EP0157421B1 - Smoke-producing projectile - Google Patents

Abstract

1. Smoke projectile, especially for shooting from launchers, with centrally arranged propellant charge (30, 77), consisting of a container (12) with smoke composition (13, 14, 15) present therein, as well as ignition charge (16, 97) and a contact head (11, 65, 70) with bridge igniter (79) connected with the container (12), delay charge (53, 96) and a collar (21), surrounding the contact head (11, 65, 70), preferably of polyamide, with contact rings (22, 23), characterized in that the contact head (11, 65, 70) has an assembly (32, 67, 72), including reception chamber (29) for the residue-free burnable propellant charge (30, 77) of nitrocellulose or nitroglycerol powder or blocks, on one end of which follows the delay charge (53, 96) and on its end lying opposite the delay charge (53, 96) are arranged concentric off-centre arranged nozzles and that the reception chamber (29) is enclosed by high-strength material.

Description

The invention relates to a mist launcher, in particular for firing from throwing cups with a centrally located propellant charge, consisting of a can with a mist set therein and an ignition charge and a contact head connected to the can with a bridge igniter, delay set and a sleeve surrounding the contact head, preferably made of polyamide. with contact rings. (See e.g. GB-A 2056632).

Such throwing bodies are fired from throwing cups (launchers) which are fastened to a tank or to another vehicle which is supposed to be able to change positions without being seen by the opponent. Using these smoke towers, a fog is generated very quickly, which takes away the opponent's view in a larger area. Since these missiles have to develop fog during the flight in order to reliably fulfill the camouflage purposes, such smoke towers are also referred to as rapid smoke towers.

These smoke projectors usually consist of a contact head with contact rings for the ignition of a propellant charge, with the aid of which the projectiles are expelled from the throwing cups. Such a smoke impact body has become known from DE-A 2908116. There, the propellant charge is enclosed in a room that is located in a contact head made of plastic. Black powder is conventionally used as the propellant charge in this case, as in other known smoke projectors. However, black powder does not burn residue-free, so the throwing cups have to be cleaned constantly to avoid corrosion of the walls of the cups by these residues. Corrosion would render the cups unusable.

In order to reduce the formation of residues, it has become known to increase the discharge pressure by means of a dam (see DE-A 2932921, there page 12, 2nd paragraph). The insulation consists of gas outlet windows and these rupture disks, which act as predetermined breaking points and, after ignition, open the way for the propellant gases.

Propellant charges that burn completely without leaving residues, e.g. Nitroglycerin or nitrocellulose cannot be used as a powder or in block form in such throwing bodies, since on the one hand a gas pressure of about 13.5 bar within 2 milliseconds must not be exceeded in the throwing cups and on the other hand the throwing bodies at the extremely high, about 10 times that occurring Pressures having value would be destroyed. In addition, such rupture discs do not reduce the expulsion pressure; after its destruction when the thrust is inserted, this acts in full on the throwing cup base, which is usually held with a spring ring.

The invention is therefore based on the object of improving smoke throwers of the type mentioned at the outset such that materials which burn completely without residues, such as nitrocellulose and nitroglycerin, as a powder or in block form, can be used as propellants while maintaining the required maximum firing pressure.

The object is achieved by a smoke throwing body with the features of claim 1. The contact heads are usually made of aluminum for weight and manufacturing reasons. However, this is unable to withstand the high explosion pressures of the propellant charges to be used according to the invention with acceptable wall thicknesses. Only by using the insert made of high-strength material, e.g. made of steel, it is possible to use nitrocellulose or nitroglycerin powder or blocks for the propellant charge.

Preferably, the contact head is made of aluminum or steel and the insert is made of high-strength steel, the insert being firmly connected to the contact head, e.g. screwed or pressed in excess. The contact head and the insert are preferably made in one piece and then made of high-strength steel. It would be advantageous to arrange the deceleration set in the contact head by means of a base plate and to connect it to the propellant charge.

According to a further preferred embodiment, the contact head is annular. Here, the insert passes through the contact head, the insert being screwed to a cover or threaded part, the cover or the threaded part carrying the deceleration set.

According to an advantageous embodiment of the invention, the insert can have a first cup-shaped part which is fastened in the contact head and a second threaded part which is fastened within the first part which carries a thread and is connected to the deceleration set.

The delay unit is preferably connected to the propellant unit via a bore, the delay unit being advantageously arranged in the second threaded part.

If the contact head is ring-shaped and the insert is screwed through the ring, the result is a particularly simple construction which also reduces the risk of propellant particles penetrating into threads and the risk of the propellant igniting during screwing.

