DE3931097A1 - Sub-calibre-propelling cage projectile with gas pressure sepn. - having extended propelling cage, hollow cylindrical section, segments and annular gap - Google Patents

Abstract

A sub-caliber propelling-cage projectile with differential gas pressure operated propelling-cage separation comprising the projectile (1) and propelling-cage (2), whereby in the rearwardly extended propelling-cage (2) a hollow cylindrical section (3) is fitted, the latter having a smaller external diam. than the propelling-cage (2) as well as a smaller O.D. than the inner diam. of barrel (4), thus defining an annular gap (5) between section (3) and the inner wall of barrel (4), so that when the projectile (shell (1) and propelling cage (2)) exits the barrel (4), the pressure drop in annular gap (5) commences earlier in time than inside section (3). The inner wall of section (3) is thus subjected to the pressure differential generated and the segments from the multi-subdivided propelling-cage (2) and section (3) carry out a movement perpendicular to the longitudinal axis of projectile (1) - (separation of the propelling-cage (2) from the projectile (1)). USE/ADVANTAGE - The arrangement can be used for a subcaliber propelling-cage projectile with gas-differential operated propelling-cage separation. The projectile is subjected to no or very minor interfering forces during the separation process of propelling-cage from the projectile, thus increasing the chance of hitting the target.

Description

In the "sub-caliber sabot projectile with differential gas actuated Sabot separation "is a wing-stabilized lower potash upper floor (with "caliber" becomes the outside in weapon and ammunition technology diameter of bullets and the inside diameter of launch tubes be draws) from a smooth launch tube (the tube has no draws inside and fields) is fired. The stabilization of such projectiles on the Trajectory takes place through the tail wings. The sealing of the projectile in the launch tube against the cargo space is generated by the sabot. This is divided into several segments and is used in the launch, after Storey exit, separated from the missile. While the missile is on the sabot segments hit the specified trajectory in different directions and at much shorter distances from the pipe mouth on the floor.

This floor construction is not new. Such bullets have so far and z. Currently manufactured in large numbers. The disadvantage of this contruct tion is that the separation process of the sabot segments from the missile, after the floor exit, is not always trouble-free. The separation process is determined by the air resistance in the air funnel, which is at the front of the sabot (with the base is arranged forward), initiated and by the flow resisted the escaping combustion at the rear of the sabot gases supported. It often happens that the separation of the sabot segments from the missile are not symmetrical and thereby disturbing forces take effect on the missile and the hit performance of the missile affect. In the case of the spin-stabilized sub-caliber bullets, that is Separation of sabot and missile can be achieved easily because here the centrifugal force induced by the projectile twist into the projectile for the separation can be used. The hit performance of drallstabi Sub-caliber bullets (APDS bullets) are usually better than with wing-stabilized sub-caliber bullets.

The object of the invention is to provide a wing-stabilized sub-caliber sabot projectile in which during the separation process of the sabot from the flight floor - after the projectile exit - no or only slight interference forces on the flight floor become effective and the performance is thereby increased.

According to the invention, this object is achieved as follows:

At the bottom of the sabot divided into several segments is in the back a hollow cylindrical extension attached. The outside The diameter of the approach is designed to be slightly smaller than the inside diameter of the launch tube, causing a between the launch tube and approach Annular gap arises. When the propellant powder ignites, they flow hot combustion gases both in the interior of the approach and in the Annular gap and drive the projectile (sabot plus flight projectile) out of the Launch tube. As soon as the trailing edge of the sabot meets the mouth of the Ab shot tube has passed, there is a pressure drop in the annular gap, because the annular gap is dimensioned in the radial direction only so large that when the propellant charge burns up only as much combustion gas in the annular gap flows in that a between the inside and outside of the approach Approaching pressure equalization takes place, so the wall thickness of the approach can be kept small. Because wall thickness means weight, and everyone The percentage by weight of the sabot reduces the effective weight of the missile. The pressure drop in the annular gap increases continuously until the rear edge of the Approach passes the mouth of the launch tube. But since inside the Approach that combustion gases cannot flow off so quickly arises a differential gas pressure to the annular gap, which (after the Notungsringes) drives the sabot segments outwards and thus separates from the missile. Only one game of forces takes place during the separation process between the mouth of the launch tube and the sabot segment, but not with the missile.

