RU2242703C1 - Turbojet shell for set-up of thermal targets - Google Patents

Abstract

FIELD: military equipment, mainly associated with protection of objects, for example, of surface ships against shells with homing heads by oncoming formation of interference clouds.

SUBSTANCE: the shell has a turbojet engine, nose cone with a useful load and a fuse rigidly interconnected. The fuse is provided with an ignition system, and the nose cone-with mechanisms of destruction of its inner wall, protection of the useful load against stretches, ignition and ejection of the useful load, which contain successively installed charges of fuse cut-off, ignition and ejection of the useful load, which contain successively installed charges of fuse cut-off, ignition and ejection of the useful load. The shell is made for an axial spin.

EFFECT: reduced time of set-up of the cloud of thermal targets.

5 cl, 1 dwg

Description

The present invention relates to the field of military equipment, mainly associated with the protection of objects, such as surface ships, from shells with homing heads by the counter formation of jamming clouds.

Known smoke-generating projectile described in US patent 5454324 (CL 6 C 06 D 3/00, 102/334, decl. 10/22/1993, figure 2), comprising a housing, at least two smoke bombs placed in the sleeves emitted by the piston under the influence of propellant gases, the axial channels of the smoke bombs form the central hollow axial channel of the projectile, in which moderators and a ring are installed to temporarily connect the bombs when they are ejected from the projectile; in the bottom of the projectile are sequentially installed blocking, electrical contact, an ignitor containing a propelling charge, on which the piston rests. The other end of the shell body is closed by a dropable lid, under which a casing is installed, containing a dispersed powder charge mixed with brass powder and supported by a fuse and a compressed spring that softens the mutual impacts of the casing and shells.

The known device operates as follows.

The defense system includes a trigger signal. The igniter ignites a propelling charge. The formed gases press on the piston, cut off the safety checks, drop the cover, throw the shells and casing out of the case. At the same time, through the axial hole in the piston, gases penetrate into the central axial channel of the projectile, igniting moderators and a fuse to ignite the charge of gunpowder in the casing. Sleeves thrown out of the casing and the casing move along with it along the trajectory; the spring expands, discarding the casing and slowing down the movement of the liners. A fuse ignites a powder charge. From the impact on the ground, the liners open, throwing out the burning pyro-composition of smoke bombs. The dispersion of the liners does not exceed 15 m, forming overlapping smoke screens.

The disadvantages of the known projectile is that it is intended only for the surface formation of smoke screens and the latter cover almost only their launcher within 20 m from it.

Closest to the proposed projectile is the device described in US patent 4791870 (CL 4 F 42 B 4/26, 102-342, application 04.04.1984 g), including an external launch tube, closed at one end with a dropable cap. The pipe has a payload in the form of a stack of packages of pyrotechnic elements having a main charge. A payload ejection mechanism is provided. This mechanism includes a system of ignition, separation and discharge of the load: the upper and lower igniters connected to the electrical contact, as well as igniters and moderators installed in the central axial channel with propelling charges located under each package. Moreover, the central axial channel of the projectile is perforated, and the upper and lower igniters are connected by a metal foil mounted on the inner wall of the projectile body. Each package is an annular pyrolysis placed in a plastic cup-case having a bottom with a main protrusion and closed with a locking cap; in the bottom of the housing and the cap there are axial holes connected by a tube to the holes in which the moderator is located, as well as a tube with an igniter.

The known device operates as follows.

The inrush current acts on the upper electric igniter, igniting the moderator and the igniter of the upper package. On the igniter tube, the force of fire is transmitted to the propellant charge of the upper package. As a result, the upper package is ejected from the launch tube, while the lid flies off. After that, after a certain period of time, the contents of the discarded packet are ignited, discarding the locking cap. The propellant charge of the upper package ignites the moderator and the ignitor of the next package, then its propellant is ignited, ejecting the package from the launch tube, etc. until the last package. Moreover, the contents of the packages may have a different composition. Thus, in air at a certain height, a protective screen of a given size and density is formed.

The disadvantages of the known device is that the packets are ejected forward along the flight path of the device, therefore, it flies through the cloud of burning pyro-composition created by it, which violates the uniformity of the latter, and partial precipitation of pyro-composition particles onto the outer walls of the flying device is possible.

The present invention is aimed at eliminating these disadvantages by setting a cloud of thermal targets in a short period of time to effectively protect a surface object using a turbojet projectile.

The task is carried out using the claimed turbojet projectile for setting thermal targets, including a turbojet engine, a payload head and a fuse rigidly interconnected, the fuse equipped with an ignition system, the head part with mechanisms to destroy its internal wall, protect the payload from longitudinal deformation, ignition, and payload ejection, which contain sequentially set fuse cut-off charges, ignition and the release of the payload; moreover, the mechanism of ignition and discharge of the payload is made in the form of a disk with moderators installed in it and an igniter charge placed in a glass or a cup with a lid mounted on the disk. The mechanism of destruction of the wall of the head part is made in the form of a disk fuse ignition system structurally connected to a cup with a misfire charge and a cup with an ignition charge mounted on it, from the load side, ring and crackers installed in thinning the inner wall of the head part. The mechanism for protecting the payload from longitudinal deformations is made in the form of two half-holes, pipes resting on disks with moderators. Moreover, the projectile is made with the possibility of axial rotation.

