EP3093609A1 - Starting system for a guided missile and guided missile for such a starting system - Google Patents

Abstract

The present invention relates to a missile launch system (1) comprising a launch tube (2) having a missile space (3) for receiving a missile (4) and a cartridge space (5) for receiving a maneuver cartridge (6), and one to the launch tube (2) Anmontierbares and of the starting pipe (2) separable handle (7) with a striker system (8) for igniting the maneuver cartridge (6).

Description

The present invention relates to a guided missile launch system. Furthermore, the invention relates to a guided missile for use in such a missile launch system. The guided missile launch system is particularly shoulder-based and thus portable for a single user.

Starting pipes for guided missiles are known from the prior art, which a user can use shoulder-supported. There is a risk that an accidental ignition takes place or locking the missile within the launch tube is unintentionally solved. In both cases, there is an unwanted escape of the missile from the launch tube, which represents a high risk, at least for the user. In addition, in such starting systems increased effort in terms of storage and transport.

It is therefore an object of the invention to provide a guided missile launch system that allows for easy and cost-effective production and assembly safe handling of the missile.

The object is achieved by the features of the independent claim. Thus, the object is achieved by a missile launch system comprising a launch tube and a handle. The launch tube has a steering missile space, which is designed to receive a missile. Furthermore, the starting pipe has a cartridge chamber, which is designed to receive a maneuvering cartridge. In particular, it is provided that both the guided missile space and the cartridge space have a connection to an environment of the launch tube. In particular, it is provided that the guided missile space and the cartridge space are completely separated from each other. Ignition of the maneuver cartridge thus does not lead to an ignition of the missile. At the launch tube, the handle is anmontierbar, wherein the handle is also separable from the launch tube at any time. The handle has a striker system for igniting the maneuver cartridge. Thus, it can be seen that the guided missile launch system has increased safety in handling. If the starting pipe is separated from the handle, an accidental ignition of the maneuver cartridge is not possible because the associated firing pin system is present in the separate handle.

The dependent claims have preferred developments of the invention to the content.

Advantageously, the starting pipe has an opening in which a firing pin element is arranged. In this case, the firing pin protrudes into the missile space. The opening of the launch tube thus connects the steering missile space with an environment of the launch tube. By inserting the firing pin element advantageously the opening is completely closed. The engagement of the firing pin element in the steering missile space makes it possible to engage the firing pin element in an ignition opening of the guided missile. Since the firing pin element thus engages both in the opening of the launch tube and in the ignition opening of the missile, an axial centering of the opening of the launch tube and the ignition opening of the missile takes place. The missile thus has a predefined orientation within the launch tube.

Particularly advantageously, the firing pin member has a collar over which the firing pin member is fixed within the launch tube. In particular, a complete implementation of the firing pin element is thus prevented by the opening of the starting pipe. This prevents the risk of accidental ignition of the missile.

Furthermore, it is particularly advantageous that the collar is designed as a tear-off. If a sufficient force is applied to the firing pin element, the collar fails, as a result of which the firing pin element can be completely transferred from the opening of the launch tube into the firing opening of the guided missile. Within the firing opening of the guided missile, the firing pin element can finally initiate an ignition of the guided missile.

With the firing pin element of the guided missile is advantageously locked in the launch tube. Thus, a lock is given by the firing pin element. This lock is not unintentionally solvable, but can only be solved by a complete displacement of the firing pin element in the ignition opening of the missile. Thus, the lock is released by the firing pin element only when the missile is to be fired. Unintentional release is thus prevented.

Advantageously, the handle has a gas channel. Through the gas passage of the maneuver cartridge space is connected to the firing pin member when the handle is mounted on the launch tube. Should the maneuver cartridge be fired in the event that the handle is mounted on the launch tube, a gas pressure is created within the gas passage which exerts a resultant force on the striker element. In this case, it is advantageously provided that a displacement of the firing pin element takes place in the ignition opening of the guided missile, so that the firing pin element ignites the guided missile. Also, since the gas passage is disposed inside the grip, ignition of the maneuver cartridge in the case where the grip is not mounted on the launch tube does not result in displacement of the striker member because the gas passage is absent. In this case, only the gas pressure from the maneuver cartridge would be delivered to an environment of the missile launch system. It can be seen that thus the reliability and safety in handling the missile launch system are significantly increased.