The delay set and the ignition set can preferably be accommodated together, forming a unit, in a bore in a housing element designed as a threaded piece, the bore having a narrowed through opening. The deceleration set is located on the side of the hole facing the propellant charge. This has the advantage that an immediate and direct continuation of the ignition from the delay set to ignite with a too fast ignition of the fog set.

The housing piece for receiving the deceleration and ignition charge is preferably the second threaded part of the insert. As a result, the part which closes the cup-shaped or cup-shaped threaded part of the insert also becomes the carrier of the delay and ignition charge.

The delay set is preferably connected directly to the space for receiving the propellant set. This leads to an improved ignition of the delay set.

An advantageous embodiment of the invention consists in the fact that the nozzles from which the propellant gases flow out are cast with a synthetic resin, preferably with epoxy resin. This ensures that the pressure inside the room that receives the propellant initially reaches a certain value and can only flow out of the room after the epoxy resin has burned through. An advantageous embodiment consists in that the nozzles are additionally covered with a plate, preferably made of silicone rubber. This protects the epoxy resin from mechanical destruction.

At least three outwardly directed nozzles are preferably provided, which have a diameter of approximately 2 mm and / or a cross section of 2 mm ² , the gas space being able to comprise approximately 1.5 to 2 cm ³ . The nozzles are arranged on a circle which is larger than the diameter of the spacer mandrel arranged on the base of the throwing cup. The nozzles for generating a gas cone are preferably arranged in an inclined manner, wherein in a further embodiment the nozzle axes can also run at an angle to the axis of the smoke throwing body for generating a swirl. If a smaller number of nozzles is provided, asymmetrical movements of the smoke throwing body can occur, which negatively influences its flight stability. Preferably, the nozzle axes for generating a swirl should not run through the axis of the throwing body, since it is then possible to impart a swirl to the fog throwing body, which significantly increases flight stability.

Several advantageous effects result from the nozzles. On the one hand, the pressure in the throwing cup is reduced to the desired values and, on the other hand, the propellant pressure is reduced with a delay, so that the smoke throwing body is driven out - as if with a rocket motor - which can lead to more stable behavior and also greater ranges. It is also possible to influence the rate at which the deceleration charge burns up by adjusting the amount of propellant charge. Under the extremely high pressure of the propellant charge, which burns without residues, the burn-up of the (specified) deceleration charge is also accelerated, so that the ignition of the smoke set can now be brought forward to a point in time immediately after leaving the throwing cup or to an adjustable distance behind, whereby only the charge quantity of the Propellant needs to be adjusted. The delay includes a backup system that prevents the delay set from being blown out. Without this safeguard, the deceleration is blown out by the high pressure in the high-pressure section and the blowout process ignites the fog set directly (without delay) and already mists in the throwing cup. This fog process, which begins in the throw cup, contaminates the throw cup. Such problems are avoided by the features according to the invention, according to which the delay set and the ignition set for the fog set are accommodated in one housing part, the two being separated from one another only by an intermediate wall with a bore.

In order to avoid that the bridge igniter is driven out radially by the explosion of the propellant charge and jammed with the cup wall, it is proposed that the insert have a bore to the bridge igniter running laterally and transversely to the axis of the contact body, the diameter of which is smaller than that of the bridge igniter . The through opening of the bore is preferably significantly smaller than the diameter of the bridge igniter. Alternatively, it is possible to secure the bridge igniter with a steel screw connection.

The propellant charge is preferably designed as a star burner made of rocket fuel - preferably as a degressive minister burner. In this case, the star burner is preferably arranged at a distance from the bottom of the insert having the bores, the bridge igniter preferably being arranged in the interior of the star burner and the connecting leads to the igniter being led through the bores, the strengths of the connecting leads approximately corresponding to the diameter of the bores and wherein the bridge igniter is preferably arranged in the pot bottom of the area of the star burner in use and is suspended from the connecting lines. This makes it possible to ignite the bridge, i.e. in the specific case, inserting the primer into the interior of the propellant charge and then leading the connection lines out through the bores can be carried out particularly advantageously.

The propellant charge preferably consists of nitrocellulose or nitroglycerin powder as base components with a binder with degressive burnup, it being extruded or pressed.

A particularly advantageous embodiment of the invention is that the insert is followed by a nozzle ring connected via an edge-side seal, spaced apart from it, which the delay set penetrates and that the can ends at the seal in such a way or protrudes at a short distance such that when the The hot fog through the nozzle openings of the nozzle ring with peripheral destruction of the seal between the contact head and socket, optionally through an annular space arranged in the contact head.

