EP3637035B1 - Launch rail for a missile - Google Patents
Launch rail for a missile Download PDFInfo
- Publication number
- EP3637035B1 EP3637035B1 EP19199162.9A EP19199162A EP3637035B1 EP 3637035 B1 EP3637035 B1 EP 3637035B1 EP 19199162 A EP19199162 A EP 19199162A EP 3637035 B1 EP3637035 B1 EP 3637035B1
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- EP
- European Patent Office
- Prior art keywords
- missile
- holding device
- launch rail
- rail
- launch
- 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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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
- F41F3/0406—Rail launchers
-
- 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
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
Definitions
- the present invention relates to a launch rail for a missile with a detachable holding device.
- a launch rail is for example in U.S. 5,094,140A disclosed.
- a starting process that is as stable as possible is of great importance for the flight behavior of unmanned missiles, such as guided missiles or the like.
- Launch rails are used for this purpose, which ensure that the missile moves in a straight line until it has reached a certain speed and emerges from the launch rail.
- brackets are attached to the missiles, which allow the respective missile to be arranged on a launch rail.
- the weight and the aerodynamic properties of the contour have a major impact on the flight behavior and functionality of a missile. Therefore, it would be desirable to be able to dispense with externally attached mounts on a missile.
- the object of the present invention is to improve the aerodynamic properties of a missile with additional weight savings by means of an improved launch rail.
- a launch rail for a missile has a rail body, a releasable holding device mounted on the rail body for holding the missile on the launch rail, and a release mechanism mounted on the rail body for releasing the holding device from the missile.
- the holding device has a locking element for locking the missile on the holding device and the triggering mechanism is designed to open the locking element.
- the locking element is designed as a pin, which is designed to positively engage in the missile from above, wherein the locking element can be lifted out of the missile and the locking of the missile can thereby be opened.
- the holding device is designed to hold the tail of the missile, and the holding device has a support element for supporting the missile, the support element being designed as a pin and the pin being designed to positively engage the tail of the missile from behind.
- One idea on which the present invention is based is to design the holder with which the missile is held on the launch rail so that it can be detached from the missile. Accordingly, weight can be saved in the missile, since there are no components attached to the missile for mounting on the launch rail. Furthermore, the omission of external components for mounting allows an advantageous aerodynamic shape of the missile.
- the locking element advantageously prevents the missile from detaching prematurely from the holding device.
- a design of the locking element as a pin, which engages in the missile in a form-fitting manner, represents a design of a locking element that is advantageously easy to implement.
- the holding device has a support element for supporting the missile, the launch process of the missile can be advantageously stabilized.
- the fact that the support element is designed as a pin according to the invention represents an embodiment of a support element that is advantageously easy to construct.
- the missile can be detached from the holding device in a particularly stable manner.
- the holding device is designed to hold the tail end of the missile allows the holding device to be detached from the missile in an advantageously easy manner.
- the mechanism can have a ramp section which is designed to guide the pin out of the missile.
- the holding device can be mounted on the rail body so that it can move linearly along the rail body.
- the missile can be held by the holding device throughout the launch process, as a result of which a stable launch process can be implemented.
- the triggering mechanism can be arranged at an exit end of the rail body. This advantageously maximizes the path length over which the missile is sustained during launch.
- the triggering mechanism can have a projection which is designed to stop a movement of the holding device. This represents a particularly easy-to-manufacture embodiment of a triggering mechanism for releasing the missile from the holding device.
- Fig. 1a shows a schematic view of a launch rail 100 according to an embodiment of the present invention before the launch of a missile 200 held in the launch rail.
- the launch rail 100 has a rail body 110 , a releasable holding device 120 and a release mechanism 130 .
- the holding device 120 is arranged at a bearing end of the rail body 110 .
- the trigger mechanism 130 is located at the opposite exit end of the rail body 110 .
- the holding device 120 holds the tail of a missile 200.
- the triggering mechanism 130 also has a projection 131 on.
- Fig. 1b shows the in Fig. 1a shown launch rail 100 during the launch process of the missile 200.
- the missile 200 moves forward along the track body 110 .
