EP2522949B1 - Device and propellant portioning method - Google Patents

Description

The invention relates to a device and a method for portioning propellant charges.

Especially in the field of large caliber weapons systems, such as battle tanks and artillery pieces, the actual weapon is operated with separate ammunition consisting of the ammunition to be fired and a separate, ignitable to accelerate the ammunition body propellant. Unlike cartridged ammunition, split ammunition has the potential to If necessary, vary the amount of propellant in order to attack more distant or nearby targets.

The propellant charge is often composed of several propellant charge modules that can be put together on the front and bottom connecting areas to different sized propellant charges.

The individual propellant charge modules usually consist of a thin outer skin, for example of a cardboard material or plastic, which can be easily damaged when not properly mating or when required from time to time separation of the propellant charge modules. Usually, the propellant charge modules are supplied by the manufacturer as mated packages of, for example, eight propellant charge modules, which subsequently have to be singulated before they are stowed inside the weapon system. If necessary, then a certain number of propellant charge modules is assembled to a propellant charge portion with the desired amount of propellant charge and - if, for example, in the context of maneuvers no firing takes place - then separated again.

It may therefore happen that a propellant charge module is plugged together several times to a propellant charge and then separated again. To isolate the nested propellant charge modules are usually placed on an edge and then applied to be separated propellant charge module from above with a force, whereby the connector between the propellant charge modules to be solved. Since the propellant charge modules often very tightly stuck together due to manufacturing tolerances, this can lead to unwanted damage to the outer skin of the propellant charge modules, which under certain circumstances means that they can not be used.

To avoid such problems, sometimes structurally elaborate devices are known, with which the propellant charge modules portioned by mating to a propellant charge of the desired size and, if necessary, can be separated into individual portions again. In the EP 1 596 150 A1 For example, a device for portioning a propellant charge is described, which has a structurally comparatively complex, dependent on external energy sources construction.

In addition, devices are known from the pipeline construction, which have two holding elements for receiving a respective tube, which are manually movable in such a way that the pipes can be joined together or separated. Such devices are for example from the US 4,893,393 A. or the US 3 426 417 A known.

The object of the invention is to provide a structurally simple device as well as a method for portioning a propellant charge, in which the risk of damage to the propellant charge modules is low.

In a device for portioning a propellant charge of pluggable propellant charge modules is proposed to solve the problem that this comprises two holding elements for receiving in each case at least one propellant charge module, which are manually movable against each other for portioning the propellant charge.

According to the invention, the holding elements can be coupled to one another by way of a gear mechanism such that a rotational movement of the holding elements is converted into an axial movement of the propellant charge modules accommodated in the holding elements. Conceivable are various types of transmissions, which convert a rotational movement of the holding elements in an axial movement of the propellant charge modules. In this context, a screw gear has proven to be particularly advantageous in terms of design, which converts the rotational movement of the holding elements in an axial movement of the propellant charge modules, through which the plug connection between the propellant charge modules can be produced or separated.

Such a configuration allows a structurally simple, independent of external energy sources construction of the device for portioning the propellant charge. By manually moving against each other, the propellant charges can be portioned in a simple manner. With the device propellant charge modules can be plugged together to form a larger propellant charge or put together propellant charge modules, without doing so Damage to the propellant charge modules are to be feared.

An advantageous embodiment provides that the holding elements are designed such that they hold the propellant charge module under pressure. By applying the holding pressure, the propellant charge modules can be kept in a simple manner in the holding element and released by discharge again.

Of constructive advantage in this context is also an embodiment, according to which the holding elements have two pincer-like articulated clamping elements. By actuating the forceps-like coupled clamping elements, the required holding pressure can be manually applied to the propellant charge modules.