With this design of the mist throwing body, there is the possibility of increasing the diameter of the mist structures generated in the flight state and, on the other hand, of improving the throwing distances with minimal effort.

It is known that smoke throwing bodies produce fog in two ways: First, the can can be disassembled, after which the fog either spreads out in the air in a spherical manner, or in a dome shape lying on the ground, or also by the fact that the fog is ejected from the ends of the throwing bodies, resulting in an approximately cylindrical fog pattern arises. However, the roller shape has the disadvantage of having relatively small diameters in flight. Furthermore, the flight distance is limited by the amount of the propellant. The enlargement of the diameter of the fog formation and the improvement of the throwing distances are achieved as follows: After the deceleration charge is ignited and burned off by a propellant charge, the ignition charge is activated and ultimately the fog charge is ignited. The hot gases formed pass through the nozzle ring and meet the material of the seal. This burns and allows the fog to emerge peripherally. The high internal pressure in the can accelerates it radially, which means that considerably larger smoke wall diameters can be achieved in flight than was previously possible. Due to the fact that the edge of the socket projects slightly beyond the contact head, a deflection of the mist against the direction of flight can be achieved, as a result of which the gas pressure is given a radial and an axial vector. The axial vector is so large that the mist launcher is accelerated further and the mist set itself acts as a rocket motor. In particular in cooperation with the above-described insert having the nozzle in the contact head, this results in further additional advantages. Since the seal e.g. can be caused by intentionally set inhomogeneities not to immediately burn evenly over the entire circumference, the fog can initially only emerge from the interior at one or more points under strong pressure. This leads to a deliberate wobbling movement that enlarges the wall of fog. If the smoke nozzle has a twist, this creates a helical ejection characteristic, which leads to homogeneous fog walls of large diameter. In contrast to conventional throwing bodies, after such a smoke impact body strikes the ground, it does not remain there, but the mist that continues to flow allows the smoke impact body to roll further in the direction of the throw, which also causes the smoke wall to expand.

A variant of this embodiment consists in that the nozzle openings are arranged conically and coaxially in the edge region of the nozzle ring and are closed by the seal, the seal being conical with the aid of a projection of the upper edge of the can and a chamfering of the lower edge of the contact button lying between them Section forms in the extension of which the nozzle openings are. The axis of the nozzle openings and that of the conical sections of the seals preferably form an angle of 45 ° to the axis of the can.

The nozzle ring can be arranged in a collar directed into the can, with the aid of which both parts can be firmly connected to one another. The collar with the nozzle ring and the socket can thus be securely attached to the contact head by simply screwing them together. A further preferred embodiment consists in that the central axes of the nozzle openings form an angle of approximately 45 ° with the throwing body axis and, if appropriate, preferably run coaxially skewed at an angle (β) to the central axis of the fog throwing body for swirl formation.

Advantageously, the nozzle openings of the nozzle ring against the fog set are closed with the aid of a foil, preferably a lead-tin foil. This material is destroyed by the burning temperatures, which releases the nozzles.

The propelling force of the emerging mist can advantageously be increased in that the mist set is designed as a driving mist set, with at least the first being the driving mist set in the case of a plurality of mist sets.

• 1. aus 40 Gew.% Hexachloräthan, 38 Gew.% Zinkoxid, 7 Gew.% Eisen(III)oxid und 15 Gew.% Aluminiumpulver einer Korngrösse <100 11m und
• 2. mit IR-Deckung aus 46 Gew.% Hexachloräthan, 12 Gew.% Calciumsilizid, 7 Gew.% Eisenoxid und 20 Gew.% Cäsiumnitrat und 15 Gew.% Aluminiumpulver einer Korngrösse <100 ₁1m.

Particularly advantageous propellant mist sets exist

• 1. from 40% by weight of hexachloroethane, 38% by weight of zinc oxide, 7% by weight of iron (III) oxide and 15% by weight of aluminum powder with a grain size <100 and 11m
• 2. with IR cover from 46 wt.% Hexachloroethane, 12 wt.% Calcium silicide, 7 wt.% Iron oxide and 20 wt.% Cesium nitrate and 15 wt.% Aluminum powder of a grain size <100 ₁ 1m.

A particularly advantageous embodiment consists in that at least the mist set that burns first has a convex or conical projecting contact surface with the correspondingly recessed second mist set.

