EP2281169B1 - Weapon system with caseless munition - Google Patents

Abstract

A weapon system uses caseless munitions. In order to permit a further use of the weapon system essentially without delay on jamming, a configuration of the weapon system is disclosed that has a weapon barrel, a projectile magazine with individual chambers and a propellant charge magazine with individual chambers. In order to guarantee a firing position, the projectile magazine and the propellant charge magazine, may be moved relative to the weapon barrel. The projectile magazine has a chamber located in a discharge position in which an ejector device for the projectile in the chamber may be activated. A further chamber of the projectile magazine may be loaded in the movement position for the projectile magazine and the propellant charge magazine has a chamber, located in a discharge position in which an ejector device for the propellant charge in the chamber may be activated. The further chamber of the propellant charge magazine may be loaded in the movement position of the propellant charge magazine.

Description

The invention relates to a weapon system with caseless ammunition according to the preamble of claim 1, as in GB 1248784 A described.

A similar system is from the EP 1 731 867 B1 known. The projectile and the propellant charge are in this case assigned to a respective independent projectile bearing or propellant charge bearings, which are aligned in firing position coaxial with the axis of the barrel of the weapon barrel.

From the DE PS 15 78 101 It is known to move the projectile bearing and propellant charges transversely to the gun barrel in opposite directions to each other, to twist or to pivot, to allow increased firing order and to keep the heat absorption of the barrel as low as possible. Unlike a classic sleeve ammunition, in which the projectile is firmly connected to the sleeve containing the propellant charge, in case of a failure of the propellant charge, no automatic ejection of the propellant charge and of the projectile is possible. Weapon systems with caseless ammunition were therefore previously disadvantaged in stoppages, insofar as it has come to this conditional use interruptions.

An object of the present invention is to further develop the weapon system according to the preamble of claim 1 such that even with stoppages further use of the weapon system without significant temporal impairment can be achieved, and that the security of the weapon system is guaranteed even after prolonged firing.

This object is achieved by a weapon system according to claim 1.

Preferably, the ejection device for the propellant charge bearing and preferably also for the projectile storage at each unloading position, d. H. with progressive clocking, automatically d. H. automatically activated.

In a simple way, the invention can be realized in that the projectile bearing and the propellant charge bearings are each rotatable about separate diametrically opposite to the axis of the axis A of the weapon barrel axes X and Y respectively.

Preferably, the axes X, Y and the axis of the axis A lie on a common plane, which extends in the weft direction.

In an advantageous manner, the idea according to the invention has at least two chambers each. Accordingly, the propellant charge bearing expediently has at least two chambers and the projectile storage at least two chambers. For weapons with a smaller caliber, such as a 20 mm cannon, a version with only two chambers in terms of dimensions and technical realization is particularly advantageous.

The timing of the system depends on the number of chambers. In a two-chamber system, each bar corresponds to a 1/4 turn. The firing position is taken after every second clock.

The unloading of the propellant charge bearing, so the removal of a possibly present propellant charge failure and the loading of the projectile bearing is preferably carried out in opposite directions. Here, the two bearings rotate in opposite directions. This is favorable for targeted heat removal measures. But also a synchronous movement is possible.

Appropriately, the projectile is ejected opposite to the firing direction to the loading side. The resistance of projectile-related attacks or leadership bands must therefore not be overcome when ejecting.

In contrast, the propellant failure is preferably ejected in the weft direction, whereby the back side, d. H. rear seal is not damaged.

The activation of the ejection devices can expediently, depending on the rotational movement of the projectile bearing and propellant charge bearing, for example via suitable synchronization gear or other control means, such. B. scenes or the like, are controlled.

Furthermore, it is expediently provided that a projectile to be unloaded can be returned to a loading space for the projectiles during the respective unloading process of the projectile warehouse and, if appropriate, can be thrown out of the loading space therefrom by a suitable device.

