EP0227671B1 - Propellant module - Google Patents

Abstract

In a propellant module with a combustible container the ignition charge for all charge graduations and in every charge position must be so arranged that in the low and high gas pressure range, while complying with the same charge graduations, a regular gas pressure pattern and a reproducible blasting outflow are made possible, and in addition a modular design is ensured by which it is possible to achieve as simultaneous ignition as possible over the whole length of the charge, for any desired chargeability and exchangeability of the module. The propellant module (1) comprises over the entire length of the module (1) a co-axially-arranged free ignition channel (3) which is formed by an ignition charge (5, 7) which is symmetrically arranged to the end-walls (8, 9) of the container (10). The limiting wall (4) of the ignition channel (3) may consist of a tube (14) in whose wall cross-section an ignition charge (5) is incorporated. The wall cross-section of the channel (3) may however also consist of a combustible support tube (6) and an ignition charge preferably made of annular pieces. The symmetrical container design enables any desired chargeability and ignition from either endside (8) or (9). The free cross-section of the ignition channel (3) ensures a virtually simultaneous ignition of the ignition charge (7) over the overall charge length.

Description

The invention relates to a propellant charge module according to the preamble of patent claim 1.

In such a propellant charge module known from FR-A-15 14 293, however, the tube forming the free ignition channel is cast from comparatively slow-burning nitrocellulose in a complex casting process. The tube contains no means to enlarge the surface, so that a faster formation of the flame front in the axial direction of ignition cannot be achieved. Furthermore, this ignition channel does not contain any means which, depending on the speed of the flame front emanating from a propellant charge igniter, enable the propellant charge to be burned on almost simultaneously. Furthermore, there is no disclosure of the diameter range in which the free ignition channel can form a simultaneous and rapid flame front. A particular disadvantage is that the charge build-up shown in FIG. 13 makes it difficult to reproduce the same sequence of shots because the end-side loading j causes the propellant charge containers stacked one behind the other to move in the longitudinal direction, to be compressed and damaged. In addition, in this known propellant charge module, the destruction of the central tube is to be initiated mechanically early on by the pressure of the ignition charge or the propellant charge. Early, in particular mechanical, destruction of the ignition channel is furthermore not expedient for a central introduction of the ignition beam and for a faster formation of the flame front in the axial ignition direction.

Even with the pyrotechnic charge known from EP-A-0 064 444, a rapid free formation of the flame front in the axial ignition direction is not possible because it is not a free cylindrical ignition channel, but a conical delay set that is arranged centrally.

From DE-A-31 13406 it is known to use solid, flammable cardboard cartridge sleeves instead of a cartridge bag. These cartridge sleeves contain an end loading and a centrally arranged transfer charge as well as a booster charge, whereby it is advantageous for better and faster ignition to provide a comparatively space-consuming ignition beam funnel.

A major disadvantage of this arrangement is that a multiple number of cartridge sleeves cannot be loaded one after the other, since this results in impermissibly large gas pressure differences over the entire length of the propellant charge at higher loading densities. Propellant powder prone to brittle fracture can be destroyed on the floor of the floor, which in unfavorable cases can lead to damage to the floor or the weapon. Furthermore, it is possible with these cartridge bags or cartridge sleeves that they are inserted in the reverse position into the cargo space, which can result in failure and in extreme cases damage to the weapon. Studies on barrel weapons with such or similar modular bulk powder propellant charges have shown that, especially with loading densities of more than 0.4 g / cm ^3, irregular gas pressure profiles and thus non-reproducible firing sequences can occur. The reason for this behavior is to be found in the unsatisfactory central implementation of the modules, whereby the ignition on the front side can intensify this effect.

In contrast, it is an object of the invention to ensure an easy-to-manufacture and laborable module structure, by means of which, with any loadability and interchangeability of the modules, a possible simultaneous ignition over the entire charge length by a propellant charge lighter and while maintaining the same charge gradations in the low and high gas pressure range uniform gas pressure and a reproducible firing sequence are possible.

This object is achieved by the invention specified in claim 1. The subclaims mention advantageous configurations.