Alternatively, the guided missile launch system has an additional element. In the additional element, a gas channel is attached. Through the gas passage of the maneuver cartridge space is connected to the firing pin member when the handle is mounted on the launch tube and the additional element is inserted into the handle or in the launch tube. The additional element is particularly advantageous movably mounted on the handle and in particular swung out of the handle or swiveled into the handle. Thus, the reliability and safety in handling the missile launch system is further increased, since in the absence of the additional element also mounted on the launch tube handle can not lead to an ignition of the maneuver cartridge.

Operational safety is therefore increased in two stages. If the handle is separated from the starting pipe, it is not possible to ignite the maneuver cartridge due to the lack of firing pin system. Nevertheless, if the maneuver cartridge ignited inadvertently, so there is no connection to the missile space, so that the ignition of the maneuver cartridge has no effect on the missile itself. Only with a combination of handle and launch tube ignition of the maneuver cartridge is possible.

The launch tube preferably has an additional locking element. With the additional locking element of the missile is lockable in the launch tube of the missile launch system. Thus, a further manual locking is provided, whereby the missile is held securely and reliably within the missile space.

In the cartridge chamber advantageously a maneuver cartridge is permanently installed. In this way, the maneuver cartridge is not removable by a user. This ensures that the maneuver cartridge is always present, so that a lack of operational capability of the missile launch system is excluded due to a missing maneuver cartridge. Also, an unintentional ignition of the maneuver cartridge is difficult within the launch tube, so there is no risk that the maneuver cartridge is ignited accidentally.

The invention further relates to a guided missile for use in a guided missile launch system as previously described. The guided missile has an ignition opening. In the ignition opening a firing pin element of the guided missile launch system is insertable. In this way, the missile is fixable in a launch tube of the missile launch system. The firing pin element therefore advantageously has the task of keeping the guided missile within the launch tube of the guided missile launch system in a predefined orientation and simultaneously locking it. The lock can only be released when the firing pin element is fully inserted into the ignition opening, whereby the missile is ignited.

In a preferred embodiment, the ignition opening leads to a thermal battery of the missile. Particularly advantageously, the ignition opening leads to a primer of the thermal battery. In this way it is possible that with the firing pin element on the primer of the thermal battery is beatable. Once the firing pin element strikes the primer cap, the thermal battery is ignited, energizing the missile. This leads to a start of the missile from the guided missile launch system.

Fig. 1

eine schematische Abbildung eines Lenkflugkörper-Startsystems gemäß einem Ausführungsbeispiel der Erfindung mit getrenntem Startrohr und Griffstück,

Fig. 2

eine schematische Abbildung des Lenkflugkörper-Startsystems gemäß dem Ausführungsbeispiel der Erfindung mit montiertem Griffstück und Startrohr,

Fig. 3

eine schematische Abbildung eines Details des Lenkflugkörper-Startsystems gemäß dem Ausführungsbeispiel der Erfindung,

Fig. 4

eine erste schematische Detailansicht des Lenkflugkörper-Startsystems gemäß dem Ausführungsbeispiel der Erfindung während eines Zündvorgangs des Lenkflugkörpers, und

Fig. 5

eine zweite schematische Detailansicht des Lenkflugkörper-Startsystems gemäß dem Ausführungsbeispiel der Erfindung während einer Zündung des Lenkflugkörpers.

The invention will now be described in detail by means of an embodiment with reference to the accompanying drawings. In the drawings:

Fig. 1

1 is a schematic illustration of a guided missile launch system according to an embodiment of the invention with a separate launch tube and handle;

Fig. 2

a schematic illustration of the guided missile launch system according to the embodiment of the invention with mounted handle and launch tube,

Fig. 3

FIG. 2 a schematic illustration of a detail of the guided missile launch system according to the exemplary embodiment of the invention, FIG.