The ejection device for the projectile and the ejection device for the propellant are expediently respectively correspondingly positioned and axially movable Auswerfdorne. Such Auswerfdorne can be coupled via suitable synchronization means or synchronization gear or the like with the rotational movement of the projectile bearing and propellant charge charger. They therefore represent a structurally simple solution variant.

Preferably, the projectile bearing is rotatably mounted about an associated axis. Furthermore, the propellant charge bearing is preferably also an associated axis rotatably mounted. Preferably, the two axes about which the projectile bearing and the propellant charge bearing are each mounted rotatably, in each case offset parallel to the axis of the weapon barrel. As a result of this rotatable mounting of the projectile bearing and of the propellant charge bearing, there are inertial advantages, in particular with regard to the alternative of a linear displaceability of the projectile bearing and of the propellant charge bearing. With a rotatable bearing, the weapon system need not work against the moment of inertia of the projectile bearing and the propellant charge bearing once the bearings are rotated. This advantage is not given in linear reciprocating pushability of the projectile bearing and the propellant charge bearing.

According to the invention, externally driven synchronization means are provided with which the respective ejection device can be actuated, depending on the rotational movement and / or the angular position of the projectile bearing and / or the propellant charge bearing. In foreign weapon systems, one understands the property that mechanical processes in the weapon system take place independently of the forces resulting from the firing of a shot. The opposite form so-called self-propelled weapon systems in which the forces resulting from the shot are used, for example, for the loading of the next cartridge. Classic self-propelled weapon systems are z. B. pressure loader or recoil loader. As a result of the external drive of the ejection device, in particular of the propellant charge bearing, the ejection of the propellant charge possibly remaining in the chamber from the chamber takes place automatically after releasing the trigger, without any forces of a firing process being necessary for this ejection process. This is particularly advantageous if the last charged propellant, which is still beaten just before releasing the trigger, failed and can not be discharged by the now lacking firing forces. The externally driven synchronization means operate in this case in any case nor the ejector of the propellant charge bearing. Preferably, the externally driven synchronization means also ensure that after this conclusion of the last cycle no new cycle is started, so that no new propellant and no new projectile is inserted into one of the chambers of the propellant charge bearing and the projectile warehouse more.

In accordance with a particularly preferred embodiment of the weapon system according to the invention, the ejection devices can be actuated in a time-shifted manner with respect to the insertion devices such that penetration of the ejection devices into the insertion devices Chambers only with a time delay for insertion of the insertion devices after rotation of the projectile bearing and / or the propellant charge bearing from the loading position by 360 ° / n, ie the n-th part of 360 °, takes place in the unloading position, where n is the number of chambers of the projectile warehouse and / or the number of chambers of the propellant charge bearing is. This time-shifted operability of the ejection devices is preferably realized in that the ejection devices and the insertion devices are coupled to each other such that movement of the insertion devices on the projectile bearing and the propellant charge bearing is associated with a preferably equal amount of movement of the ejection devices away from the projectile bearing and the propellant charge bearing. Accordingly, a movement of the insertion devices away from the projectile bearing and the propellant charge bearing is preferably associated with a preferably equal amount of movement of the ejection devices to the projectile warehouse and the propellant charge storage. In this case, the projectile bearing and the propellant charge bearing are preferably arranged between the insertion devices and the ejection devices. This can be ensured in an advantageous manner that the ejection / ejection of Zündversagern can take place in the opposite direction to the insertion direction.

This time-shifted actuation of the ejection devices can be controlled by the synchronization means described above. The advantage of the time delay of the operation of the ejection devices and the coupling of the ejection devices and the insertion devices lies in the simple and trouble-free controllability of the loading and unloading process. Furthermore, the weapon system designed in this way is characterized by a very smooth running.

