KR100796706B1 - Artillery projectile comprising an interchangeable payload - Google Patents

Abstract

An inexpensive artillery munition of great range and acquisition accuracy for universal use while maintaining the external-ballistic coefficients is afforded when inserted between a standardized tail section (12) and also standardized tip section (13) is a load section (14) which connects the two contours of said sections together and which can be equipped with very different warheads which in particular are optimized against hard targets. For launch into an aerodynamically stabilized ballistic trajectory the tail section (12) is provided with super-calibre stabilization fins (17).

Description

Artillery Projector with Interchangeable Payload {ARTILLERY PROJECTILE COMPRISING AN INTERCHANGEABLE PAYLOAD}

The present invention relates to an artillery projectile as described in the preamble of claim 1.

A common device is known as the artillery rocket system MLRS 1/2. Its continuous rocket casing can be equipped with a canister from the tail while the tail is still open behind a nose cone fitted with a time fuse. The canister is equipped with a distribution unit for the discharge of other armor-piercing active bodies such as, for example, small bombs or armored explosives. Behind its axial stack of the canister, the rocket is equipped with its motor, the tail region of the rocket's housing is equipped with a control rudder, the control rudder can be deployed and parallel to the system axis. Is curved. However, the flexibility of such a system is limited because the rocket casing is one part from the nose cone to the disconnection position for the connection of the disposable rocket motor. The maneuverability of such artillery rockets is only moderately good, because the motors that operate for only a short time after leaving the launch barrel will cause the rocket to be subjected to high levels of acceleration with a relatively flat trajectory. Termination of purely time-dependent missions by timed fuses in the nose cone does not allow pin-point accuracy predictions for target acquisition, so the timed fuse responds to the motor burned for a long time at that time. When exploded and disposed, only the distracted active fuselage develops meaninglessly.
A device comparable to the above device is provided with a carrier for mounting various types of sub-projectiles to be distributed between a head portion forming the front end of the carrier and a rear tail portion which may be provided with a tail control surface assembly and which may have a drive. 08 796 A1. The carrier itself is formed integrally with its head and tail, and adaptation to the different sub-projectiles to be distributed is achieved by intervening in the separating wall internal parts of the carrier. The interchange of carriers to launch different payloads has not been considered. It is not affected by the use of the carrier's flight dynamics in different sub-projectiles.
A completely different kind of problem is to avoid the high peak of the sea missile's launch curve that will be fired from a submarine or seaship in order to keep the launch curve below the enemy's radar range and thus not leak the launch coordinates. , 364, 530 are concerned with avoiding high peaks of such firing curves. This is achieved by the fact that the thrust vector control module is fitted to the rear of the rocket already present for launch, which converts a rather vertical trajectory into a roughly horizontal trajectory immediately after lift-off. After increasing the inflow velocity in such a roughly horizontal trajectory, the rocket guidance is performed in a conventional manner with the control surface in the middle or load range of the rocket and the tail pin in the rocket motor in front of the booster to be discarded. . As in the prior art, no mention is made of exchanges according to payload duty or true interchange of overall payload selection.
US Pat. No. 4,889,956 also does not relate to the optimization of the area of the projectile payload section. Rather, the screw means between the warhead and the much longer rocket fuselage placed behind the warhead opens, and the module is screwed into it, where it has been described that the rocket trajectory can be altered by transversely directed pulses. The module, screwed into the intermediate position, extends the total length of the rocket and thus affects its aerodynamic properties, and it has never been referenced to affect the area where the warhead as payload is placed or to truly optimize the area.

The technical object of the present invention is to provide a system that is more open in terms of warhead exchangeability and is distinguished by a precisely targeted supply of payloads, in particular despite large and large ranges. .

According to the present invention, such an object is that according to the combination of features in the independent claims, the payload space is the complete center of the artillery projectile which is ballistically fired and, after peaking, enters the controlled gliding flight. The accommodating part remains the same for all payloads and the standard tail which immediately determines the external trajectory immediately after leaving the barrel and the fuselage wing or nose-mounted control surface for controllable gliding also remains the same for all payloads. And a standard tip provided to a navigation device, such as inertial and / or satellite navigation, for payload supply of ultimately possible pinpoint accuracy.

