EP0239755B1 - Rammer for ordnance - Google Patents

Abstract

A flick rammer for artillery rounds. The rammer has a loading tray that is positioned in alignment with the powder chamber at a prescribed distance to the rear of the gun. The tray accommodates the round. The rammer also has a mechanical acceleration component that engages the rear of the round and is connected to a cylinder-type drive mechanism. To improve the device to the extent that ramming will remain rapid whereas the design will be simple enough to operate reliably even at light loads and to occupy very little space, the cylinder-type drive mechanism is a pneumatic cylinder that communicates with a compressed-air reservoir through a rapid-opening control valve, and the mechanical acceleration component is connected to the moving component of the pneumatic cylinder through a stroke-transmission mechanism with a transmission ratio greater than 1.

Description

The invention relates to a free-flight rifle for artillery projectiles with a loading trough in a predetermined distance behind the gun, flush with the cargo space, into which the projectile can be inserted, and to a mechanical acceleration member acting on the rear of the projectile, which is designed as the free end of a pivotable attachment lever , which is connected to a cylinder drive via a path transmission device with a transmission ratio greater than 1.

To load artillery guns, it is necessary to drive the 50 kg or heavier artillery shells into the barrel of the gun at a speed of at least 1.5 m / sec until the soft metal guide ring of the projectile is pressed into the conical part of the cargo space. The press-in must be so strong that the projectile no longer falls out due to its own weight, even when the gun barrel is very high, and at the same time the cargo space is sealed to the front.

Most of the known tank artillery pieces are currently being put on by the crew manually. For this purpose, the gun barrel is brought into a suitable position, the grenade is inserted into the cargo area by hand and then driven into the cargo area by two to three men with a ramrod with the greatest possible force. This method has been found to be disadvantageous because, for loading the gun barrel, it is brought into a position that deviates from the direction of the shot must, which is time consuming and then requires a new sideboard. Furthermore, this type of loading requires a large personnel expenditure with considerable physical strain on the crew members. The fire speeds achieved thereby no longer meet the requirements of modern fire fighting.

Various devices are known which are intended to dispense with the manual application of the projectile described.

In a known, so-called chain piecer, two chains wound on a drum are brought together by a special gear in such a way that the two chains hook into one another and thereby stiffen strongly. The assembled chain then emerges from the gearbox in a quasi-rod shape and can be used to attach the projectile. A disadvantage of this known device is, in addition to the great effort for the chain transmission, the relatively slow attachment speed, which also results from the fact that the chain must be withdrawn again from the cargo space after the attachment process.

Rack and pinion attachments are based on a principle similar to that of chain attachments, in which a gear drives a rack forward, which causes the attachment process. Above all, this device has the disadvantage that a long space must be available behind the gun to accommodate the rack, which, as a rule, cannot be the case with tank artillery guns.

Telescope attachments have also become known in which the attachment process is carried out by a telescopic pneumatic cylinder takes place, which is arranged behind the gun. This arrangement is more suitable for being integrated into armored artillery guns, but in turn also has the disadvantage of being quite slow and in particular taking up valuable time for the withdrawal process.

Finally, there are so-called free-flight attachments, which are based on the principle of imparting such a great acceleration to a grenade located outside the cannon that after leaving the acceleration system, the grenade continues to move in free flight due to the moment in its existing moment due to the acceleration and the attachment process is open this way is realized.

In known free-flight attachments, this acceleration is generated either on the basis of a prestressed spring or by means of a controllable hydraulic cylinder.

An advantage of the free flight attachments is the high speed with which the attaching process takes place and in particular the fact that no time is wasted for withdrawing the attachers from the cargo space. A major disadvantage of the known free-flight attachments, however, is that the effort for control technology, valves, pressure and compensation accumulators in hydraulic and mechanical systems is so great that in addition to the uncomfortably high effort, which reduces the reliability of the system, there is also a lot of space inside a vehicle is required to integrate the system. In free-flight attachments with a preloaded spring, there is still the problem that the spring cannot be preloaded sufficiently when using small loading quantities.

The invention is based on a free-flight attachment with the features described at the beginning and in the preamble of claim 1. Such a free-flight attachment is described, for example, in DE-A-2 320 398. In this known free-flight attachment, the pivotable attachment lever acting on the rear of the projectile is connected to a hydraulic cylinder via a planetary gear.