- the holding device 120 holding the missile 200 moves together with the missile 200 and keeps it stable during the launch process. to the in Fig. 1b shown point in time, the holding device 120 hits the triggering mechanism 130. As a result, the holding device 120 is released from the missile 200.
- FIG. 1c shows the in Fig. 1a shown launch rail 100 after the launch process of the missile 200.
- the missile 200 released from the holding device 120 and thus from the launch rail 100, continues its movement in the forward direction.
- the holding device 120 was released from the missile 200 by the triggering mechanism 130 and remains on the launch rail 100.
- FIG. 2 shows a schematic rear view of the launch rail 100 and the missile 200.
- the holding device 120 is movably mounted on the rail body 110 .
- the holding device has two locking elements 121 .
- the locking elements 121 are in the form of pins which engage in a form-fitting manner in the missile 200 from above.
- the holding device 120 has two support elements 122 .
- the support elements 122 are in the form of pins which engage in a form-fitting manner in the missile 200 from behind.
- the locking elements 121 and support elements 122 prevent movement of the missile 200 relative to the holding device 120.
- the missile 200 is accordingly held securely by the holding device 120 on the launch rail 100.
- An optional further locking device is not shown, which can be provided in order to prevent a movement of the holding device 120 until shortly before the planned launch of the missile 200.
- FIG. 3 shows a schematic sectional view of the holding device 120.
- the holding device 120 has a locking element 121 and a support element 122 .
- the locking element 121 is designed as a pin which engages in a form-fitting manner in the missile 200 from above.
- the support element 122 is designed as a pin which engages in the tail of the missile 200 from behind in a form-fitting manner.
- FIG. 4 shows a schematic sectional view of the interaction of the triggering mechanism 130 and the holding device 120.
- the trigger mechanism 130 includes a ramp portion 132 .
- the missile 200 After the drive of the missile 200 has been ignited, it moves forward together with the movably mounted holding device 120 in the direction of the triggering mechanism 130.
- the head of the locking element 121 designed as a pin engages in the ramp section 132 of the triggering mechanism 130.
- the sliding of the head of the pin causes the locking element 121 to move vertically upwards, as indicated by an arrow P1.
- the locking element 121 is thereby lifted out of the missile 200, as a result of which the locking of the missile 200 is opened.
- figure 5 shows a further schematic sectional view of the interaction of triggering mechanism 130 and holding device 120.
- the holding device 120 comes into contact with the projection 131 of the triggering mechanism 130.
- the projection 131 thereby stops the further movement of the holding device 120, as indicated by an arrow P2 pointing to the right.
- the locking element 121 has already been pushed up the ramp section 132 to such an extent that it is no longer in contact with the missile 200 .
- the holding device 120 is released from the missile 200 .
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
Die vorliegende Erfindung betrifft eine Startschiene für einen Flugkörper mit einer lösbaren Halteeinrichtung. Eine derartige Startschiene ist beispielsweise in der
Für das Flugverhalten von unbemannten Flugkörpern, wie beispielsweise Lenkraketen oder dergleichen, ist ein möglichst stabiler Startvorgang von großer Bedeutung. Zu diesem Zweck kommen Startschienen zur Anwendung, die eine geradlinige Bewegung des Flugkörpers gewährleisten, bis dieser eine gewisse Geschwindigkeit erreicht hat und aus der Startschiene austritt. Hierfür werden Halterungen an den Flugkörpern angebracht, welche es erlauben, den jeweiligen Flugkörper an einer Startschiene anzuordnen.A starting process that is as stable as possible is of great importance for the flight behavior of unmanned missiles, such as guided missiles or the like. Launch rails are used for this purpose, which ensure that the missile moves in a straight line until it has reached a certain speed and emerges from the launch rail. For this purpose, brackets are attached to the missiles, which allow the respective missile to be arranged on a launch rail.
Das Gewicht und die aerodynamischen Eigenschaften der Kontur haben einen großen Einfluss auf Flugverhalten und Funktionalität eines Flugkörpers. Daher wäre es wünschenswert, auf extern angebrachte Halterungen an einem Flugkörper verzichten zu können.The weight and the aerodynamic properties of the contour have a major impact on the flight behavior and functionality of a missile. Therefore, it would be desirable to be able to dispense with externally attached mounts on a missile.
