DE2330045A1 - MISSILE FOR FIRE AND PROPERTY REFLECTIVE MATERIAL - Google Patents

Description

B 386

A-8

AB Bofors, Bofors, Sweden

Missile to fire and spread reflective

material

The invention relates to a missile for firing and dispersing reflective material, in particular Consists of cut pieces of fiber or thread that allow a radar echo after firing and spreading target.

The rocket consists of a rear propellant part with a rocket motor and a rocket head, which is to be fired and Contains material to be disseminated. The rocket head consists of a cylindrical jacket, the front end of which with is equipped with a tip cone.

There are rockets of this type known in which the propagation of the reflective material init. With the help of a spreading or stray charge, when it spreads either the jacket surrounding the material

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blows away or drifts away or, after removing the tip cone, expels the material from the jacket forwards.

With these known rockets, the problem arises that the re ± \ Lektierende material simultaneously and instantaneously and is wholly ejected, resulting in unsatisfactory dispersion. To achieve the required radar echo, it is also necessary to progressively move the material along

of a section of the missile trajectory, and this is not possible with the known missiles.

A further difficulty with scattering is that the individual particles of the reflective material with a must be distributed at a suitable distance from each other because this to achieve the best possible reflection effect important is.

The identified difficulties are now according to the Invention eliminated by means of a missile of the type mentioned, which is characterized in that the jacket with the Missile body is connected by means of a locking mechanism which is releasable and arranged such that it with Using a separating charge is ejected forward and then exposes the material so that it is under the influence of the Air flow around the rocket is distributed,

The advantage of this arrangement is that the re-

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inflected material not all at once but in its entirety is progressively dispersed along a reasonable portion of the missile trajectory, and this becomes achieved that the material after blowing away the jacket surrounding it under the influence of the air flow of the rocket is spread. In this way, a special stray charge can be dispensed with for this purpose.

In the drawing, a preferred embodiment is the Invention shown for example.

Fig. 1 is a side view of the missile according to the invention;

Fig. 2 is a partially cut-away side view of the Hook head;

Fig. 3 is a longitudinal section through the when spreading the reflective material part of the missile to be blown away;

Fig. 4 is a section through a locking device for securing the air to be blown away before spreading Part on a larger scale;

Fig. 5 is a top plan view of one of the separator disks used between batches of the reflective Materials are arranged; and

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Figure 6 is a top plan view of a support plate disposed in the missile head.

As can be seen from Fig. 1, the rocket has a rear propulsion part 1, which contains a rocket motor, and a Missile head 2 containing the reflective material to be propagated. The driving part 1 does not form part of the invention, and a detailed description of it is therefore not necessary.

The rocket head shown in Fig. 2 and 3 has an elongated cylindrical jacket 3, the front end with a Point cone 4 is provided »At the joint between the jacket 3 and the point cone 4 there is a fastening plate 5. In the middle of the plate 5, an inner tube 7 is welded, which is coaxial to the cylindrical shell 3 after extends to the rear and is practically the same length as this one. The tube 7 is provided with openings 9.

The rear end of the jacket 3 is on the periphery of a mounting plate 10 mounted, 'which are screwed on with threaded holes the plate is attached to the missile body. The rocket head is by means of a sealing ring 11 between the jacket 3 and the plate 10 sealed, in the center of which a forward outer tube 12 is screwed, which surrounds the inner tube 7 and has essentially the same length as this. Located between the two tubes a sealing ring 13 »which is in a groove of the in-

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nenrohres 7 is mounted. At the front end of the outer tube 12, a support plate Ik is mounted, which is guided in relation to the fastening plate 5 by means of a pin 15. The plate 14 is intended to prevent the reflective material located behind the plate from migrating forwards when the jacket is blown away, and the plate is penetrated by holes 14a (FIG. 6). By choosing different dimensions for the perforations in the plate 14, different scattering times and correspondingly different degrees of propagation of the reflective material can be achieved. In the space between the outer tube 12 and the housing 3, the reflective material is mounted in the form of a stack consisting of batches 1 ^, each of which has the shape of a hollow cylinder. The stack is enclosed in four plate segments 16a which protect the individual batches during separation of the rocket and prevent scattering of the reflective material before the separation is complete. Separating disks 17, one of which is shown in plan view in FIG. 5, are arranged between the individual batches 16 of the reflective material. As can be seen from this figure, the disks 17 are provided with four cutouts 18 evenly distributed over the circumference. In addition, the disks are divided into two equal parts on a line 19 along a diameter. The cutouts 18 allow the envelope, for example made of paper, of the individual batches 16 to be cut open. These cuts between the segments 17 are made before the casing 3 is assembled.