In general, the use of as many chambers in the propellant storage is advantageous because the energy input (at the same cadence, ie at the same firing frequency per unit time) in the propellant bearing is the lower, the more chambers are provided. The disadvantage, however, that the residence time of the respective propellant charges in their chambers is the longer, the more chambers are provided when using many propellant charge chambers. The long residence time of the propellant charges in the propellant charge storage increases the risk of auto-ignition (cook-off). The invention thus faces the problem of two opposing tendencies, on the one hand to provide as many propellant charge chambers to heat the propellant charge bearing as little as possible, on the other hand to provide as few propellant charge chambers to the residence time of the individual propellant charges in their chambers keep as low as possible. In the context of the present invention, following detailed studies of theoretical and experimental nature, it has been found that the optimum number n of the chambers of the propellant charge storage is equal to 2 (n = 2). For this case (n = 2) thus results in a time-delayed penetration of the ejection devices in the chambers after rotation of the projectile bearing and / or the propellant charge bearing from the loading position by 180 ° in the unloading position. Another advantage of the realization of the weapon system according to the invention with only 2 propellant charge chambers and only 2 projectile chambers is that in this configuration, the advantageous opposite rotation of the projectile bearing and the propellant charge bearing can be realized more easily, since a rotation from the loading position by 180 ° clockwise at both Projectile bearing as well as propellant storage at the same discharge position and the same position of the projectile chambers and the propellant charge chambers to each other as a rotation from the loading position by 180 ° counterclockwise. For this reason, if the number n of chambers is greater than 2, it is more advantageous if the projectile bearings and the propellant bearings rotate in the same direction. But even in the case of n = 2, the same direction rotating projectile warehouse and propellant storage is conceivable.

An expedient embodiment of the present invention will be explained in more detail with reference to drawing figures.

Fig. 1

eine stark vereinfachte schematische Darstellungsweise des Ladevorgangs einer zweckmäßigen Ausgestaltung der Erfindung in Teilschnittdarstellung von vorne (Fig. 1 A), entlang der Schnittlinie B-B von Fig. 1A (Fig. 1B) sowie entlang der Schnittlinie C-D von Fig. 1B (Fig. 1C),

Fig. 2

eine stark vereinfachte schematische Darstellungsweise des Entladevorgangs der obigen Ausgestaltung der Erfindung in Teilschnittdarstellung von vorne (Fig. 2A), entlang der Schnittlinie B-B in Fig. 2A (Fig. 2B) sowie entlang der Schnittlinie C-D in Fig. 2B (Fig. 2C),

Fig. 3

eine stark vereinfachte schematische Darstellungsweise der Schussposition,

Figs. 4A - 4L

mehrere zeitlich aufeinanderfolgende Momentaufnahmen einer bevorzugten Ausführungsform des erfindungsgemäßen Waffensystems zur Darstellung des Funktionsablaufs während eines ungestörten Zyklus (ohne Zündversager), und

Figs. 5A - 5L

mehrere zeitlich aufeinanderfolgende Momentaufnahmen der bevorzugten Ausführungsform des erfindungsgemäßen Waffensystems zur Darstellung des Funktionsablaufs während eines gestörten Zyklus (mit Zündversager).

In the drawings, the same or similar reference numerals designate the same or similar parts. Show it:

Fig. 1

a greatly simplified schematic representation of the charging process of an expedient embodiment of the invention in a partial sectional view from the front ( Fig. 1 A) , along the section line BB of Fig. 1A (Fig. 1B ) as well as along the section line CD of Fig. 1B (Fig. 1C )

Fig. 2

a greatly simplified schematic representation of the unloading process of the above embodiment of the invention in partial sectional view from the front ( Fig. 2A ), along the section line BB in Fig. 2A (Fig. 2B ) as well as along the section line CD in Fig. 2B (Fig. 2C )

Fig. 3

a simplified schematic representation of the firing position,

Figs. 4A - 4L

a plurality of temporally successive snapshots of a preferred embodiment of the weapon system according to the invention for the representation of the functional sequence during an undisturbed cycle (without ignition failure), and

Figs. 5A - 5L

a plurality of successive snapshots of the preferred embodiment of the weapon system according to the invention for illustrating the functional sequence during a faulty cycle (with Zündversager).

