hermetically sealed from the environment of the container.
Es hat sich gezeigt, dass mit dem erfindungsgemäßen Behälter, beziehungsweise Kanister, Startvorgänge von in dem Behälter angeordneten Flugkörpern realisiert werden können, bei welchen sehr geringe Reaktionskräfte auf die Startvorrichtung ausgeübt werden.It has been shown that starting operations of missiles arranged in the container can be realized with the container or canister according to the invention, in which very small reaction forces are exerted on the starting device.
Die für die Strahlumlenkvorrichtung verwendeten Materialien sind offensichtlich derart zu wählen, dass sie den beim Start eines Flugkörpers vorherrschenden Temperaturen standhalten. Zumindest die Ablenkvorrichtungen, beispielsweise Keilflächen oder Wandungsflächen des Strömungskanals, werden vorzugsweise aus einem feuerfesten Material gefertigt. Sollte es zu einem Störfall, wie beispielsweise einem Hangfire kommen, bei dem ein Flugkörper im Behälter verbleibt, so ist die Verwendung feuerfesten Materials besonders geschickt, um größere Beschädigungen zu verhindern.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.
Im Folgenden wird die Erfindung anhand von Figuren näher erläutert. Soweit zweckdienlich sind hierin gleichwirkende Elemente mit gleichen Bezugszeichen versehen. Es zeigen:
- Fig. 1
- Lastkraftwagenbasierte Startvorrichtung mit einem Strahlabweiser gemäß dem Stand der Technik.
- Fig. 2
- Teildarstellung eines Behälters in schematischer Darstellung.
- Fig. 3
- Schematische Teilschnittdarstellung durch den Behälter der
Fig. 2 . - Fig. 4
- Schematische Schnittdarstellung durch ein Ausführungsbeispiel des erfindungsgemäßen Behälters.
- Fig. 5
- Perspektivische Detaildarstellung der Strahlumlenkvorrichtung des Behälters aus
Fig. 4 . - Fig. 6
- Schematische Schnittdarstellung durch die Strahlumlenkvorrichtung aus
Fig. 5 entlang A-A.
- Fig. 1
- Truck-based launching device with a jet deflector according to the prior art.
- Fig. 2
- Partial representation of a container in a schematic representation.
- Fig. 3
- Schematic partial sectional view through the container of
Fig. 2 , - Fig. 4
- Schematic sectional view through an embodiment of the container according to the invention.
- Fig. 5
- Perspective detail of the Strahlumlenkvorrichtung the container
Fig. 4 , - Fig. 6
- Schematic sectional view through the Strahlumlenkvorrichtung
Fig. 5 along AA.
Die
Die Strahleintrittsöffnung 23 und die Strahlaustrittsöffnung 25 sind über einen Strömungskanal 27 miteinander verbunden. Wie
Die Strahlaustrittsöffnung 25 ist mit einem Deckel 13 versehen, welcher Sollbruchstellen 15 aufweist. Bei einem Start des Flugkörpers 3 wird somit der Deckel 13 durch den Antriebsstrahl geöffnet, sodass dieser entweichen kann. Als Sicherheitsmaßnahme ist ein Überdruckventil an der Strahlumlenkvorrichtung 5 vorgesehen.The jet outlet opening 25 is provided with a
Für die Montage des Behälters 1 an einer Startvorrichtung sind im vorliegenden Ausführungsbeispiel Zentrierbolzen 19 sowie ein Verriegelungszapfen 21 vorgesehen. Zweckmäßiger Weise ist an der Seite der Strahlaustrittsöffnung 25 eine Feuchtigkeitsanzeige 7 sowie ein an sich bekannter Kurbelzugang 9 angeordnet. Auf diese Weise bleiben die Feuchtigkeitsanzeige und der Kurbelzugang bei einer Montage des Behälters 1 in einer Startvorrichtung zugänglich beziehungsweise einsehbar.For the assembly of the
Wird der Flugkörper 3 gestartet, gelangt der Antriebsstrahl durch eine Strahleintrittsöffnung 56 in den Strömungskanal 27, wird dort teilweise von der Keilfläche 52 abgelenkt und tritt durch die Strahlaustrittsöffnung 58 aus der Strahlumlenkvorrichtung 50 heraus.When the
Der teilweise Eingriff der Keilfläche 52 in den Antriebsstrahl bewirkt vorliegend eine starke Aufweitung des Antriebsstrahls, was eine verringerte Wechselwirkung des Antriebsstrahls mit der Umgebung zur Folge hat. Insbesondere wird loser Untergrund wie Steine weniger stark aufgewirbelt. Die Gefahr einer Beschädigung des Behälters 51 oder anderer in der Umgebung befindlicher Gegenstände wird somit verringert.The partial engagement of the
Wie
Bei einer Verwendung der Strahlumlenkvorrichtung 50 gemäß den Darstellungen der
In Analogie zur Strahlenumlenkvorrichtung 5 aus den
Wie die Beispiele der
Sofern eine Reduzierung von auf den Behälter wirkenden Kräften gewünscht ist, kann dies dadurch erreicht werden, dass für die Strahlumlenkvorrichtung, oder einen Teil von ihr, eine Anlagefläche oder Halterung in der Startvorrichtung vorgesehen wird.If a reduction of forces acting on the container is desired, 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.