Vor diesem Hintergrund liegt der vorliegenden Erfindung die Aufgabe zugrunde, mittels einer verbesserten Startschiene die aerodynamischen Eigenschaften eines Flugkörpers bei zusätzlicher Gewichtseinsparung zu verbessern.Against this background, the object of the present invention is to improve the aerodynamic properties of a missile with additional weight savings by means of an improved launch rail.
Erfindungsgemäß wird diese Aufgabe gelöst durch eine Startschiene mit den Merkmalen des Patentanspruchs 1.According to the invention, this object is achieved by a launch rail with the features of
Demgemäß ist eine Startschiene für einen Flugkörper vorgesehen. Die Startschiene weist einen Schienenkörper, eine an dem Schienenkörper gelagerte, lösbare Halteeinrichtung zur Halterung des Flugkörpers an der Startschiene und einen an dem Schienenkörper gelagerten Auslösemechanismus zur Lösung der Halteeinrichtung von dem Flugkörper auf. Dabei weist die Halteeinrichtung ein Verriegelungselement zur Verriegelung des Flugkörpers an der Halteeinrichtung auf und der Auslösemechanismus ist dazu ausgebildet, das Verriegelungselement zu öffnen. Ferner ist das Verriegelungselement als Pin ausgebildet, der dafür ausgebildet ist, von oben formschlüssig in den Flugkörper einzugreifen, wobei das Verriegelungselement aus dem Flugkörper heraushebbar ist und hierdurch die Verriegelung des Flugkörpers geöffnet werden kann. Ferner ist die Halteeinrichtung dazu ausgebildet, das Heck des Flugkörpers zu halten, und die Halteeinrichtung weist ein Stützelement zur Abstützung des Flugkörpers auf, wobei das Stützelement als Pin ausgebildet ist und der Pin dazu ausgebildet ist, von hinten formschlüssig in das Heck des Flugkörpers einzugreifen.Accordingly, a launch rail for a missile is provided. The launch rail has a rail body, a releasable holding device mounted on the rail body for holding the missile on the launch rail, and a release mechanism mounted on the rail body for releasing the holding device from the missile. The holding device has a locking element for locking the missile on the holding device and the triggering mechanism is designed to open the locking element. Furthermore, the locking element is designed as a pin, which is designed to positively engage in the missile from above, wherein the locking element can be lifted out of the missile and the locking of the missile can thereby be opened. Furthermore, the holding device is designed to hold the tail of the missile, and the holding device has a support element for supporting the missile, the support element being designed as a pin and the pin being designed to positively engage the tail of the missile from behind.
Eine der vorliegenden Erfindung zugrunde liegende Idee besteht darin, die Halterung mit der der Flugkörper an der Startschiene gehalten wird von dem Flugkörper lösbar auszubilden. Demnach kann bei dem Flugkörper Gewicht eingespart werden, da an dem Flugkörper angebrachte Bauteile zur Halterung an der Startschiene entfallen. Des Weiteren ermöglicht der Verzicht auf externe Bauteile zur Halterung eine vorteilhaft aerodynamische Form des Flugkörpers.One idea on which the present invention is based is to design the holder with which the missile is held on the launch rail so that it can be detached from the missile. Accordingly, weight can be saved in the missile, since there are no components attached to the missile for mounting on the launch rail. Furthermore, the omission of external components for mounting allows an advantageous aerodynamic shape of the missile.
Das Verriegelungselement verhindert vorteilhafterweise, dass sich der Flugkörper verfrüht von der Halteeinrichtung löst.The locking element advantageously prevents the missile from detaching prematurely from the holding device.
Eine Ausbildung des Verriegelungselements als Pin, der in den Flugkörper formschlüssig eingreift, stellt eine vorteilhaft leicht zu verwirklichende Ausbildung eines Verriegelungselements dar.A design of the locking element as a pin, which engages in the missile in a form-fitting manner, represents a design of a locking element that is advantageously easy to implement.
Dadurch, dass erfindungsgemäß die Halteeinrichtung ein Stützelement zur Abstützung des Flugkörpers aufweist, kann der Startvorgang des Flugkörpers vorteilhaft stabilisiert werden.Because, according to the invention, the holding device has a support element for supporting the missile, the launch process of the missile can be advantageously stabilized.