The reference numeral 1 denotes a weapon barrel z. B. for a 20 mm rapid-fire cannon of a preferably automatically operated weapon system with caseless ammunition and high firing order, for example, for use in a tank, helicopter or the like. The weapon system includes a total of two chambers 3, 30 comprehensive projectile 2 for receiving located in a storage or loading space 11 projectiles 6. A punch 8 is used to exactly positioned in the insertion position projectile 6, for example, as in Fig. 1B shown to spend in the chamber 30 of the projectile carrier 2. In the loading space 11 is a plurality of stockpiled projectiles, by means of a (not shown) feeding into the insertion position for the subsequent chamber, z. B. 3, can be brought. The chamber 3 is located in the in Fig. 2 shown timing in unloading position.

The weapon system also includes an independent propellant charge bearing 4 with also two chambers 5, 50, in each of which a propellant charge 7 can be introduced. Like from the Fig. 1B it can be seen, the loading of the propellant charge bearing 4 is ensured via a located on the weft direction side punch 9. The stored in the loading space 12, stored propellant charges 7 are successively placed in the insertion position and the respective chamber (in Fig. 1B the chamber 50) of the propellant charge bearing 4 is supplied.

Both the propellant charge bearing 4 and the projectile bearing 2 are designed as a pivot bearing and are moved in opposite directions, for example. According to Fig. 1A be the propellant bearing 4 about the axis of rotation Y counterclockwise and the Projectile bearing 2 is moved around the rotation axis X in a clockwise direction. How out Fig. 1A it can be seen, in the rotational position (timing) shown therein, the chamber 5 is being filled with a propellant charge 7, while the chamber 30 of the projectile bearing 2 is filled with the projectile 6.

In the middle, the position of the weapon barrel 1. In this rotational position, there is neither a chamber of the projectile bearing 2 nor a chamber of the propellant charge bearing 4 in alignment with the axis of the soul A of the weapon barrel. 1

Fig. 1C shows the arrangement of each not in firing position chambers, namely the chambers 3, 30 of the projectile bearing 2 and the chambers 5, 50 of the propellant charge bearing 4 relative to the gun barrel. 1

The rotational movement of the projectile bearing 2 and propellant charge bearing 4 takes place in a 1/4 turn. Like in the Fig. 2 is shown in the same rotational position via a first Auswerfdorn 13 which possibly ejected by Zündhemmung in the chamber 3 projectile 6 is ejected preferably opposite to the firing direction, preferably from the projectile warehouse 2 in the loading space 11 back where it by a (not shown) device is singled out.

At the same time the possibly defective propellant charge 7 is ejected by the second Auswerfdorn 10 preferably in the weft direction from the chamber 50 of the propellant charge bearing 4, preferably in the loading space 12, where it is separated by a (also not shown) device.

Loading according to Fig. 1 and unloading according to Fig. 2 occurs after every other clock cycle, such that the Auswerfdorne 10, 13 enter into the respective chambers regardless of whether in the chamber in question a projectile 6 and a propellant charge 7 is or not.

After loading or unloading according to Fig. 1 or 2, the projectile bearing 2 and propellant bearing 4 rotates by a 1/4 turn further in the Fig. 3 shown position (shooting position), in which the previously loaded chambers 30 and 50 are in alignment with the axis of the soul A of the gun barrel 1.

In this firing position or firing position, the previously loaded chambers 30 and 50 are thus coaxial to the axis of the barrel 1, or in other words, the chambers 30 and 50 are in alignment with the weapon barrel 1.

The control of Auswerfdorne 10, 13 can be effected by synchronization means 15 and / or coupling means 14 which actuate the Auswerfdorne 10 and 13 depending on the rotational movement and / or the angular position.

The FIGS. 4A to 4L show first several temporally successive snapshots of a preferred embodiment of the weapon system according to the invention for the representation of the functional sequence during an undisturbed cycle (without failure of a propellant charge). Figures 5A to 5L then show several temporally consecutive snapshots of already in FIG. 4 illustrated preferred embodiment of the weapon system according to the invention. The FIG. 5 serves to display the functional sequence during a faulty cycle (with ignition failure of a propellant charge).