Fig. 4

a first schematic detail view of the guided missile launch system according to the embodiment of the invention during an ignition of the missile, and

Fig. 5

a second schematic detail view of the guided missile launch system according to the embodiment of the invention during ignition of the missile.

FIG. 1 schematically shows a guided missile launch system 1 according to an embodiment of the invention. The guided missile launch system 1 comprises a launch tube 2 and a handle 7. In FIG. 1 the handle 7 is separated from the starting pipe 2. FIG. 2 shows the guided missile launch system 1 from FIG. 1 , wherein the handle 7 is mounted on the starting pipe 2.

The guided missile launch system 1 is particularly suitable for launching shoulder-mounted missiles 4. The launch tube 2 serves as a logistic package for the guided missile and to launch the missile. 4

The handle 7 is in particular connected only to launch the missile 4 with the launch tube 2 and is used to handle the missile launch system 1, the securing of the missile 4 and the initiation of the ignition process. The guided missile 4 is mounted in the launch tube 2 and locked and secured by two independent locking mechanisms. In this case, a first locking mechanism is present such that the guided missile 4 is manually locked to the launch tube. This is known from the prior art and therefore in not shown in the figures. A second locking mechanism consists in a firing pin element 9, which is arranged both within an opening of the starting pipe 2 and within an ignition opening 10 of the guided missile 4. The ignition opening 10 serves as an interface of the missile for initiating and thus for firing the missile. 4

The initiation of the guided missile 4 takes place by the targeted application of a arranged in a thermal battery 13 of the missile 4 Anzündhütchens 15 by the firing pin element 9. For this purpose, the firing pin member 9 must be accelerated to pitch on the primer 15. This is initiated by a maneuver cartridge 6.

The maneuvering cartridge 6 is arranged within a cartridge chamber 5 of the starting pipe 2. The cartridge chamber 5 is separated from the guided missile space 3. In this case, the cartridge chamber 5 has an opening, so that the cartridge chamber 5 is opened to an environment of the starting pipe 2 out. The maneuvering cartridge 6 is advantageously arranged fixedly within the cartridge chamber 5, so that removal of the maneuvering cartridge 6 by a user of the guided missile launching system 1 is not possible.

Only by inserting the handle 7 in the launch tube 2 of the maneuver cartridge chamber 5 is connected to the firing pin member 9. For this purpose, the handle 7 has a gas channel 12. The gas channel 12 connects the cartridge chamber 5 with the missile space 3 only when the handle is mounted on the launch tube 2. If the handle 7 is mounted on the starting pipe 2, then the maneuvering cartridge 6 can be ignited in order to generate an overpressure within the gas channel 12. This overpressure within the gas channel 12 finally leads to an acceleration of the firing pin element 9.

To initiate the maneuver cartridge 6, a conventional striker system 8 is present. Such a striker system 8 may for example be installed in handguns. The firing pin element 8 is completely integrated within the grip piece 7, so that the firing pin system 8 can be separated from the launch tube 2 together with the grip piece 7. In this way, the product safety is substantially increased, since an unintentional ignition of the maneuver cartridge 6 is prevented. Only by mounting the handle 7 on the Starting pipe 2, the firing pin system 8 is aligned axially to the maneuver cartridge 6 to allow ignition of the maneuver cartridge 6. At the same time established by the insertion of the handle 7 of the gas channel 12 between the cartridge chamber 5 and firing pin member 9 so that an ignition of the maneuver cartridge 6 leads to an acceleration of the firing pin member 9.

In FIG. 3 a detail view of the guided missile launch system 1 is shown. In FIG. 3 the guided missile launch system 1 is shown such that the grip 7 is mounted on the launch tube 2.

It can be seen that the firing pin element 9 engages in the ignition opening 10 of the guided missile 4. This ignition opening 10 is aligned axially with an opening within the starting pipe 2, so that the firing pin element 9 is inserted in alignment both in the opening of the starting pipe 2 and in the ignition opening 10 of the guided missile 4.