In order to achieve a defined system of propellant charge modules in the holding elements, it is proposed according to a further embodiment that on the inside of the clamping elements plungers are arranged for conditioning of the propellant charge module. Advantageously, the pressure pieces made of a rubber-elastic material, resulting in a shell of the propellant charge modules gentle system. Also, the plungers may be designed so spring loaded that their spring spans when creating the plungers to the propellant charge modules. This results in a defined pressure limitation, by which damage to the propellant charge module is avoided.

With a view to easy handling, it is proposed that the clamping elements have handles by means of which the clamping elements can be tensioned against the propellant charge modules. By gripping the handles, a relative movement between the two holding elements can be generated in this way at the same time and the required holding pressure is exerted on the propellant charge module which results in a particularly user-friendly design.

In a further embodiment of the invention, it is proposed that the holding elements for portioning the propellant charge can be coupled to one another. After the two holding elements have been coupled together, a defined relative movement of the holding elements and thus the propellant charge modules can be generated via the coupling.

A further embodiment provides that one of the holding elements has a groove and the other has a slot nut which can be introduced into the groove. The movement of the sliding block within the groove results in a structurally simple manner a guided movement of the holding elements.

In this context, it is also advantageous if the groove has an axially extending axial region and an angle extending obliquely contrasting. The nut can, depending on whether a disconnect or mating of two propellant charge modules is desired, either enter the groove over the oblique region or over the axial region.

Moreover, in a method for portioning propellant charge for achieving the above-mentioned object, it is proposed that the propellant charge modules are moved against each other via a device of the type described above.

Such a method allows a simple, independent of external energy sources portioning the propellant charge. By manually moving against each other, the propellant charges can be portioned in a simple manner. With the device propellant charge modules can be plugged together to form a larger propellant charge or put together propellant charge modules, without causing damage to the propellant charge modules to be feared.

In a further development of the method, it is further proposed that the two holding elements are first attached to at least one propellant charge module and then coupled together.

In a further embodiment, it is proposed that the mutually coupled holding elements are rotated against each other and the rotational movement of the holding elements is converted into an axial movement of the recorded in the holding elements propellant charge modules. This makes it possible to achieve a defined portioning of the propellant charge.

Fig. 1:

in perspektivischer Ansicht ein Halteelement,

Fig. 2:

in perspektivischer Ansicht zwei Halteelemente mit zwei ineinander gesteckten Treibladungsmodulen,

Fig. 3:

eine perspektivische Ansicht zweier miteinander gekoppelter Treibladungsmodule mit zwei ineinander gesteckten Treibladungsmodulen,

Fig. 4:

eine seitliche Ansicht gemäß der Darstellung in Fig. 3,

Fig. 5:

eine der Darstellung in Fig. 3 entsprechende Darstellung, wobei die Halteelemente gegeneinander verdreht dargestellt sind,

Fig. 6:

eine seitliche Ansicht gemäß der Darstellung in Fig. 5,

Fig. 7:

eine perspektivische Ansicht der Halteelemente nach dem Trennen zweier Treibladungsmodule, und

Fig. 8:

eine seitliche Ansicht gemäß der Darstellung in Fig. 7.

Further details and advantages of a device according to the invention and of a method according to the invention are described below with reference to be explained in the accompanying drawings of an embodiment. Show:

Fig. 1:

in perspective view a holding element,

Fig. 2:

in perspective view two holding elements with two nested propellant charge modules,

3:

a perspective view of two coupled propellant charge modules with two nested propellant charge modules,

4:

a side view as shown in Fig. 3 .

Fig. 5:

one of the illustration in Fig. 3 corresponding representation, wherein the holding elements are shown rotated against each other,

Fig. 6:

a side view as shown in Fig. 5 .

Fig. 7:

a perspective view of the holding elements after separating two propellant charge modules, and

Fig. 8:

a side view as shown in Fig. 7 ,

Fig. 1 shows a holding element 3 of the two of the basic structure similarly designed holding elements 3, 4 existing device 1, see. also Fig. 3 ,

The two holding elements 3, 4 serve to receive a respective propellant charge module 2 and can be manually moved against each other for portioning a propellant charge composed of two propellant charge modules 2.