The in the FIGS. 4 and 5 Each functional sequence shown represents a complete cycle, which includes the three positions "loading position", "shot position" and "unloading position". The operation of the weapons system according to the invention thus detects any sequence of cycles FIG. 4 and / or 5.

Just like in the FIGS. 1 to 3 the reference numeral 1 denotes a weapon barrel of a weapon system, which is preferably automatically operated, with caseless ammunition and high firing order. The weapon system includes a preferably two chambers 3, 30 projectile projectile 2 for receiving located in a storage or loading space 11 projectiles 6. An insertion device 8 is used to move the positioned in the insertion position projectile 6 in the chamber 3 of the projectile bearing 2 (see FIGS. 4A to 4C such as FIGS. 5A to 5C ). In the loading space 11 is a plurality of stockpiled projectiles 6, by means of a (not shown) feeding into the insertion position for the next chamber, z. B. 30, can be brought.

The weapon system also includes a propellant charge bearing 4 with a number of chambers 5, 50, in each of which a propellant charge 7 can be introduced. Preferably, the number of chambers 5, 50 of the propellant charge bearing 4 coincides with the number of chambers 3, 30 of the projectile bearing 2. In the present example the FIGS. 4 and 5 is Accordingly, the number of chambers 5, 50 of the propellant charge bearing 4 equal 2. The loading of the propellant charge bearing 4 is ensured by a slide-9. The stored in the loading space 12, stored propellant charges 7 are successively placed in the insertion position and the respective chamber (in FIGS. 4A to 4C or in FIGS. 5A to 5C : the chamber 5) of the propellant charge bearing 4 is supplied. Both the propellant charge bearing 4 and the projectile bearing 2 are designed as a pivot bearing, which preferably rotate in opposite directions. By the opposite rotation of propellant bearing 4 and projectile bearing 2 a high degree of smoothness of the weapon system can be achieved. The reason for the increased smoothness is the mutual compensation of any imbalance of the propellant charge bearing 4 and the projectile bearing 2 and the mutual compensation of bearing forces, which act on the rotary bearings of the propellant charge bearing 4 and the projectile bearing 2. Again FIG. 4A can be seen, the propellant charge bearing 4 is rotatably mounted about the rotation axis Y and the projectile bearing 2 is rotatably mounted about the rotation axis X. The two axes X, Y are each arranged offset parallel to the axis of the axis A of the weapon barrel 1. The propellant charge bearing 4 and the projectile bearing 2 are disposed between the rear end of the weapon barrel 1 and the striker 77. The firing pin device 77 has a firing pin 777.

With reference to the FIGS. 4A to 4L Now the trouble-free operation of the preferred embodiment of the weapon system will be explained. In the FIGS. 4A to 4C a first phase of the cycle is shown, in which the chamber 3 of the projectile bearing 2 is in a first position, namely a loading position. In this first position, the insertion device 8 for inserting a projectile 6 in this chamber 3 can be activated. Further, in this first position, the chamber 5 of the propellant charge bearing 4 in the loading position, in which a slide-in device 9 for inserting a propellant charge 7 in this chamber 5 can be activated. The FIGS. 4A to 4C show these two insertion processes for the projectile 6 and the propellant charge 7. In this case, the insertion device 8 for inserting the projectile 6 into the chamber 3 and the insertion device 9 for inserting the propellant charge 7 in the chamber 5 may be coupled together. Through this - preferably rigid - coupling between the two insertion devices 8, 9 can be achieved in a simple manner, a synchronous insertion of the projectile 6 and the propellant 7.