The arrangement of a free ignition channel within a porous ignition charge or an ignition charge consisting of ring tablets of the propellant charge module advantageously results in the propellant charge powder being ignited almost uniformly over the entire charge length and thereby minimizing the differential pressures within the cargo space. This makes it possible to influence the gas pressure curve in such a way that a perfectly reproducible firing sequence can be achieved even at high loading densities.

The axially symmetrical arrangement of the ignition charge in the area of the ignition channel wall ensures, in addition to fast and central ignition of the propellant charge powder, simple manufacture and processing of the igniter charge within the propellant charge module. A particularly simple construction is achieved if the ignition tube consists of extruded porous nitrocellulose. A simple variation of the length of the primer charge is made possible by the use of ring tablets that can be stacked on the face. According to a further design feature, these ring tablets can advantageously be arranged centering themselves.

Furthermore, the propellant charge module allows an axially arbitrary installation position in the cargo space. For this purpose, the container is axially and radially symmetrical to the central axis such that the propellant charge module in the gun barrel can be loaded several times in a row in any axially forward or backward facing position of the end walls and in the loading position from each end wall the firing of the respective propellant charge modules by ignition clouds is possible.

The constant clear diameter of the ignition channel is advantageously between 5 and 40 mm, so that a spreading of the ignition vapor over the entire charge length is made possible faster than the radial firing of the propellant charge to be transmitted by the ignition charge.

Depending on the artillery task, any module of the same type can now be fed to different shot units. This advantageously eliminates the compulsory compliance with the charge sequence of previous partial propellant charges of different lengths.

The propellant charge modules can also be stored indefinitely thanks to moisture protection, their handling is uncomplicated and they ensure safe manual loading even in the dark, because the module end walls can now be swapped around arbitrarily when they are inserted into the cargo space.

Due to their equality and possibility of exchange, the propellant charge modules can now also be charged automatically. A time-consuming pre-sorting is advantageously unnecessary, so that the propellant charge modules can be stored in a simple manner and loaded by a loader without orientation. In this way, compared to known propellant charge modules, the firing order can be increased significantly and an increase in the power of the gun can be achieved.

The invention is explained in more detail with reference to the exemplary embodiments shown in the drawings.

• Fig. 1 in einer Schnittdarstellung das Treibladungsmodul mit verschiedenen der Modullänge entsprechenden Anzündladungen ;
• Fig. 2 in einer Schnittdarstellung das Treibladungsmodul mit verschiedenen aus Ringtabletten bestehenden und einem Teilbereich der Modullänge entsprechenden Anzündladungen ;
• Fig. 3 in einer Schnittdarstellung mehrfach im Waffenrohr angeordnete gleiche Treibladungsmodule.

It shows :

• 1 shows a sectional view of the propellant charge module with different ignition charges corresponding to the module length;
• 2 shows a sectional illustration of the propellant charge module with different igniter charges consisting of ring tablets and corresponding to a partial area of the module length;
• Fig. 3 in a sectional view of multiple propellant charge modules arranged several times in the gun barrel.

The propellant charge modules 1 shown in FIGS. 1 and 2 each consist of a container 10, a propellant charge powder 12 and an ignition channel 3 which is arranged coaxially over the entire module length 1 and has a free central cross section 25. The container 10 is symmetrical in multiple axes. It contains two symmetry elements, the central longitudinal axis 2 forming a first symmetry element and a mirror surface 23 leading perpendicular to the longitudinal axis 2 through the module center 31 forming a second symmetry element.

Accordingly, the outer wall 26 of the container 10 is constructed in a tubular manner in a known manner, cylindrical or polygonal, the transitions on both sides to the end walls 8, 9 arranged at right angles to the longitudinal axis 2 having the same radii R and the transitions 27, 27 'to the ignition channel 3 having the same central shapes.

The free ignition channel 3 is essentially formed by the ignition charge 5, 7, which is also arranged symmetrically to the end faces 8, 9 of the container 10.

The shape of the container 10 and the design of the ignition channel 3 enable the propellant charge module 1 in the weapon barrel 11 (FIG. 3) to be loaded several times in succession in any axially forward or backward position of the end walls 8, 9, with the loading position 13 (FIG 3) from each end wall 8, 9 the firing of the respective propellant charge modules 1 is made possible by fumes.