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Figure 4 shows a locking mechanism designed to hold the blow-away jacket on the hook prior to the scattering of the reflective material, and is released by the action of a separating charge so that the jacket can be driven away when the material is to be scattered . The jacket 3 with the tip cone k is held in its position before firing by means of the locking mechanism with the aid of the front fastening plate 5 and the inner tube 7, in that the locking mechanism in the locked position forms a connecting element between the inner tube 7 and the rear fastening plate 10. The locking mechanism has an outer sleeve 20 which is fastened to the inner tube 7 by screwing its front end into it. In the sleeve 20, an inner sleeve 21 is slidably arranged, in the front end of which a locking piston 22 is inserted. The inner sleeve 21 is held in its position in the outer sleeve 20 by means of a radially outwardly directed collar Zk which, in the position shown, is in contact with the front end of the outer sleeve 20 and also forms a contact surface for the rear end of a compression spring 25 the front end is supported on an abutment disk 26, which in turn is supported on a step in the inner tube 7. The sleeve 21 has axially directed gas channels in the form of slots 23.

In the position shown, the locking piston 22 is against axial movement with respect to the inner sleeve 21

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held by locking balls 27 which are inserted into radial openings in the sleeve 21 and in a circumferential groove 28 engage in piston 22. In the front end of the piston 22 there is an axial recess 29, the Function is described in more detail below.

The rear end of the outer sleeve 20 is provided with radial openings into which locking balls 32 are inserted, which are inserted into an inner circumferential groove in a fastening? engage ring 33 which is pressed into the mounting plate 10. A nut 35 is screwed onto the hub part of the plate 10 and forms a holder for a separating charge J6 .

After the missile is fired, the separating charge 36 is assisted with a predetermined reasonable time delay ignited an ignition device, not shown. The piston 22 is due to the gas pressure prevailing behind it together with the sliding inner sleeve 21 under tiberwin-. application of the force of the spring 25 pushed forward. When the step 20 on the rear part of the inner sleeve 21 on the balls 32 has passed, these can move radially inward and separate from the locking ring 33, so that the Locking between the outer sleeve 20 and the ring 33 is released. The inner sleeve 7 and consequently also the jacket 3 can then move forward with respect to the outer tube 12 and the rear propellant portion of the missile.

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When the inner sleeve 21 continues to move forward with respect to the sleeve 20, the balls 27 occur at the front end the outer sleeve 20 over. When this is done, the balls 27 can move radially outward and off the groove 28 in the piston 22. In this way the piston is released and continues its forward movement through the Tube 7 continues under the action of the gas pressure. When the rear end of the piston 22 at the rear end of the gas channels 23 has passed in the sleeve 21, then the gas can flow through these gas channels past the piston 22, during the Piston 22 is still guided in sleeve 21. Through the gas channels 23, however, the exit speed of the Piston 22 is limited when leaving the sleeve 21. Since the piston 22 is provided with the recess 29, its front end is more easily deformable, so that the kinetic energy of the piston when it hits the plate 5 during the deformation of the front part of the piston is used up.

When the piston 22 completely leaves the inner sleeve 21, a continuous gas channel is opened through this sleeve and the tube 7. Under the influence of the gas pressure, the inner tube 7 is pushed forward, and the jacket 3 is then also displaced forward with the tip cone k. The rear end of the shell 3 then leaves the plate 10, and as the shell moves forward, the plate segments 16a are released.

When the inner tube 7 has moved so far forward,

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that the openings 9 have passed the end of the outer tube 12, ketone gas flow out through these openings. In this way it is prevented that a partial vacuum is created in the space between the plates 5 and Ik when this space is enlarged by the blowing off of the jacket by the plate 5 moving forward while the plate 14 is that shown in FIG Maintains position. When the jacket 3 is thrown off and the plate segments 16a are completely exposed, they fall off quickly so that the reflective material is entirely released. Through the one around the rocket and through the openings 1 ka. The material is continuously scattered in the air stream flowing through the plate. Since the cutting disks 17 are divided diametrically into two equal parts, they fall off the pipe without hindering the spread of the material.

Fire tests have shown that with a missile according to the invention described, a radar echo with a broadened shape can be achieved at the same time and to the extent that the ⁺ reflective particles in the scattered material are improved.

After what has been said, the person skilled in the art recognizes the possibility of manifold modifications without deviating from the concept of the invention.

+ Distribution of the _o, _

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Claims (5)

Pat exempt 1. / Missile for firing and scattering reflective Material with a hook body, in the rear part of which is a rocket motor *, and with a missile head containing the reflective material and with a center of a separating charge (36) jacket that can be blown away from the rocket body (3) is equipped, characterized in that the jacket (3) is connected to the missile body by means of a locking mechanism which is activated by the action of the Gas pressure can be released from a separating charge. 2. rocket according to claim 1, characterized in that the Jacket (3) is connected to the locking mechanism by means of a coaxial tube (7) which has a gas channel between the separating charge (jb) and the front part of the Mantle forms. 3. Missile according to claim 2, characterized in that the locking mechanism includes a valve member (22), which closes the gas duct when the locking mechanism is in the closed position and is arranged in this way is that it opens the gas channel when the locking mechanism is released. 4. missile according to one of claims 1 to 3 »thereby ge -10- 309851/0532 indicates that the locking mechanism is ever a set of locking balls (32) for locking of the jacket (3) 5 and (27) for locking the valve member (22). 5. Missile according to claim 1, characterized in that the locking mechanism by means of a spring (25) can be biased in its locked position. -11- 309851/0532 Blank page