In order to prevent the firing pin element 9 from being displaced unintentionally out of its position, the firing pin element 9 has a collar 11 which rests against the launch tube 2 outside the guided-body space 3. About a locking ring 14 of the collar 11 is fixed. Thus, a movement of the firing pin member 9 is prevented. The firing pin member 9 therefore serves as a Verrieglung for the missile 4, since the at least partially engaging the firing pin member 9 in the ignition opening 10 prevents displacement of the missile 4 within the missile space 3 of the launch tube 2. This locking can be achieved only by igniting the maneuver cartridge 6, since this ignition leads to a displacement of the firing pin member 9, whereby the firing pin member 9 is disposed completely within the ignition opening 10.

The collar 11 is formed as a tear-off. If the gas pressure inside the gas channel 12 is increased by igniting the maneuver cartridge 6, this leads to a tearing off of the collar 11, as a result of which the firing pin element 9 becomes displaceable. Due to the pressure within the gas channel 12, therefore, an acceleration of the firing pin element 9 takes place in the ignition opening 10 of the guided missile 4 into it. This case is in FIG. 4 shown.

In FIG. 4 the firing pin system 8 was triggered, whereby the maneuver cartridge 6 was ignited. This is analogous to the firing of a handgun instead. By igniting the maneuver cartridge 6, an overpressure within the gas channel 12 is generated. This overpressure acts on the firing pin element 9. As soon as the overpressure reaches a predefined pressure, the collar 11 of the firing pin element 9 fails FIG. 5 shown.

In FIG. 5 the collar 11 of the firing pin element 9 has failed, so that the firing pin element 9 is accelerated by the gas pressure within the gas channel 12. As a result of the acceleration of the firing pin element 9, this is pushed completely into the ignition opening 10 of the guided missile 4. Thus, on the one hand, the lock between launch tube 2 and guided missile 4, which was established by the firing pin member 9, solved, on the other hand proposes the firing pin member 9 on the primer 15 of the thermal battery 13 of the guided missile 4. In this way, the thermal battery 13 is activated, whereby the guided missile 4 is supplied with electrical energy. This leads to a start-up of the electronics of the missile, whereby the functions of the missile are started. This leads advantageously to a launch of the missile from the launch tube. 2

1. A) Systeminitiierung unter Verwendung eines Gasgenerators in Form einer Manöverpatrone, welche sich aufgrund ihrer Bauform zum einen durch eine voll integrierte Anzündkette und zum anderen durch eine hohe Robustheit gegenüber Umweltwirkungen auszeichnet.
2. B) Systemische Trennung von primären Initiator und Energieträger beziehungsweise Anzündkette, bei gleichzeitiger Unterbrechung des Gaskanals durch segmentalen Aufbau, wobei ein Gaskanalsegment im Griffstück verbleibt und den Gaskanal derart öffnet, dass in getrennter Konfiguration keine Verdämmung und somit kein Gasdruckanstieg im Gaskanalsystem ermöglicht ist. Dies trägt wesentlich zur Robustifizierung des Systems und einer Maximierung der Produktsicherheit bei. Im vorliegenden Fall ist der primäre Initiator vorteilhafterweise eine Schlagbolzenkinematik im Griffstück, während der Energieträger beziehungsweise die Anzündkette die Manöverpatronen darstellt.
3. C) Integration eines Bolzenelements mit Doppelfunktion, welches formschlüssig im Gesamtsystem verbaut ist und den Lenkflugkörper axial wie auch radial im Abschussrohr verriegelt und nach Initiierung des Gesamtsystems seine Funktion und Form gemäß seiner zweiten Bestimmung als Schlagbolzenelement verändert, indem bei Erreichen eines am Boden des Schlagbolzenelements anstehenden Mindestgasdrucks ein geometrischer Absatz oder Ansatz, insbesondere ein Kragen, vom Schlagbolzenelement abreißt, sodass der Formschluss aufgehoben wird und der Bolzen zwecks Initiierung in Richtung einer internen Anzündkette des Lenkflugkörpers beschleunigt wird, sodass im Zuge der Beschleunigung auch die Verriegelung des Lenkflugkörpers im Gesamtsystem gelöst wird.