The diameter d of the free cross-section 25 of the ignition channel 3 is of such a size that the spreading of the ignition vapor over the entire charge length is faster than the radial ignition of the propellant charge powder 12 to be transmitted by the ignition charge 5, 7, the charge length being the sum of the individual lengths of the propellant charge modules 1 arranged in series in the cargo space of the weapon barrel 11 (FIG. 3).

The clear diameter d can be at least 5 mm and a maximum of 40 mm, depending on its essential influencing variables, for example the speed of propagation of the ignition jet or the ignition swell of the propellant charge igniter 28 (FIG. 3) and the burn-up characteristic of the ignition charge and the caliber, a preferred more favorable one Diameter range is between 12 and 30 mm.

Fig. 1 shows left and right halves differently formed ignition propellant charges 5, 7 with a constant clear diameter d over the entire module length 1. Left half (Fig. 1a), the boundary wall 4 consists of a continuous tube 14 forming the ignition channel 3, the wall cross section of which is made of an integrated one Ignition charge 5, preferably consists of extruded porous nitrocellulose or of extruded porous nitrocellulose and an admixture of known igniter charges. The tube 14 is fastened to the end walls 8, 9 in a manner not shown.

On the right-hand side (FIG. 1b), the wall cross section of the ignition channel 3 consists radially on the outside of a combustible support tube 6 and radially on the inside of an ignition charge 7 centered by the support tube 6. This ignition charge 7 is formed from ring tablets 15 stacked in the axial direction, the total length of which corresponds to the module length 1 . Instead of the support tube 6 and the ring tablets 15, the arrangement of self-centering ring tablets 24 (FIG. 2a) is optionally also possible.

The ring tablets 15 located on both ends of the ignition channel 3, but also the ring tablets 24, have centerings 30 for central attachment to the end walls 8, 9. A ring tablet 15, 24 also stacked on the end face and which is symmetrical over at least one partial area a Ignition charge 7 extending module length 1 is shown in FIG. 2.

In order to achieve an axially symmetrical central position of the partial region a of the ignition charge 7, the container 10 contains pipe connections 18 facing each other at the same distance b from the end walls 8, 9, which are provided with spacers 16 for the full frontal contact of the ring tablets 15, 24.

The pipe sockets 18 are each evenly necked in the transition area of the end walls 8, 9 to form a pipe extension 29, the necking can be rounded, for example. To fasten the spacers 16 to the respective pipe socket attachment 29, they have axially outward centerings 17. Compared to the position of the centerings 17 on the channel side shown in FIG. 2, these can also be arranged in a manner not shown, on the powdered fuel side, axially outwards for receiving the respective tube extension 29.

The spacers 16 have the purpose of axially fixing the ignition charge 5, 7. However, as is shown on the left in FIG. 2a, they can also be designed with an axially inward projection 29 'or a centering 30' for the radial fastening of the self-centering ring tablets 24.

For self-centering, the ring tablets are also formed on both sides on the end faces with a shoulder 29 "pointing in the axial direction and a centering 30". In this way, the ring tablets 24 can also be stacked in an axially centering manner.

If the use of an additional support tube 6 can be dispensed with when using self-centering ring tablets 24, then it is imperative for the radial fixation of the ring tablets 15 which do not have self-centering shown in FIG. 2b. The support tube 6.1 is connected to the spacers 16 in a manner not shown.

The ring tablets 15, 24 on the one hand allow the ignition charge to be arranged in a coherent axially symmetrical region a (FIG. 2a), but on the other hand also with the aid of a plurality of spacers 19 to be arranged between the ring tablets 15, an axially symmetrical arrangement of the ignition charge 7 in a plurality of partial regions a.

For the storage of the propellant charge module 1, combustible or consumable or consumable foils 20 are arranged on the pipe socket 18 as moisture protection for the primer charge 7 and the propellant charge powder 12. The foils 20 are arranged in the ignition channel 3 at the inwardly directed ends 21 of the pipe socket 18 or at the outwardly directed socket extensions 22 or at the entry and exit of the ignition channel 3 at the transitions of the pipe socket 18 to the end faces 8, 9. They can be designed as an individual part, but can also be connected in one piece with the pipe socket 18 or the end wall 8, 9 of the container 10. Such films 20 are also arranged as a moisture seal on both sides of the ignition channel 3 (FIG. 1).