The propellant charge module 2 is received in the interior of the holding elements 3, 4 and held in the manner of a pair of pliers under pressure. For this purpose, the holding elements 3, 4 have two clamping elements 5, 6 connected via a joint 7, which in the exemplary embodiment are designed in the manner of half-shells.

On the tensioning elements 5, 6 opposite side of the joint 7, the clamping elements 5, 6 are each provided with handles 10, 11, in which an operator by hand penetrate and in this way a pressure on the between the clamping elements 5, 6 arranged propellant charge module 2 can muster. At the same time can be generated on the handles 10, 11, a relative movement between the two holding elements 3, 4, which will be discussed in more detail.

Since the propellant charge modules 2 usually consist of an easily damaged outer casing, pressure pieces 9 are provided on the inner side 8 of the clamping elements 5, 6, by means of which the pressure is applied to the casings of the propellant charge modules 2 at several points. The plungers 9 are made of a rubber-elastic material, which can produce a uniform pressure distribution on the envelopes of the propellant charge modules 2. Further, the pressure pieces 9 are biased by a spring tensioning mechanism not shown in detail in the direction of the propellant charge modules 2, so that the pressure pieces 9 against a pressure on the propellant charge modules 2 against the pressure of the spring in the direction of the inside 8 of the clamping elements 5, 6 move, which can limit the pressure applied to the propellant charge modules 2 pressure.

As in particular the representation in Fig. 2 shows, the device 1 consists of two separate holding elements 3, 4, which can be coupled to each other for portioning the propellant charge, as hereinafter with reference to the representations in the Figures 2-8 will be discussed, which illustrate the processes when separating two propellant charge modules 2.

Fig. 2 shows in perspective view two propellant charge modules 2, which are frontally plugged together. For this purpose, the propellant charge modules 2 have, in the region of their one end face, a plug-in area which is reduced in relation to the remaining diameter of the propellant charge module 2 and which can be plugged into a correspondingly shaped recess in the bottom side of an adjacent propellant charge module 2.

In order to be able to separate two propellant charge modules 2, which are thus put together, in a defined manner without the risk of damaging the casing of the propellant charge module 2, the one holding device 3 is first placed on a propellant charge module 2. Subsequently, the second holding device 4 is placed on the adjacent propellant charge module 2. Subsequently, the two holding elements 3, 4 are coupled together via a gear 12, cf. also the representation in Fig. 3 in which the transmission area is shown transparent for the purpose of illustration, whereby the internal gear components are visible.

The serving for coupling the holding elements 3, 4 gear 12 is formed in the embodiment in the manner of a screw gear. For this purpose, a holding device 3 in the region of its on the other holding device 4th assigning end on a groove 13. The groove 13 consists of an axially extending in the axial direction of the propellant charge modules 2 Axialbereich 13.1 and a beveled with respect to the axial region 13.1 inclined region 13.2. Both the axial region 13.1 and the oblique region 13.2 terminate in one end face of the retaining element 3, which is why a sliding block 14 can be introduced from the axial direction into both the axial region 13.1 and the oblique region 13.2 of the groove 13. The sliding block 14 is arranged on the inside of an annular region 14.1 arranged on the retaining element 4 and points in the direction of the interior of the retaining element 4.

After the initially loose placement of both holding elements 3, 4 on the propellant charge modules 2, the holding element 4 and with this the sliding block 14 relative to the support member 3 are moved. In this case, the sliding block 14 enters the axial region 13.1 of the groove 13 until the in Fig. 3 shown end position is reached, in which the sliding block 14 is located in the transition between the axial region 13.1 to the oblique region 13.2 of the groove 13.