In a further embodiment of the projectile according to the invention can lower end of the approach, outside, stabilizing ribs, the outer Be limit corresponds approximately to the caliber of the launch tube, be arranged. This measure ensures that the separation of the sabot segments beginning first.

According to a further feature of the invention, the centering ribs can be poses. When flowing through the combustion gases, the propellant caged an angular momentum, the possible inaccuracies in the construction Compensates segments and the detachment of the segments from the missile sym can be done metrically.  

According to an additional feature of the invention, the circumferential grooves have an angle of increase to the radial plane on the missile. The tangential component of the reaction acting on the missile when fired force initiates an angular momentum on the missile and sabot. By this constructive interpretation will be the disturbing forces on the missile Separation process further reduced.

According to a further feature of the invention, a front of the sabot can be funnel-shaped spoiler can be arranged, the separation process by the Air resistance supported.

Advantage: Due to the trouble-free or low-noise separation process from The missile and sabot will improve the hit performance.

The projectile according to the invention is exemplified in Fig. 1 and Fig. 2 ver.

Fig. 1 side view of the projectile 1 and sabot 2

Fig. 2 side view of the projectile 1 and sabot 2.

To Fig. 1

Here the flight floor 1 with sabot 2 is shown in section in Seitenan view. The projectile is in the firing position (cartridge chamber).

To Fig. 2

Here, too, the missile 1 with sabot 2 is shown in a side view. The missile 1 and sabot 2 have already emerged from the mouth of the launch tube 4 , while the approach 3 is partly in the launch tube 4 . The approach 3 is provided with centering ribs 6 . The grooves 9 rise in the axial direction at an angle 8 . At the front end of the sabot 2 , a funnel-shaped spoiler 10 is attached. The sabot 2 is drawn in half section.

List of reference numbers:

1 - Missile
2 - sabot or sabot segment
3 - approach
4 - launch tube
5 - annular gap
6 - centering rib
7 - Angle of attack of the rib
8 - pitch angle of the groove
9 - groove
10 - funnel spoiler
11 - propellant charge case
12 - propellant powder
13 - gag groove
14 - sealing ring
15 - tail unit

Claims (5)

1. "Sub-caliber sabot projectile with differential gas pressure-operated sabot separation" consisting of the missile ( 1 ) and the sabot ( 2 ), characterized in that in the rear extension of the sabot ( 2 ) a hollow cylindrical extension ( 3 ) is attached, that the approach ( 3 ) has a smaller outer diameter than the sabot ( 2 ) and also as the inner diameter of the launch tube ( 4 ), whereby an annular gap ( 5 ) is formed between the approach ( 3 ) and the inner wall of the launch tube ( 4 ) that at the exit of the projectile according to the invention (missile ( 1 ) and sabot ( 2 )) from the mouth of the launch tube ( 4 ), the drop in the muzzle gas pressure in the annular gap ( 5 ) starts earlier than within the approach ( 3 ) that the resultant Differential gas pressure acts on the inner wall of the approach ( 3 ) and the segments from the multi-sectioned drive cage ( 2 ) and approach ( 3 ) reduce movement real projectile to the longitudinal axis of the aircraft (1) perform (separation of the sabot (2) of the projectile (1)). 2. sub-caliber sabot projectile according to claim 1, characterized in that at the rear end of the neck ( 3 ) outwardly facing centering ribs ( 6 ) are attached, the outer boundary surfaces are approximately at the level of the inner diameter of the launch tube ( 4 ). 3. sabot projectile according to claim 2, characterized in that the centering ribs ( 6 ) are made at an angle ( 7 ) to the radial plane. 4. sabot projectile according to claim 1 to 3, characterized in that the circumferential grooves ( 9 ) on the missile ( 1 ) and sabot ( 2 ), for fixing these two parts in the axial direction, have an increase angle ( 8 ) to the radial plane. 5. sabot projectile according to claim 1 to 4, characterized in that a funnel spoiler ( 10 ) is introduced at the front end of the sabot ( 2 ).