The centrally inserted interchangeably between these two standard ends is at least one warhead as a target tracking submunition, a bundle of bombs to be dispersed, and a high energy warhead or post-acceleration in its hollow cylindrical circumferential casing. It has a post-acceleratable bar penetrator. Properly produced projectile casings in the center are flange-mounted on the standard bottom section and the standard tip, for example connected together by radial pins or a kind of bayonet coupling. In any case, the projectile has a single air frame for several different payloads, and for that reason, due to the unchanged external trajectory, there is no problem with firing from the turret regardless of the payload to be fired upon firing from the turret. Are treated.

Further details, developments, and advantages of the structure according to the invention, in addition to the appended claims, are directed to preferred embodiments of the structure according to the invention, which are schematically illustrated in the drawings, which are not practical scales and are not indispensable. Note the following description.

1 is an axial longitudinal cross-sectional view of a gliding projectile with an exchangeable payload portion between standard ends and an enhanced range for ballistic firing.

1 shows in cross section a projectile 11 projected from an artillery cannon, ie ballistically, which is divided into three parts in the axial direction, namely the tail 12 and the tip ( 13) has a load section 14 that can be inserted between. The rod 14 is thus no longer a loadable load space in the continuous projectile casing, but together with its wall 15 implements a fully interchangeable central area of the projectile 11.

As described above, the payload space 16 in the center of the projectile 11 or in the wall 15 of the rod 14 is subjected to attacks on a variety of warheads, in particular hard-armoured targets. Warheads may be mounted. Properly produced rod portion 14 may be mounted at the completion stage together with tail 12 and tip 13 to complete projectile 11.

The projectile 11 is equipped with a stabilization fin 17, which is firmly oriented in a parallel relationship with the axis under spring bias until fired from the barrel, eg steel It includes a sheet and is applied to the cylindrical outer peripheral surface of the tail (12). The cup-shaped cover 18 is secured from the rear with respect to the tail 12 with the stabilizing pin 17 surrounding the tail so that the stabilizing pins are held in a slightly sub-caliber launch position. Is pressed. The hollow cylindrical annular wall 19 prevents the stabilization pin 17 applied to the cylindrical surface of the tail 12 from developing.

A guide band 21 extending around is inserted into the radially shallow axially wide groove 20 provided in the outer circumferential surface of the annular wall 19. It is designed as a so-called slip-through guide band 21, ie it is a natural value of the stabilization spin generated by the barrel's rifle when the projectile is fired from the barrel. in order to reduce it to about 10% of its value, it is not non-rotatingly connected to the projectile 11, since the projectile 11 is not intended to fly in a spin-stabilized mode after leaving the entrance of the barrel, i.e. This is because it was then intended to be aerodynamically stabilized by a fin 17 extending radially outwardly. In principle, in order to reduce such spins in the barrel, the annular wall 19 can be rotated relative to the projectile 11, ie with respect to the tail 12 of the projectile, but with the annular wall 19. It is structurally easy for the cover 18 to be fixed non-rotatively to the tail and the guide band 21 to slip-through in the groove 20.

When the tail 12 leaves the barrel opening, the component of the dynamic pressure acting on the annular wall 19 in a parallel relationship with the lower suction effect behind the cover 18 and the axis of the cover is that the annular wall 19 Axially moved backwards and finally the annular wall 19 is completely peeled off from the tail 12 so as to radially extend the stabilizing pin 17 which still leans against the periphery of the tail 12. Release it. Such a spreading effect can be realized for an axis parallel to the projectile axis under the effect of centrifugal forces, but as already mentioned, it is more appropriate that the stabilizing pin 17 is made from a spring plate, the spring plate each having a tail along the edge. The length of the projectile from the state of being firmly connected to the part 12 (riveted as an example), supported by an elastic spring and, when released, held in contact with the tail 12 by the annular wall 19. It is released to a position projecting radially in a curved shape parallel to the direction axis 22.