The Figures 4D and 4E show the transition from the first position to a second position, the firing position, as in the Figures 4F and 4G is shown. In the firing position are the chamber 3 of the projectile bearing 2 and the chamber 5 of Propellant charge bearing 4 in alignment with the weapon barrel 1. The transition between the first position and the second position is achieved by the preferably opposite rotation of the projectile bearing 2 and the propellant charge bearing 4 about their respective axes of rotation X, Y. In the firing position, the end faces of the weapon barrel 1, the projectile bearing 2, the propellant charge bearing 4 and the firing pin device 77 preferably close tightly with one another in order to ensure the required pressure development upon ignition of the propellant charge 7. While in Figures 4D and 4E shown rotational phase, the insertion devices 8, 9 are preferably not moved or possibly from the maximum insertion position of the FIG. 4C a small piece withdrawn to ensure an undisturbed rotation of the projectile bearing 2 and the propellant charge bearing 4.

In FIG. 4G the firing pin device 77 is actuated in the firing position. In this case, the firing pin 777 strikes the in-chamber 5 propellant body 7, possibly also on a mounted on the propellant charge 7 Zündplättchen. The propellant 7 then explodes in the chamber 5 of the propellant charge bearing 4 and accelerates the projectile 6 located in the chamber 3, which is accelerated by the weapon barrel 1 in the direction of the target.

The Figures 4H to 4J show the transition from the second position to a third position, the unloading position, as in the Figures 4K and 4L is shown. The transition from the second position to the third position is again by rotation of the projectile bearing 2 and the propellant charge bearing 4 about the associated axis X and Y. In the unloading ejection devices 13, 10 can be activated in the form of Auswerfdornen, which in the shortly before Retract filled chambers 3 and 4. The ejection devices 13, 10 are preferably always activated in this third position, that is, even if in the firing position previously the firing was successful and the chambers 3, 5 have been emptied. This allows safe and trouble-free operation regardless of the success or failure of the previous shooting attempt. Preferably, the ejection devices 13, 10 are coupled together. This has the advantage that a synchronization of the ejection process in the projectile chamber 3 and the propellant charge chamber 5 can be achieved in a simple manner. Furthermore, in particular the retraction of the ejection device 10 into the propellant charge chamber 5 also has a benefit from a prior scheduled ignition of the propellant charge 7, namely a cleaning function of the propellant charge chamber 5. In particular by appropriate design of the end face of the ejection device 10 (eg with scrapers or scrapers) Brushes) namely burn-off residues of the ignited propellant charge 7 can be removed from the propellant charge bearing 5.

With reference to the Figures 5A to 5L Now the disturbed operation (with Zündversager) of the preferred embodiment of the weapon system will be explained. This functional sequence is in the FIGS. 5A to 5F identical to the trouble-free functional sequence, as he in the FIGS. 4A to 4F is shown. To avoid repetition, the explanations to FIGS. 4A to 4F for the explanation of FIGS. 5A to 5F fully referenced. Representing all other figures is in FIG. 5A nor the optional use of a synchronization means 15 shown, with which depending on the rotational movement and / or the angular position of the projectile bearing 2 and / or the propellant charge bearing 4, the respective ejector 10, 13 and / or the respective slide-in device 8, 9 can be actuated. The synchronization means 15 preferably acts on the rotary shafts of the projectile bearing 2 and the propellant charge bearing 4 and on the insertion devices 8, 9 and the ejection devices 10, 13. In the case of a coupling of the insertion devices 8 and 9, the synchronization means 15 also act on this coupling. In the case of a coupling of the ejection devices 10, 13, the synchronization means 15 can also act on this coupling. FIG. 5A also shows the possibility of coupling the insertion devices 8, 9 with the ejection devices 10, 13. This coupling 14 is preferably connected to the coupling between the insertion devices 8 and 9 and the coupling between the ejection devices 10 and 13. In the case of the use of such a coupling 14, the synchronization means 15 can also act directly on this coupling 14. The coupling 14 causes a movement of the insertion devices 8, 9 on the projectile bearing 2 and the propellant charge bearing 4 is connected to a preferably equal amount of movement of the ejection devices 10, 13 away from the projectile bearing 2 and the propellant charge bearing 4. Furthermore, the coupling 14 causes a movement of the insertion devices 8, 9 away from the projectile bearing 2 and the propellant charge bearing 4 with a preferably equal amount of movement of the ejection devices 10, 13 is connected to the projectile bearing 2 and the propellant charge bearing 4. The coupling 14 does not necessarily have to be rigid. A rigid coupling 14 is merely the simplest embodiment of such a coupling. Rather, the coupling 14 can also be realized via a more complex synchronized control operation for the insertion devices 8, 9 and the ejection devices 10, 13, which the insertion devices 8, 9 and ejection devices 10, 13 is impressed by the synchronization means 15. The Optionality of both the synchronization means 15 and the coupling 14 is expressed by the dashed representation of these components. Preferably, the synchronization means 15 is externally driven, which can be ensured in an advantageous manner that in each case a cycle started is completed and is terminated with the operation of the ejector 10 for the propellant charge bearing 5, 50, thus the timely output of a possibly still in the propellant charge chamber 5, 50 to ensure propellant charge 7.