Furthermore, BE-A-656 276 describes a projectile rifle in which the projectile is pushed into the loading position under the action of a hydraulic cylinder without the interposition of a path translation device. It is also proposed in this connection to use a pneumatic cylinder instead of the hydraulic cylinder.

The invention has for its object to design a free flight attachment of the type mentioned in such a way that, on the one hand, it can be started at high speed, but on the other hand only very little technical effort is required, the functional reliability is independent of the loading quantity and very little space is required .

This object is achieved according to the invention with the features from the characterizing part of patent claim 1.

Advantageous embodiments of the free-flight adapter according to the invention are described in the subclaims.

The invention is based on the basic idea of generating the force required to accelerate the projectile (approx. 5000 Nm) using a pneumatic cylinder. Since large forces have to be made available very quickly when artillery shells are used, but the positioning accuracy is insignificant, a pneumatic system is considerably superior to the hydraulic system. To generate the force required to accelerate the projectile, a particularly large pneumatic cylinder with a short stroke can be used, the path of which is translated by the path translation device, for example in a ratio of 5: 1. The pneumatic cylinder is chosen so large that despite the translation of 5: 1, for example, the necessary force (approx. 5000 Nm) is still available at the point of impact of the projectile. Since it is important to move the pneumatic cylinder particularly quickly and a According to the further invention, a slow pressure build-up in the cylinder, which is normally out of the question, is preceded by a compressed air accumulator upstream of the pneumatic cylinder, and the pneumatic cylinder is connected to the compressed air accumulator via a quick-opening control valve with a particularly large cross-section. It is advantageous if the pressure accumulator and pneumatic cylinder are designed in such a way and the pre-pressure prevailing in the pressure accumulator is so much above the maximum permissible pressure of the pneumatic cylinder that after opening the control valve and the sudden pressure equalization in the compressed air accumulator and pneumatic cylinder that the maximum pressure permissible for the pneumatic cylinder prevails . This ensures that the pneumatic cylinder always works with the maximum possible force and speed depending on the pressure introduced. The consequence of this is that, together with a suitable transmission ratio of approx. 5: 1, the accelerator can be accelerated so strongly that an artillery shell with a weight of 50 kg attached to it reaches a starting speed of more than 7 m / sec. This starting speed is clearly sufficient to place the projectile in any position of the gun barrel in the cargo area.

• a) Die Ansetzgeschwindigkeit des Geschosses liegt deutlich höher als bei hydraulischen oder federgespannten Systemen.
• b) Der technische Aufwand für die Gesamtanlage ist wesentlich geringer als bei bekannten Systemen, da die Anlage grundsätzlich nur einen Druckluftbehälter, einen Pneumatikzylinder und ein Ventil benötigt, während alle bisher bekannten Vorrichtungen sehr viel mehr notwendige Baugruppen aufweisen. Dies eröffnet die Möglichkeit eines redundanten Aufbaus.
• c) Die Verwendung von Preßluft mit ca. 16 bar Druck ist ungefährlich für die Besatzung im Gegensatz zu hydraulischen Systemen, bei denen das toxische, aggressive und brennbare Hydrauliköl mit 120 bis 150 bar und mit Temperaturen von über 100°C im Einsatz ist.
• d) Die Verwendung von Preßluft ist hinsichtlich geringfügiger Leckage unkritisch, weil einerseits kein Mediumsverlust entsteht, der eine Versorgung mit Ersatzmedium erforderlich macht und zum anderen durch die Leckage keine Toxitizität, Brandgefahr oder Korrosion entstehen kann.
• e) Die Reparatur von pneumatischen Systemen, beispielsweise das Auswechseln von Leitungen, ist ohne Probleme (z.B. anschließende Entlüftung des Systems) möglich.
• f) Das pneumatische Freiflugansetzsystem kann im Notbetrieb nach Ausfall der zentralen Steuerung und Energieversorgung auch aus einer mitgeführten Preßluftflasche direkt angesteuert werden, wodurch ein Freiflugansetzen im Notbetrieb möglich ist.
• g) Der pneumatische Freiflugansetzer ist in seiner Leistungsfähigkeit nicht von der verschossenen Treibladung abhängig.