In order to avoid residues in the cargo space 32 (FIG. 3), the container 10, the spacers 16, 19 and the support tube 6 are made of combustible materials which are known per se from cartridge ammunition. However, the material of the container 10 has such a strength that there is the possibility of loading a projectile (not shown) and the charge consisting of the propellant charge modules 1 in one charge. The ignition charge 7 consisting of ring tablets 15, 24 is also known and consists, for example, of a boron / potassium nitrate powder. Known bulk powder is preferably also used as the propellant charge powder 12.

Fig. 3 illustrates the arrangement several times in the cargo space 32 of a gun barrel 11 arranged one behind the other and loaded in any loading direction of the same propellant charge modules 1. The free ignition channel 3 allows the spread of the ignition jet or the ignition clouds of the propellant lighter 28 located in the tube closure 33 over the entire Charge length is faster than the radial firing of the propellant charge powder 12 to be transmitted by the ignition charge 5, 7 (FIG. 1). A known propellant lighter 28 with a projectile is expediently used to overcome the protective films 20 (FIG. 2).

The individual propellant charge modules 1 are provided on the outside with a lacquer coating, which advantageously provides moisture protection and a reduction in flame sensitivity.

Claims (7)

1. Propellant module with a combustible cylindrical container of which the outer wall (26), the end walls (8, 9) and a limiting wall (4) which forms a free coaxial ignition channel (5) are of symmetrical construction radially to the longitudinal axis (2) and also perpendicularly to a mirror surface (23) passing through the central point of the module, the propellant modules (1) situated in succession to one another in the loading chamber (30) forming an ignition channel of constant diameter, characterised by the fact that the cylindrical limiting wall (4) forming the free ignition channel (3) consists of an ignition charge (5) integrated as porous nitrocellulose, or as porous nitrocellulose containing an admixture of further ignition media in an extruded tube (14), or that the limiting wall (4) consists of annular tablets (15) stacked end side on and supporting the ignition charge (7), their length extending symmetrically over at least a part zone (a) of the length of the module (1), while the constant internal diameter (d) of the ignition channel (3) of a number of propellant modules (1) positioned in succession to one another in the loading chamber amounts to at least 5 mm and to not more than 40 mm and enables the ignition jet or ignition vapours of a propellant igniter (28) to be propagated over the entire length of the charge as compared to the initial combustion undergone by the propellant powder (12) and to be transmitted by the ignition charge (5, 7).

2. Propellant module in accordance with Claim 1, characterised by the fact that the wall cross section of the ignition channel (3) consists externally of a combustible support tube (6) and internally of annular tablets (15) centered by the support tube (6) and constructed as an ignition charge (7).

3. Propellant module in accordance with Claims 1 and 2, characterised by the fact that the ignition charge (7) consists of self-centering annular tablets (24).

4. Propellant module in accordance with one of Claims 1 to 3, characterised by the fact that the following features :

(a) the ignition charge (7) situated in at least one partial zone (a) and consisting of annular tablets (15, 24) is fixed in position by combustible spacers (16) ;

(b) the spacers (16) are in each case provided as a means of securing them to the container (10) with centering devices (17, 30') directed axially outwards or axially outwards and inwards.

5. Propellant module in accordance with one of Claims 1 to 4, characterised by the fact that in the container pipe socket pieces (18), serving to secure the spacers (16) are provided facing each other and an equal distance (b) from the end walls (8, 9).

6. Propellant module in accordance with one of Claims 1 to 5, characterised by the fact that combustible spacers (19) are provided in axially symmetrical positions between the annular tablets (15) of the ignition charge (7).

7. Propellant module in accordance with one of Claims 1 to 6, characterised by the following features :

(a) for the bearing system of the propellant module (1) combustible or expendable or consumable foils (20) are provided on the pipe socket pieces (18) in order to protect the ignition charge (7) and the propellant powder (12) from moisture ;

(b) the foils (20) are positioned at the inwardly directed ends (21) of the pipe socket pieces (18) or outwardly directed socket extensions (22), if in the ignition channel (3), or else at the transition points from the pipe socket pieces (18) to the end walls (8, 9) if at the inlet and outlet of the ignition channel (3).

Images