In FIG. 5G will be like in FIG. 4G in the firing position, the firing pin device 77 is actuated. In this case, the firing pin 777 strikes the in-chamber 5 propellant body 7. In contrast to the trouble-free operation of FIG. 4G but explodes in Fig. 5G due to a failure ignition the propellant charge 7 not. Consequently, the projectile 6 remains in its chamber 3.

The Figures 5H to 5J show the transition from the second position to the third position, the unloading position, as in the Figures 5K and 5L is shown. The transition from the second position to the third position takes place by rotation of the projectile bearing 2 and the propellant charge bearing 4 about the associated axis X or Y. In the unloading position, the ejection devices 13, 10 are now routinely activated. Driving as in Figures 5K and 5L is shown, the Auswerfdorne 13, 10 in the filled with the Zündversagern 6, 7 chambers 3, 5 and push the remaining in the chamber 3 projectile 6 and remaining in the chamber 5 propellant 7 preferably opposite to the insertion direction of the respective chambers. 3 , 5 out.

At one in the sense of FIGS. 4 and 5 designed weapon system is advantageously ensured that each cycle, which begins with the loading of a chamber 3, 30 of the projectile bearing 2 and a chamber 5, 50 of the propellant charge bearing 4, always completely through to discharge, in particular the chamber 5, 50 of the propellant charge storage 4 is, regardless of when (especially in the case of an automatic weapon) the trigger is released and also regardless of whether in particular the last charged propellant charge 7 is a failure or not. This can ensure that a propellant charge 7, which is introduced at a certain time in a chamber 5, 50 of the propellant charge bearing 4 (and thus in the combustion chamber), dwells in each case only for a very short period of time in the combustion chamber. Either the charged propellant 7 intentionally ignited a short time later in the firing position, or in case of failure of the propellant charge 7, or in case of interruption of the firing order, ejected from its propellant charge chamber 5, 50. As a result, inadvertent ignition of a propellant charge 7 even with heated propellant charge bearing 4 can be prevented in all conceivable cases with high probability. As a result, the safety of the conventional weapon system according to the preamble of claim 1 is significantly improved.

Reference numerals and figures in the claims are for illustrative purposes only and are in no way to be construed as limiting the scope of protection as determined by the language of the claims.

LIST OF REFERENCE NUMBERS

1

barrel

2

projectile camp

3, 30

Chamber (projectile)

4

Propellant storage

5, 50

Chamber (propellant charge)

6

projectile

7

propellant

8th

Stamp; Insertion device (projectile)

9

Stamp; Insertion device (propellant charge)

10

Auswerfdorn; Ejection device (propellant charge)

11

Loading space (projectiles)

12

Loading space (propellant charges)

13

Auswerfdorn; Ejecting device (projectile)

13

coupling

14

synchronization means

77

Firing pin device

777

firing pin

X

Rotation axis (projectile warehouse)

Y

Rotation axis (propellant charge bearing)

A

Soul Axis (weapon barrel)

Claims (4)