Like the tail 12, the tip 13 is also designed as a standard regardless of the shape of the rod 14. Tip portion 13 includes a wing or nose-mounted gliding wing 23 protruding from the outside of nose cone 24 by a pivoting motion as soon as projectile 11 passes through the apogee on its initial ballistic launch trajectory, for example. Is provided. The wing 23 acts for both the gliding step and the steering towards the target. Initially, there is a transition from the ballistic descent path behind the vertex to an extended controlled gliding, in such a way that a correspondingly larger range is achieved as a result of the path of significantly shallow descent. At the same time, the projectile is steered towards a predetermined target point by an inertial or satellite navigation system. The flight guidance is carried out by the main unit of the nose cone 24 by the steering unit 25 which is operated by the navigation device 26 so that the projectile 11 is displaced from the shallow gliding to the steep attack trajectory just before flying on the predetermined target point. By the pivoting movement of the gliding wing 23 from its neutral position parallel to the generatrix. Finally, just above the target, the discharge device 28 is operated by a fuse 27 acting in a distance-oriented relationship with respect to the enclosing area, from the steep attack trajectory, for example, so that the tip portion 13 ) Is separated from the rod portion 14 and the payload space 16 is emptied by the position of separation to a more defined target area.

Thus, in accordance with the present invention, in the aerodynamically stabilized gliding projectile 11, a standardized tail 12 initially determining the external trajectory and also a standardized tip 13 determining the range and accuracy in the final stage When the rod portion 14 is inserted between the two outer sections and can be equipped with a variety of warheads optimized for particularly solid targets, it is always variable under the same aerodynamic conditions in maintaining external ballistic projectile coefficients. In terms of payload, inexpensive final stage steerable artillery delivery with significantly increased range and capture accuracy for universal use is possible. For launch into the aerodynamically stable ballistic trajectory, the tail 12 is provided with a super-caliber stabilizing pin 17, which is applied to the outer circumferential surface of the tail 12 within the barrel. In the firing position an annular wall 19 is joined thereon, which is provided with a slip-through guide band 21 for initial reduction of spin while still in the barrel. Preferably, immediately after the peak of the trajectory trajectory, the nose-mounted gliding wing 23 extends from the tip 13 and, by the wing 23, by the steering unit 25, the descending path of the trajectory trajectory. To a larger range of shallow gliding paths are performed, and there is a steep descent from the shallow gliding path to a final target area closer to the target under navigation control, and the payload 14 loads the payload 14 into the predetermined target area. To supply.

The artillery projectiles of the present invention are more open in terms of warhead exchangeability and provide particularly large ranges and provide payloads exactly on target, despite large ranges.

Claims (9)

In artillery projectiles with interchangeable payloads, Within the projectile 11, a replaceable load section 14, on which various other payloads can be mounted, is arranged between the standardized tail 12 and the standardized tip 13 so that the tail An artillery projectile which interconnects the contours of the tip and the tip. The method of claim 1, An artillery projectile comprising a stabilization fin (17) in which the tail (12) extends radially in a super-caliber configuration with the bottom of the projectile (11). . The method of claim 2, The stabilizing pin 17 is attached to the outer circumferential surface of the tail 12 and the tail 12 is surrounded by an annular wall 19, the annular wall 19 firing from the barrel. Artillery projectile which is pulled rearward from the tail portion (12) of the projectile (11) parallel to the axis when the stabilization pin (17) is enabled for deployment. The method of claim 3, The annular wall (19) is an artillery projectile surrounded by a guide band (21). The method of claim 4, wherein The guide band (21) is mounted to a groove (20) extending around the annular wall (19), the guide band (21) is suitable for sliding controllable through the groove (20). The method according to any one of claims 3 to 5, The annular wall 19 is the wall of the cup-shaped cover 18, the cup-shaped cover 18 at the tail end with the stabilizing pin 17 folded against the wall of the cup-shaped cover 18. Artillery projectile being pulled into the tail (12). The method according to any one of claims 1 to 5, The tip portion 13 is a gun projectile is equipped with a gliding wing (23) that can extend from the appearance of a nose cone (ogive) (24). The method of claim 7, wherein A artillery projectile in which the navigation controlled steering unit (25) used in the fuselage canard gliding wing (23) is provided in the tip (13). The method according to any one of claims 1 to 5, A separating device 28 operable by a fuse 27 is provided in the tip 13 to open the discharge opening so that the connection between the rod 14 and the tip 13 is exploded and opened. Gun projectile provided.

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