Dass erfindungsgemäß das Stützelement als Pin ausgebildet ist, stellt eine vorteilhaft leicht zu konstruierende Ausführungsform eines Stützelements dar.The fact that the support element is designed as a pin according to the invention represents an embodiment of a support element that is advantageously easy to construct.
Bei einer Ausbildung des Pins dazu, in den Flugkörper einzugreifen, kann der Flugkörper besonders stabil von der Halteeinrichtung gelöst werden.If the pin is designed to engage in the missile, the missile can be detached from the holding device in a particularly stable manner.
Dass erfindungsgemäß die Halteeinrichtung dazu ausgebildet ist, das Heck des Flugkörpers zu halten, ermöglicht eine vorteilhaft leichte Lösung der Halteeinrichtung von dem Flugkörper.The fact that, according to the invention, the holding device is designed to hold the tail end of the missile allows the holding device to be detached from the missile in an advantageously easy manner.
Vorteilhafte Ausgestaltungen und Weiterbildungen ergeben sich aus den weiteren Unteransprüchen sowie aus der Beschreibung unter Bezugnahme auf die Figuren.Advantageous refinements and developments result from the further dependent claims and from the description with reference to the figures.
Gemäß einer Weiterbildung kann der Mechanismus einen Rampenabschnitt aufweisen, der dazu ausgebildet ist, den Pin aus dem Flugkörper zu führen. Dies stellt eine vorteilhaft einfach zu konstruierende Ausführungsform des Auslösemechanismus zum Öffnen des Verriegelungselements dar.According to a further development, the mechanism can have a ramp section which is designed to guide the pin out of the missile. This represents an embodiment of the release mechanism for opening the locking element that is advantageously easy to construct.
Gemäß eines weiteren Ausführungsbeispiels kann die Halteeinrichtung an dem Schienenkörper entlang des Schienenkörpers linear beweglich gelagert sein. Hierdurch kann der Flugkörper über den Startvorgang hinweg durch die Halteeinrichtung gehalten werden, wodurch sich ein stabiler Startvorgang realisieren lässt.According to a further exemplary embodiment, the holding device can be mounted on the rail body so that it can move linearly along the rail body. As a result, the missile can be held by the holding device throughout the launch process, as a result of which a stable launch process can be implemented.
Gemäß einer Weiterbildung kann der Auslösemechanismus an einem Austrittsende des Schienenkörpers angeordnet sein. Hierdurch wird der Weglänge, über die hinweg der Flugkörper während des Startvorgangs gehalten wird, vorteilhaft maximiert.According to a further development, the triggering mechanism can be arranged at an exit end of the rail body. This advantageously maximizes the path length over which the missile is sustained during launch.
Gemäß einer Weiterbildung kann der Auslösemechanismus einen Vorsprung aufweisen, der dazu ausgebildet ist, eine Bewegung der Halteeinrichtung zu stoppen. Dies stellt eine besonders leicht zu fertigende Ausführungsform eines Auslösemechanismus zum Lösen des Flugkörpers von der Halteeinrichtung dar.According to a further development, the triggering mechanism can have a projection which is designed to stop a movement of the holding device. This represents a particularly easy-to-manufacture embodiment of a triggering mechanism for releasing the missile from the holding device.
Die obigen Ausgestaltungen und Weiterbildungen lassen sich, sofern sinnvoll, beliebig miteinander kombinieren. Weitere mögliche Ausgestaltungen, Weiterbildungen und Implementierungen der Erfindung umfassen auch nicht explizit genannte Kombinationen von zuvor oder im Folgenden bezüglich der Ausführungsbeispiele beschriebenen Merkmale der Erfindung. Insbesondere wird dabei der Fachmann auch Einzelaspekte als Verbesserungen oder Ergänzungen zu der jeweiligen Grundform der vorliegenden Erfindung hinzufügen.The above configurations and developments can be combined with one another as desired, insofar as this makes sense. Further possible refinements, developments and implementations of the invention also include combinations of features of the invention described above or below with regard to the exemplary embodiments that are not explicitly mentioned. In particular, the person skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.