The pyrotechnic connection of the fuse ignition system, the mechanisms of destruction of the head wall, ignition and ejection of the payload ensures instant transmission of the force of fire and the operation of the ejection mechanism, which is structurally more reliable than described in the prototype.

Implementation of the mechanisms of destruction of the head wall, ignition and discharge of the load, the form of the load package and the rigid connection of the main structural elements of the rotating shell guarantee the reliability and completeness of the ejection of the payload.

The shape of the payload packaging in combination with the above mechanisms ensures its uniform combustion and, accordingly, the setting of thermal targets of the required dimensions at the required time.

The inventive projectile contains a new design scheme - the mechanisms of destruction of the inner wall of the head part, protection of the payload, ignition and ejection of the payload from the projectile, which we have not identified in other known technical solutions and fall under the criterion of "inventive step".

The drawing shows a longitudinal section of the head of the projectile (without engine), along the axis of symmetry.

The proposed turbojet for setting thermal targets contains the following main elements: fuse 1, the head part 2 and a turbojet engine. In the fuse 1, an ignition system is installed - a remote tube, and the head part 2 contains a mechanism for destroying its walls, a mechanism for protecting the payload from longitudinal deformations, and a mechanism for igniting and ejecting the payload. The destruction mechanism of the wall of the head part 2 consists of a disk 3 with a cup 6 with an ignition charge 7 installed on it from the load side, and a cup 4 with a cut-off charge 5, ring 8, crackers 9 installed in thinning 10 of the inner wall of the head part from the fuse side 2. The mechanism for protecting the payload from longitudinal deformations consists of two half holes 11, pipes 12, supported by disks 13. The mechanism of ignition and discharge of the payload is made in the form of a disk 13 with moderators 14 and an igniter charge 15 or 16, placed in the stack 17 or cup 18, mounted on the disc 13. Useful stacked load in the tipping paper, forming a central channel.

A turbojet projectile for setting thermal targets operates as follows.

In the active section of the flight path when the projectile reaches a certain speed, the trigger of the fuse 1 activates, including its clock mechanism, and the countdown of the set time begins, after which the fuse 1 fires. The resulting force of fire flows around the cup 4, passes through the holes 19 in the disk 3 and ignites the charge 7. The powder gases generated by the actuation of the charge 7 ignite the charge 5 through the hole 20, the moderators 14 installed in the first (from fuse 1) disk 13, and the payload in the half-holes 11. The force from the pressure of the powder gases generated from the combustion of the charge 5, through the disk 3 and crackers 9 is transmitted to thinning 10 of the inner wall of the head part 2, cutting it off. After the delay time, the moderators 14 are activated and ignite the first charge 15 of the ignition mechanism. The pressure of the powder gases generated during the combustion of the charge 15, half-holes 11 are ejected from the projectile. At the same time, the powder gases generated during the combustion of the charge 15 ignite the moderators 14 installed in the second disk 13 and ignite the load placed in the pipes 12. Similarly, the pipes 12 are ejected in pairs with a useful load at a certain interval. Under the action of centrifugal forces and an incoming air stream, half-holders and pipes ejected from the projectile are freed from the payload, which is scattered in the air, forming local clouds, consisting of decreasing burning elements that form clouds of different colors of smoke when burning, which have the corresponding characteristics.

The proposed design of a turbojet for setting thermal targets ensures due to the expansion of the payload in the air, both in the radial direction, a sequential with the established deceleration, ejection of the payload and forward in the longitudinal direction (along the flight path) and provides the required cloud length. Sectional discharge of the load allows you to create combined thermal goals.

The specified target characteristics created by the proposed turbojet projectile for serial products and foreign analogues are achieved over a longer period.

Claims (5)

1. A turbojet projectile for setting thermal targets, comprising a turbojet engine, a payload head and a fuse rigidly interconnected, the fuse equipped with an ignition system, and the head with a central channel, ignition and payload ejection mechanisms, characterized in that the projectile is additionally equipped with mechanisms for destroying the wall of the head part, as well as protecting the payload from longitudinal deformations and is made with the possibility of axial rotation. 2. The projectile according to claim 1, characterized in that the ignition system installed in the fuse and the mechanisms for destroying the wall of the head part, as well as the ignition and ejection of the payload installed in the fuse, contain sequentially established charges for cutting, igniting and ejecting the payload. 3. The shell according to claim 1 or 2, characterized in that the destruction mechanism of the head wall includes a disk structurally connected to the fuse ignition system with a cup mounted on it with a cut-off charge and a cup with an ignition charge on the load side, a ring and crackers installed in thinning of the inner wall of the head. 4. The projectile according to claim 1 or 2, characterized in that the mechanism of ignition and discharge of the payload is made in the form of a disk with moderators and an igniter charge placed in a glass or cup with a lid mounted on the disk. 5. The projectile according to claim 4, characterized in that the mechanism for protecting the payload from longitudinal deformations is made of two semi-holes, pipes resting on disks with moderators.