In summary, it can be said that the following advantages can be achieved with the free-flight attachment according to the invention:

• a) The attachment speed of the projectile is significantly higher than with hydraulic or spring-loaded systems.
• b) The technical outlay for the overall system is considerably less than with known systems, since the system basically only requires a compressed air tank, a pneumatic cylinder and a valve, while all previously known devices have much more necessary assemblies. This opens up the possibility of a redundant structure.
• c) The use of compressed air with approx. 16 bar pressure is harmless for the crew in contrast to hydraulic systems, in which the toxic, aggressive and combustible hydraulic oil is used with 120 to 150 bar and with temperatures of over 100 ° C.
• d) The use of compressed air is not critical with regard to slight leakage, because on the one hand there is no loss of medium, which requires a supply of replacement medium, and on the other hand no leakage, toxicity, fire risk or corrosion can result from the leakage.
• e) The repair of pneumatic systems, for example the replacement of lines, is possible without any problems (eg subsequent ventilation of the system).
• f) The pneumatic free flight attachment system can also be controlled in emergency operation after failure of the central control and power supply from a compressed air bottle that is carried along, whereby free flight attachment in emergency operation is possible.
• g) The performance of the pneumatic free-flight attachment is not dependent on the propellant charge being fired.

In the following, an embodiment of a free-flight attachment according to the invention is explained in more detail with reference to the accompanying drawings.

Fig. 1

in einer teilweise als Schaltbild dargestellten Prinzipdarstellung einen Freiflugansetzer unmittelbar vor der Auslösung seiner Betätigung;

Fig. 2

den Freiflugansetzer nach Fig. 1 während des Beschleunigungsvorganges des Geschosses;

Fig. 3

den Freiflugansetzer nach Fig. 1 und 2 nach Ablauf des Ansetzvorganges.

The drawings show:

Fig. 1

in a schematic diagram partially shown as a circuit diagram, a free-flight attachment immediately before its actuation;

Fig. 2

1 during the acceleration process of the projectile;

Fig. 3

1 and 2 after the attachment process.

1 to 3, the rear end 1 of a gun barrel is shown in a highly schematic representation, on which a free-flight attachment is arranged, with a loading trough 2 arranged in alignment with the cargo space 3 of the gun barrel 1, into which a projectile A can be inserted. The actual gun barrel 5 with trains and fields connects to the cargo space 3 via a conical part 4.

The free flight attachment furthermore has an attachment lever 6 which can be pivoted about a pivot axis 9, the free end of which engages on the rear side of the projectile A inserted into the loading trough 2 via a guide roller 7. At a pivot point 8 between the pivot axis 9 and the free end of the attachment lever 6, a transmission linkage 13 engages, which is connected via an articulated connection 14 to the piston 11 of a pneumatic cylinder 10, the piston movement of which takes place against a return spring 12.

The articulation point 8 on the attachment lever 6 is selected so that the ratio of the distance of the free end of the attachment lever 6, i.e. the distance of the guide roller 7, from the pivot axis 9 to the distance of the articulation point 8 from the pivot axis 9, which is the ratio of the translation of the movement by Attachment lever 6 is about 5: 1.

The inlet 15 of the pneumatic cylinder 10 is connected via a quick-opening control valve 17 with an electromagnetic actuating part 18 to a compressed air reservoir 19, which in turn is connected via a further control valve 20 with an electromagnetic actuating part 22 to a compressed air source 21.

Furthermore, the cylinder outlet 16 of the pneumatic cylinder 10 can be connected to the outside air via a control valve 25 with an electromagnetic actuating part 26.

The electromagnetic actuating parts 18, 22 and 26 are in an electrical control circuit, the actuating part 18 being switchable by a switch 24, the actuating part 22 by a switch 23 and the actuating part 26 by a switch 27.

The operation of the free-flight adapter shown in FIGS. 1 to 3 is as follows:
In the starting position shown in FIG. 1, the projectile A is inserted into the loading trough 2 manually or by a loading mechanism. The free end of the attachment lever 6 is located behind the floor and lies with the guide roller 7 on the floor of the floor.

In this state, the compressed air reservoir 19, controlled by the filling valve 20, is filled with compressed air. When the switch 24 is actuated, the control valve 17 is opened via the electromagnetic actuating part 18 and the compressed air is suddenly introduced into the pneumatic cylinder 10. In this case, the piston 11 moves upwards at high speed, and in its end position, equality of pressure between the compressed air reservoir 19 and the pneumatic cylinder 10 is achieved. The movement of the piston 11 is transmitted via the connecting rod 13 to the attachment lever 6, the entire arrangement being chosen so that the connecting rod 13 is subjected to tension, which reduces the risk of buckling. The attachment lever 6 transmits its moment to the floor A in the loading trough 2 and this starts in the direction of the cargo space 3 in motion. This state is shown in Fig. 2. The projectile A is in the cargo space 3 on the flight towards the piecing cone 4. The articulated connection 14 between the linkage 13 and the piston 11 compensates for the lateral deviation of the movement of the piecing lever 6.