Im allgemeinen Teil der Beschreibung ist die Verwendung der Singularform für einzelne Merkmale der Erfindung als ein "mindestens" zu verstehen. Der Fachmann wird ohne weiteres die genaue Anzahl der vorzusehenden Merkmale auswählen können ohne dabei den Rahmen der vorliegenden Erfindung zu verlassen.In the general part of the description, the use of the singular form for individual features of the invention is to be understood as “at least”. Those skilled in the art will readily be able to select the precise number of features to be included without departing from the scope of the present invention.
Die vorliegende Erfindung wird nachfolgend anhand der in den schematischen Figuren angegebenen Ausführungsbeispiele näher erläutert. Es zeigen dabei:
- Fig. 1a - 1c
- schematische Ansichten einer Startschiene nach einem Ausführungsbeispiel der vorliegenden Erfindung zu verschiedenen Zeitpunkten eines Startvorgangs eines Flugkörpers;
- Fig.2
- eine schematische Rückansicht der in
Fig. 1 gezeigten Startschiene; - Fig. 3
- eine schematische Schnittansicht einer Halteeinrichtung der in
Fig. 1 gezeigten Startschiene; - Fig. 4
- eine schematische Schnittansicht des Zusammenwirkens des Auslösemechanismus und der Halteeinrichtung der in
Fig. 1 gezeigten Startschiene; und - Fig. 5
- eine weitere schematische Schnittansicht des Zusammenwirkens des Auslösemechanismus und der Halteeinrichtung der in
Fig. 1 gezeigten Startschiene.
- Figures 1a - 1c
- schematic views of a launch rail according to an embodiment of the present invention at different times of a launch process of a missile;
- Fig.2
- a schematic rear view of in
1 shown launch rail; - 3
- a schematic sectional view of a holding device in
1 shown launch rail; - 4
- a schematic sectional view of the interaction of the triggering mechanism and the holding device in
1 shown launch rail; and - figure 5
- a further schematic sectional view of the interaction of the triggering mechanism and the holding device in
1 shown starting rail.
Die beiliegenden Figuren sollen ein weiteres Verständnis der Ausführungsformen der Erfindung vermitteln. Sie veranschaulichen Ausführungsformen und dienen im Zusammenhang mit der Beschreibung der Erklärung von Prinzipien und Konzepten der Erfindung. Andere Ausführungsformen und viele der genannten Vorteile ergeben sich im Hinblick auf die Zeichnungen. Die Elemente der Zeichnungen sind nicht notwendigerweise maßstabsgetreu zueinander gezeigt.The accompanying figures are intended to provide a further understanding of embodiments of the invention. They illustrate embodiments and, together with the description, serve to explain principles and concepts of the invention. Other embodiments and many of the foregoing advantages will become apparent by reference to the drawings. The elements of the drawings are not necessarily shown to scale with respect to one another.
In den Figuren der Zeichnung sind gleiche, funktionsgleiche und gleich wirkende Elemente, Merkmale und Komponenten - sofern nichts anderes ausgeführt ist - jeweils mit denselben Bezugszeichen versehen.In the figures of the drawing, elements, features and components that are the same, have the same function and have the same effect--unless stated otherwise--are each provided with the same reference symbols.