1. Weapon system for caseless ammunition, comprising a weapon barrel (1),
   a projectile holder (2) which has individual chambers (3, 30), and
   a propellant charge holder (4) which has individual chambers (5, 50),
   wherein the projectile holder (2) and the propellant charge holder (4) can be moved relative to the weapon barrel (1) in order to ensure a firing position (Figures 4F, 4G, 5F, 5G and 3)in which one of the chambers (for example 3) in the projectile holder (2) and one of the chambers (for example 5) in the propellant charge holder (4) are located coaxially with respect to the bore axis of the weapon barrel (1), wherein the projectile holder (2) can be moved in one or more successive cycles, wherein each of the cycles comprises the following successive positions:

   a first position, in which one of the chambers (for example 3) of the projectile holder (2) is located in a loading position (Figures 4A, 4B, 4C, 5A, 5B, 5C and 1), in which an insertion device (8) can be activated in order to insert a projectile (6) into this chamber (3),

   a second position, in which this chamber (3) in the projectile holder (2) is located in the firing position (Figures 4F, 4G, 5F, 5G and 3), and

   a third position, in which this chamber (3) in the projectile holder (2) is located in an unloading position (Figures 4J, 4K, 4L, 5J, 5K, 5L and 2), in which an ejection device (13) can be activated in order to eject the projectile (6), which may still be located in this chamber (3), from this chamber (3);

   wherein the propellant charge holder (4) can be moved in one or more successive cycles, wherein each of the cycles comprises the following successive positions:

   a first position, in which one of the chambers (for example 5) in the propellant charge holder (4) is located in a loading position (Figures 4A, 4B, 4C, 5A, 5B, 5C and 1), in which an insertion device (9) can be activated in order to insert a propellant charge (7) into this chamber (5),

   a second position, in which this chamber (5) in the propellant charge holder (4) is located in the firing position (Figures 4F, 4G, 5F, 5G and 3), and

   a third position, in which this chamber (5) in the propellant charge holder (4) is located in an unloading position (Figures 4J, 4K, 4L, 5J, 5K, 5L and 2), in which an ejection device (10) can be activated in order to eject the propellant charge (7), which may still be located in this chamber (5), out of this chamber (5), characterized in that externally driven synchronization means (15) are provided, by means of which the respective ejection device (10, 13) can be operated as a function of the rotational movement and/or the angular position of the projectile holder (2) and/or of the propellant charge holder (4),

   and in that the externally driven synchronization means (15) ensure that no further cycle is started after completion of the final cycle, as a result of which no further new propellant charge (7) and no further new projectile (6) is inserted into one of the chambers (5, 3) of the propellant charge holder (4) and of the projectile holder (2).
2. Weapon system according to Claim 1,
   wherein the projectile holder (2) is borne such that it can rotate about an associated axis (X), the propellant charge holder (4) is borne such that it can rotate about an associated axis (Y), and the two axes (X, Y) are each arranged offset parallel to the bore axis (A) of the weapon barrel (1).
3. Weapon system according to Claim 2,
   wherein the ejection devices (10, 13) can be operated with a time offset with respect to the insertion devices (8, 9), such that the ejection devices (10, 13) always enter the chambers (3, 5) only with a time offset with respect to the insertion of the insertion devices (8, 9) after rotation of the projectile holder (2) and/or of the propellant charge holder (4) through 360°/n from the loading position, that is to say the n-th part of 360°, into the unloading position, where n is the number of chambers (3, 30) in the projectile holder (2) and/or the number of chambers (5, 50) in the propellant charge holder (4).
4. Weapon system according to Claim 2 or 3,
   wherein the ejection devices (10, 13) and the insertion devices (8, 9) are coupled (14) to one another such that a movement of the insertion devices (8, 9) toward the projectile holder (2) and the propellant charge holder (4) is linked to a movement, preferably of the same magnitude, of the ejection devices (10, 13) away from the projectile holder (2) and the propellant charge holder (4), and in that a movement of the insertion devices (8, 9) away from the projectile holder (2) and the propellant charge holder (4) is linked to a movement, preferably of the same magnitude, of the ejection devices (10, 13) toward the projectile holder (2) and the propellant charge holder (4).

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