- 11
- Behältercontainer
- 33
- Flugkörpermissile
- 55
- Strahlumlenkvorrichtungbeam bending
- 77
- Feuchtigkeitsanzeigehumidity display
- 99
- Kurbelzugangcrank access
- 1111
- ÜberdruckventilPressure relief valve
- 1313
- Deckel auf StrahlaustrittsöffnungCover on jet outlet
- 1515
- SollbruchstelleBreaking point
- 1717
- Steckeranschlussconnector
- 1919
- Zentrierbolzencentering
- 2121
- Verriegelungszapfenlocking pin
- 2323
- StrahleintrittsöffnungBeam entrance opening
- 2525
- StrahlaustrittsöffnungBlast opening
- 2727
- Strömungskanalflow channel
- 2929
- Wandungsfläche StrömungskanalWall surface flow channel
- 5050
- Strahlumlenkvorrichtungbeam bending
- 5151
- Behältercontainer
- 5252
- Keilflächewedge surface
- 5353
- Aufweitungsraumexpansion space
- 5454
- Seitenflächeside surface
- 5555
- Eingriffintervention
- 5656
- StrahleintrittsöffnungBeam entrance opening
- 5858
- StrahlaustrittsöffnungBlast opening
- 6060
- Längsachse BehälterLongitudinal axis container
- 7070
- Starvorrichtung auf LastkraftwagenStar device on truck
- 72a72a
- Behältercontainer
- 72b72b
- Behältercontainer
- 7474
- StrahlabweiserStrahlabweiser
- αα
- Schnittwinkelcutting angle
Claims (5)
- Container (51) for a jet-propelled missile (3) havinga) a jet deflection device (50), having a jet entry opening (56) and a jet exit opening (58), the latter being interconnected by a flow duct (27),b) a wedge face (52) which is disposed in the flow duct (27), wherein, for at least partially diverting a propulsion jet of the missile (3), the wedge face (52) within the jet deflection device (50), commencing from one internal container side, in relation to the longitudinal axis (60) of the container (51) extends at an inclination in the direction of the opposite internal container side, andc) two lateral faces (54) which are mutually spaced apart and are adjacent to the wedge face (52) and are located within the jet deflection device (50), and which in relation to the longitudinal axis (60) of the container (51) form an angle of intersection of 0° to 20°,characterized in that
the lateral faces (54) open into an expansion space (53) which is located within the jet deflection device (50) and which, in relation to a space which within the jet deflection device (50) is delimited by the lateral faces (54), has an enlarged cross section. - Container (51) according to Claim 1, wherein the jet entry opening (56) and the jet exit opening (58) are disposed on different sides of the jet deflection device (50), preferably on opposite sides.
- Container (51) according to Claim 1 or 2, wherein the wedge face (52) in relation to a longitudinal axis (60) of the container (51) forms an angle of intersection (α) of 10° to 50°.
- Container (51) according to one of the preceding claims, wherein the wedge face (52), when measured in the longitudinal direction of the container (51), extends across a length of 20 cm to 50 cm, in particular of 30 cm to 35 cm.
- Container (51) according to one of the preceding claims, wherein the two lateral faces (54) run so as to be substantially perpendicular to the wedge face (52).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE201010006493 DE102010006493B4 (en) | 2010-02-02 | 2010-02-02 | Container for a jet-propelled missile |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2354751A2 EP2354751A2 (en) | 2011-08-10 |
EP2354751A3 EP2354751A3 (en) | 2014-10-29 |
EP2354751B1 true EP2354751B1 (en) | 2016-05-25 |
Family
ID=43902838
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11000643.4A Active EP2354751B1 (en) | 2010-02-02 | 2011-01-27 | Container for a jet propelled missile |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2354751B1 (en) |
DE (1) | DE102010006493B4 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2543439C1 (en) * | 2013-10-09 | 2015-02-27 | Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" | Device for launching rockets |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH01124494A (en) * | 1987-11-07 | 1989-05-17 | Brother Ind Ltd | Sewing machine wherein thread can be set by one touch operation |
DE4112287A1 (en) * | 1991-04-15 | 1992-10-22 | Israel Aircraft Ind Ltd | Housing for pair of guided missiles - has outlet positioned between tail edge of missiles for gases generated by missile launching |
US5153367A (en) * | 1991-09-17 | 1992-10-06 | Fmc Corporation | Cocoon launcher and storage system |
JP3396449B2 (en) * | 1999-09-17 | 2003-04-14 | 三菱重工業株式会社 | Flying object launcher and flying object canister |
JP2001124494A (en) * | 1999-10-25 | 2001-05-11 | Mitsubishi Electric Corp | Discharger for flier |
ITRM20050166A1 (en) * | 2005-04-07 | 2005-07-07 | Mbda italia spa | TERRESTRIAL LAUNCHER FOR VERTICAL LAUNCHES. |
DE102008009638B3 (en) * | 2008-02-18 | 2009-09-03 | Lfk-Lenkflugkörpersysteme Gmbh | Launcher with at least one launch tube for rocket-propelled missiles |
JP2010007948A (en) * | 2008-06-26 | 2010-01-14 | Toshiba Corp | Missile launching tube |
-
2010
- 2010-02-02 DE DE201010006493 patent/DE102010006493B4/en active Active
-
2011
- 2011-01-27 EP EP11000643.4A patent/EP2354751B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
EP2354751A2 (en) | 2011-08-10 |
DE102010006493B4 (en) | 2012-04-26 |
EP2354751A3 (en) | 2014-10-29 |
DE102010006493A1 (en) | 2011-08-04 |
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