Die Startschiene 100 weist einen Schienenkörper 110, eine lösbare Halteeinrichtung 120 und einen Auslösemechanismus 130 auf. Die Halteeinrichtung 120 ist an einem Lagerungsende des Schienenkörpers 110 angeordnet. Der Auslösemechanismus 130 ist an dem gegenüberliegenden Austrittsende des Schienenkörpers 110 angeordnet. Die Halteeinrichtung 120 hält das Heck eines Flugkörpers 200. Der Auslösemechanismus 130 weist weiterhin einen Vorsprung 131 auf.The
Die Vorteile der vorliegenden Startschiene 100, die Halteeinrichtung 120 lösbar von dem Flugkörper 200 auszubilden werden erst nach der Initiierung des Starts des Flugkörpers 200 in den folgenden
Der Flugkörper 200 bewegt sich entlang des Schienenkörpers 110 nach vorne. Die den Flugkörper 200 haltende Halteeinrichtung 120 bewegt sich zusammen mit dem Flugkörper 200 und hält diesen während des Startvorgangs stabil. Zu dem in
Der von der Halteeinrichtung 120 und damit von der Startschiene 100 gelöste Flugkörper 200 setzt seine Bewegung in Vorwärtsrichtung fort. Die Halteeinrichtung 120 wurde durch den Auslösemechanismus 130 von dem Flugkörper 200 gelöst und verbleibt an der Startschiene 100.The
In dieser Ansicht ist erkennbar, dass die Halteeinrichtung 120 beweglich an dem Schienenkörper 110 gelagert ist. Die Halteeinrichtung weist zwei Verriegelungselemente 121 auf. Die Verriegelungselemente 121 sind in dieser Ausführungsform als Pins ausgebildet, die von oben in den Flugkörper 200 formschlüssig eingreifen. Des Weiteren weist die Halteeinrichtung 120 zwei Stützelemente 122 auf. Die Stützelemente 122 sind in dieser Ausführungsform als Pins ausgebildet, die von hinten formschlüssig in den Flugkörper 200 eingreifen.In this view it can be seen that the holding
Die Verriegelungselemente 121 und Stützelemente 122 verhindern eine Bewegung des Flugkörpers 200 relativ zu der Halteeinrichtung 120. Der Flugkörper 200 wird demnach sicher durch die Halteeinrichtung 120 an der Startschiene 100 gehalten. Nicht dargestellt ist eine optionale weitere Verriegelungseinrichtung, welche vorgesehen sein kann um eine Bewegung der Halteeinrichtung 120 bis kurz vor dem geplanten Start des Flugkörpers 200 zu unterbinden.The locking
Auch in dieser Darstellung ist erkennbar, dass die Halteeinrichtung 120 ein Verriegelungselement 121 und ein Stützelement 122 aufweist. Das Verriegelungselement 121 ist als Pin ausgebildet, der von oben formschlüssig in den Flugkörper 200 eingreift. Das Stützelement 122 ist als Pin ausgebildet, der von hinten formschlüssig in das Heck des Flugkörpers 200 eingreift.It can also be seen in this representation that the holding
Der Auslösemechanismus 130 weist einen Rampenabschnitt 132 auf.The
Nachdem der Antrieb des Flugkörpers 200 gezündet wurde, bewegt sich dieser mitsamt der beweglich gelagerten Halteeinrichtung 120 nach vorne in Richtung des Auslösemechanismus 130. Der Kopf des als Pin ausgebildeten Verriegelungselements 121 greift in den Rampenabschnitt 132 des Auslösemechanismus 130 ein. Das Gleiten des Kopfes des Pins bewirkt eine vertikale Bewegung des Verriegelungselements 121 nach oben, wie durch einen Pfeil P1 angedeutet. Das Verriegelungselement 121 wird dadurch aus dem Flugkörper 200 herausgehoben, wodurch die Verriegelung des Flugköpers 200 geöffnet wird.After the drive of the
Nach weiterer Vorwärtsbewegung des Flugkörpers 200 kommt die Halteeinrichtung 120 in Kontakt mit dem Vorsprung 131 des Auslösemechanismus 130. Der Vorsprung 131 stoppt dabei die weitere Bewegung der Halteeinrichtung 120, wie durch einen nach rechts gerichteten Pfeil P2 angedeutet ist. Das Verriegelungselement 121 ist zu diesem Zeitpunkt bereits soweit auf dem Rampenabschnitt 132 nach oben verschoben worden, dass es den Flugkörper 200 nicht mehr kontaktiert.After further forward movement of the
Da sich der Flugkörper 200 hierdurch nunmehr ungehindert weiter bewegen kann, wird die Halteeinrichtung 120 von dem Flugkörper 200 gelöst.Since the
Die vorliegende Erfindung wurde hier anhand eines expliziten Ausführungsbeispiels beschrieben. Sie soll jedoch keines Wegs auf dieses eine Ausführungsbeispiel beschränkt sein. Insbesondere sind für die diversen Bauteile der vorliegenden Erfindung auch andere Ausgestaltungsformen denkbar.The present invention has been described here on the basis of an explicit exemplary embodiment. However, it should in no way be limited to this one embodiment. In particular, other configurations are also conceivable for the various components of the present invention.