The invention further has the following advantages:

1. A) system initiation using a gas generator in the form of a maneuver cartridge, which is characterized by its design on the one hand by a fully integrated ignition chain and on the other by a high robustness to environmental effects.
2. B) Systemic separation of primary initiator and energy carrier or ignition chain, with simultaneous interruption of the gas channel by segmental structure, wherein a gas channel segment remains in the handle and the gas channel opens so that in a separate configuration no entrainment and thus no increase in gas pressure in the gas channel system is possible. This contributes significantly to the robustness of the system and maximization of product safety. In the present case, the primary initiator is advantageously a firing pin kinematics in the handle, while the energy carrier or the ignition chain represents the maneuver cartridges.
3. C) Integration of a double-action pin element, which is positively installed in the overall system and locks the missile axially as well as radially in the launch tube and changed its function and shape according to its second determination as a firing pin element after initiation of the overall system by pending on reaching the bottom of the firing pin element Minimum gas pressure a geometric paragraph or approach, in particular a collar, tearing off the firing pin element, so that the pin is accelerated for initiation in the direction of an internal ignition chain of the missile, so that in the course of acceleration and the locking of the missile is solved in the overall system.

In addition to the above written description of the invention is to the additional disclosure hereby explicitly to the drawings of the invention in the Fig. 1 to 5 Referenced.

LIST OF REFERENCE NUMBERS

1. 1 guided missile launch system
2. 2 launch tube
3. 3 guided missile space
4. 4 guided missiles
5. 5 cartridge space
6. 6 maneuver cartridge
7. 7 grip piece
8. 8 striker system
9. 9 firing pin element
10. 10 ignition opening
11. 11 collar
12. 12 gas channel
13. 13 thermal battery
14. 14 circlip

Claims (11)

Guided missile launch system (1) comprising a take-off tube (2) with a missile space (3) for receiving a missile (4) and with a cartridge space (5) for receiving a maneuver cartridge (6), and one to the launch tube (2) and from the starting pipe (2) separable handle (7) with a striker system (8) for igniting the maneuver cartridge (6). Guided missile launch system (1) according to claim 1, characterized in that the starting tube (2) has an opening in which a firing pin element (9) is arranged, wherein the firing pin member (9) in the steering missile space (3) protrudes, so that with the Impact bolt element (9) in an ignition opening (10) of the missile (4) is engageable. Guided missile launch system (1) according to claim 2, characterized in that the firing pin element (9) has a collar (11) via which the firing pin element (9) can be fixed in the starting pipe (2). Guided missile launch system (1) according to claim 3, characterized in that the collar (11) is designed as a tear-off element. Guided missile launch system (1) according to any one of claims 2 to 4, characterized in that with the firing pin element (9) of the guided missile (4) in the launch tube (2) can be locked. Missile launch system (1) according to one of claims 2 to 5, characterized in that the handle (7) has a gas channel (12) which connects the maneuver cartridge chamber (5) with the firing pin member (9) when the handle (7) is mounted on the starting pipe (2). Guided missile starting system (1) according to one of claims 2 to 5, characterized by an additional element, wherein the additional element has a gas channel (12) which connects the maneuver cartridge chamber (5) with the firing pin element (9) when the handle (7) the starting pipe (2) is mounted and the additional element is inserted into the starting pipe (2) or the grip (7). Guided missile launch system (1) according to any one of the preceding claims, characterized in that the starting tube 2 has a locking element, with which the guided missile (4) in the steering missile space (3) can be locked. Guided missile launch system (1) according to any one of the preceding claims, characterized in that in the cartridge chamber (5) a maneuver cartridge (6) is permanently installed, so that the maneuver cartridge (6) can not be removed by a user. Guided missile (4) for use in a guided missile launching system (1) according to any one of the preceding claims, characterized in that the guided missile (4) has an ignition opening (10) into which a firing pin element (9) of the guided missile launch system (1) is insertable to fix the guided missile (4) in a launch tube (2) of the guided missile launch system (1). Guided missile (4) according to claim 10, characterized in that the ignition openings (10) leads to a thermal battery (13) of the guided missile (4), so that the firing pin element (9) on a primer cap (15) of the thermal battery (13) is beatable.

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