From Fig. 3, the final state of the piecing process can be seen by the projectile A has passed through the cargo space 3 and is fixed with its guide ring in the conical part 4.

At the same time, the vent valve 25 is opened by switching on the switch 27 via the actuating part 26, as a result of which the pneumatic cylinder 10 is vented and the piston 11 returns to its starting position under the action of the return spring 12.

In the embodiment of the free flight attachment shown in FIGS. 1 to 3, the pivot axis 9 of the attachment lever 6 is in a plane E1, which is perpendicular to the longitudinal axis L of the loading trough 2, between the front and rear ends of the loading trough 2 and at a predetermined distance Arranged from this longitudinal axis L and the attachment lever 6 is guided from the plane E1 into a plane E2, which is arranged perpendicular to the longitudinal axis L behind the loading trough 2, the attachment lever 6 at Reaching the plane E2 has a bend, so that its free end 6a lies essentially in this plane E2. 3, this arrangement and design has the advantage that the return of the gun barrel 1 in the direction R when firing the shot, which can be done up to the position shown in dashed lines in FIG. 3, is not hindered by the attachment lever 6 .

As the exemplary embodiment shown shows, the described free-flight adapter can be constructed from very few modules which can be arranged in a compact manner. This opens up the possibility of redundant expansion in that two identically constructed free-flight attachments can be arranged very close to each other on a gun barrel.

In the embodiment shown in FIGS. 1 to 3, a piston cylinder is used as the pneumatic cylinder. At this point, a pneumatic membrane cylinder with a large cylinder area can also be used, by means of which the device can be activated particularly quickly.

Claims (6)

1. Free-flight rammer for ordnance shells having a loading tray (2) which is arranged at a predetermined distance behind the gun and in line with the loading chamber (3), into which tray the shell (A) can be placed, as well as having a mechanical accelerating element, which acts on the rear of the shell and is designed as the free end (7) of a pivotable ramming lever (6), which is connected to a cylinder drive (10) via a displacement transmission device having a transmission ratio greater than 1, characterised in that the cylinder drive is designed as a pneumatic cylinder (10) which is connected via a quickly opening control valve (17) to a compressed-air accumulator (19), and the pivotable ramming lever (6) is connected at a predetermined point of articulation (8) via a connecting linkage (13) and a link connection (14) to the movable part (11) of the pneumatic cylinder (10), the transmission ratio being given by the ratio between the distance of the free end (7) from the pivot axis (9) and the distance of the point of articulation (8) from the pivot axis (9).
2. Free-flight rammer according to Claim 1, characterised in that the transmission ratio is at least 5:1.
3. Free-flight rammer according to Claim 1 or 2, characterised in that pressure accumulator (19) and pneumatic cylinder (10) are designed in such a way and the supply pressure prevailing in the pressure accumulator (19) can be set to a value which lies so much above the maximum admissible pressure of the pneumatic cylinder (10) that, with opened control valve (17) and abrupt pressure equalisation which takes place, the maximum admissible pressure for the pneumatic cylinder prevails in the pressure accumulator (19) and pneumatic cylinder (10).
4. Free-flight rammer according to one of Claims 1 to 3, characterised in that the pivot axis (8) [sic] of the ramming lever (6) is arranged in a first plane (E1), perpendicular to the longitudinal axis (L) of the loading tray (2), and between the front and the rear end of the loading tray (2) at a predetermined distance from this longitudinal axis (L), and the ramming lever (6) is guided out of this first plane (E1) into a second plane (E2), perpendicular to the longitudinal axis (L), behind the loading tray (2), and has in the region of its free end a section (6a) running essentially in this second plane (E2).
5. Free-flight rammer according to one of Claims 1 to 4, characterised in that the pneumatic cylinder (10) is arranged with respect to the ramming lever (6) such that, upon its actuation, the connecting linkage (13) is subjected to tensile loading.
6. Free-flight rammer according to one of Claims 1 to 5, characterised in that the pneumatic cylinder is designed as a diaphragm cylinder.

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