So wäre es denkbar an Stelle des Rampenabschnitts des Auslösemechanismus eine mechanische Feder oder einen Keilabschnitt vorzusehen, um das Verriegelungselement zu öffnen.It would thus be conceivable to provide a mechanical spring or a wedge section instead of the ramp section of the triggering mechanism in order to open the locking element.
- 100100
- Startschienelaunch rail
- 110110
- Schienenkörperrail body
- 120120
- Halteeinrichtungholding device
- 121121
- Verriegelungselementlocking element
- 122122
- Stützelementsupport element
- 130130
- Auslösemechanismustrigger mechanism
- 131131
- Vorsprunghead Start
- 132132
- Rampenabschnittramp section
- 200200
- Flugkörpermissile
- P1, P2P1, P2
- PfeilArrow
Claims (6)
- Launch rail (100) for a missile (200), having a rail body (110);a holding device (120) that is mounted in a detachable manner on the rail body (110) so as to hold the missile (200) on the launch rail (100), anda release mechanism (130) that is mounted on the rail body (110) so as to release the holding device (120) from the missile (200);wherein the holding device (120) comprises a locking element (121) for locking the missile (200) to the holding device (120) and the release mechanism (130) is embodied so as to open the locking element (121);wherein the locking element (121) is embodied as a pin that is embodied for the purpose of engaging from above in a positive-locking manner into the missile (200);wherein the locking element (121) can be lifted out of the missile (200) and as a consequence it is possible to open the locking arrangement of the missile (200);wherein the holding device (120) is embodied for the purpose of holding the tail of the missile (200) and the holding device (120) comprises a supporting element (122) for supporting the missile (200), wherein the supporting element (122) is embodied as a pin and the pin is embodied so as to engage from the rear in a positive-locking manner into the tail of the missile (200).
- Launch rail (100) according to claim 1,
wherein the release mechanism (130) comprises a ramp section (132) that is embodied so as to guide the pin out of the missile body (200). - Launch rail (100) according to one of the preceding claims,
wherein the holding device (120) is mounted on the rail body (110) so that said holding device can move in a linear manner along the rail body (110). - Launch rail (100) according to claim 3,
wherein the release mechanism (130) is arranged on a discharge end of the rail body (110). - Launch rail (100) according to claim 4,
wherein the release mechanism (130) comprises a projection (131) that is embodied so as to stop a movement of the holding device (120). - Missile launch system having a launch rail (100) according to one of the preceding claims and a missile (200).
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102018008008.1A DE102018008008A1 (en) | 2018-10-10 | 2018-10-10 | Starting rail for a missile |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP3637035A1 EP3637035A1 (en) | 2020-04-15 |
| EP3637035B1 true EP3637035B1 (en) | 2022-08-17 |
Family
ID=68066596
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP19199162.9A Active EP3637035B1 (en) | 2018-10-10 | 2019-09-24 | Launch rail for a missile |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3637035B1 (en) |
| DE (1) | DE102018008008A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112361873A (en) * | 2020-11-03 | 2021-02-12 | 西安航天动力技术研究所 | Rail-mounted launch rocket's loading mechanism that goes into rail |
| CN116123932B (en) * | 2023-03-01 | 2025-08-22 | 西安航天动力技术研究所 | A rocket support mechanism capable of automatically falling off |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3040629A (en) * | 1960-04-11 | 1962-06-26 | Garnett C Duncan | Missile launcher |
| DE3016925A1 (en) * | 1980-05-02 | 1981-11-12 | Dornier Gmbh, 7990 Friedrichshafen | STARTING DEVICE FOR CARRYING AND STARTING AIRCRAFT, IN PARTICULAR FOR AIRCRAFT |
| US4660456A (en) * | 1983-10-03 | 1987-04-28 | Frazer-Nash Limited | Airborne missile launcher of modular construction |
| US5094140A (en) * | 1991-03-11 | 1992-03-10 | Techteam, Inc. | Missile launcher assembly |
-
2018
- 2018-10-10 DE DE102018008008.1A patent/DE102018008008A1/en not_active Ceased
-
2019
- 2019-09-24 EP EP19199162.9A patent/EP3637035B1/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| DE102018008008A1 (en) | 2020-04-16 |
| EP3637035A1 (en) | 2020-04-15 |
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