In this position, an operator can grab the holding elements 3, 4 at their handles 10, 11, which on the one hand generates the required clamping action on the propellant charge modules 2 and on the other opens the possibility to rotate the holding elements 3, 4 against each other. The mutual rotational movement of the holding elements 3, 4 is added via the gear 12 an axial movement, so that the assembled propellant charge modules 2 are axially separated from each other. When turning the holding elements 3, 4, the sliding block 14 enters the oblique region 13.2 of the groove 13, whereby the required axial movement is generated in a power-saving and defined manner. Both the rotary and the axial movement is transmitted to the propellant charge modules 2, so that they at the same time Loosen each other axially from each other until the connector is released.

In Fig. 5 a position is shown in which the sliding block 14 has reached the end of the oblique portion 13.2 of the groove 13. In this position, the propellant charge modules 2 are separated from each other, see. also the representation in Fig. 6 ,

The retaining elements 3, 4 are again decoupled from each other after leaving the sliding block 14 from the inclined area 13.2 and the propellant charge modules 2 are separated from each other, cf. also the representations in the FIGS. 7 and 8 ,

When plugging two propellant charge modules 2, the processes are similar, but in this case the sliding block 14 does not enter via the axial region 13.1 in the groove 13, but on the inclined portion 13.2, so that upon mutual rotation of the holding elements 3, 4 facing one another axial movement the propellant charge modules 2 is generated, which causes the propellant charge modules 2 are connected to each other at the front and bottom.

The above-described device 1 for portioning propellants is characterized by a comparatively simple, independent of external energy sources construction and is easily operated by untrained operators. Damage to the propellant charge modules 2 are avoided even with multiple connection or disconnection.

Reference numerals:

1

contraption

2

Propellant module

3

retaining element

4

retaining element

5

clamping element

6

clamping element

7

joint

8th

inside

9

Pressure piece

10

Handle

11

Handle

12

transmission

13

groove

13.1

axial

13.2

slant range

14

sliding block

14.1

rings range

Claims (9)

1. Device for portioning a propellant charge consisting of propellant charge modules (2) which can be plugged together, having two holding elements (3, 4) for respectively receiving at least one propellant charge module (2), which are manually movable with respect to one another to portion the propellant charge, characterized in that, to portion the propellant charge, the holding elements (3, 4) can be coupled to one another via a mechanism (12) in such a way that a rotary movement of the holding elements (3, 4) is converted into an axial movement of the propellant charge modules (2) received in the holding elements (3, 4).
2. Device according to Claim 1, characterized in that the holding elements (3, 4) are designed in such a way that they hold the propellant charge module (2) under the action of pressure.
3. Device according to Claim 1 or Claim 2, characterized in that the holding elements (3, 4) have two clamping elements (5, 6) which are articulatedly coupled to one another in the manner of tongs.
4. Device according to Claim 3, characterized by pressure pieces (9) which are arranged on the inner side (8) of the clamping elements (5, 6) and intended for bearing the propellant charge module (2).
5. Device according to either of Claims 3 or 4, characterized in that the clamping elements (5, 6) have handles (10, 11) via which the clamping elements (5, 6) can be clamped against the propellant charge modules (2).
6. Device according to one of the preceding claims, characterized in that one of the holding elements (3) has a groove (13) and the other has a sliding block (14) which can be introduced into the groove (13).
7. Device according to Claim 6, characterized in that the groove (13) has an axially extending axial region (13.1) and an oblique region (13.2) extending in an angled-off manner thereto.
8. Method for portioning propellant charges, characterized in that the propellant charge modules (2) are moved with respect to one another via a device (1) according to one of Claims 1 to 7, and in that the two holding elements (3, 4) are first attached to respectively at least one propellant charge module (2) and then coupled to one another.
9. Method according to Claim 8, characterized in that the holding elements (3, 4) coupled to one another are rotated with respect to one another and the rotary movement of the holding elements (3, 4) is converted into an axial movement of the propellant charge modules (2) received in the holding elements (3, 4).

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