This avoids so-called “holes” in the fog wall, as are common in the prior art. In the prior art, the fog sets usually consist of pellets. Due to the manufacture, the height of these disc-shaped bodies is limited. However, one has to rely on stacking several compacts, which has the following disadvantage: Normally, the burning rate is not uniform over the cross-section of the compacts, because the deceleration set preferably ignites the mists in the middle, from where the Spreads the ignition spot. But this leads to the fact that the subsequent compact is also ignited in a punctiform manner, which happens exactly at the moment when the effect of the first compact diminishes. This results in the "holes" in the fog wall that can be observed particularly clearly during flight.

The invention provides a quick-release smoke missile with long ranges and at the same time a significantly improved fog effect.

• Fig. 1 einen Nebelwurfkörper, im Schnitt;
• Fig. 2 den Kontaktkopf des Nebelwurfkörpers nach Fig. 1, in vergrösserter Darstellung;
• Fig. 3 eine weitere Ausgestaltung eines Kontaktkopfes;
• Fig. 4 eine dritte Ausführungsform des Kontaktkopfes;
• Fig. 5 den Einsatz im Kontaktkopf gemäss Fig. 1 und 2 in Draufsicht;
• Fig. 6 den Einsatz im Kontaktkopf gemäss Fig. 3 in Draufsicht;
• Fig. 7 den Einsatz des Kontaktkopfes gemäss
• Fig. 4 in Draufsicht;
• Fig. 8 und 9 den Ausschnitt A aus Fig. 1, vergrössert;
• Fig. 10 einen Verzögerungssatz für den Kontaktkopf gemäss Fig. 1;
• Fig. 11 eine Platte, die den Kontaktkopf vom Nebelsatztrennt, im Schnitt;
• Fig. 12 die Platte gemäss Fig. 11, in Draufsicht;
• Fig. 13 eine Treibladung für den Kontaktkopf gemäss Fig. 4, im Schnitt;
• Fig. 14 die Treibladung gemäss Fig. 13, in Draufsicht;

The invention is explained in more detail below using exemplary embodiments with reference to drawings, further advantageous refinements and improvements being mentioned. It shows:

• Figure 1 shows a smoke missile, in section.
• FIG. 2 shows the contact head of the smoke nozzle according to FIG. 1, on an enlarged scale;
• 3 shows a further embodiment of a contact head;
• Fig. 4 shows a third embodiment of the contact head;
• 5 shows the insert in the contact head according to FIGS. 1 and 2 in a top view;
• 6 shows the insert in the contact head according to FIG. 3 in a top view;
• Fig. 7 shows the use of the contact head
• Fig. 4 in plan view;
• 8 and 9 the detail A from FIG. 1, enlarged;
• FIG. 10 shows a delay set for the contact head according to FIG. 1;
• Fig. 11 shows a plate which separates the contact head from the mist set, in section;
• FIG. 12 the plate according to FIG. 11, in a top view;
• FIG. 13 shows a propellant charge for the contact head according to FIG. 4, in section;
• FIG. 14 the propellant charge according to FIG. 13, in a top view;

Fig. 1 shows a section through a smoke nozzle 10 with an aluminum contact head 11 of a box 12, in which fog sets 13, 14 and 15 are housed. Above the mist set 15, which is designed as a propellant mist set in the present embodiment, there is an ignition set 16. At the lower edge of the can 12, a rubber plate 17 is fastened by means of a nut 18 and secured with an adhesive 19 to secure the shock. The contact surface 20 between the fog sets 15 and 14 is frustoconical. The fog set 15 engages in the fog set 14.

The contact head 11, which is made of aluminum, is surrounded by an insulating sheath 21 which is made of polyamide and is arranged all around on the contact rings 22 and 23. The contact rings 22 and 23 are connected via connecting lines 24 and 25, which run through unspecified openings of the insulating sleeve 21 to the inside, with a bridge igniter 26, which is accommodated in a bore 27 in the contact head 11 and via an opening 28 with the Receiving space 29 for a propellant charge 30 is connected.

A threaded blind hole 31, into which an insert 32 made of high-strength material is screwed, is located centrally in the central region of the contact head 11. The insert 32 is pot-shaped, its bottom region 33 is directed upwards and contains a plurality of nozzles 34 which are poured out with epoxy resin and are additionally closed to the outside by means of a metal foil 35. The insulating sleeve 21 lies against a shock protection 36 on a flange-like collar 37 at the upper end of the contact head 11. In the central region, the contact head 11 has a cylindrical extension 38, which is surrounded by a hollow cylindrical projection 40 to form an annular space 39, the extension 38 projecting slightly beyond the hollow cylindrical projection 40. The contact head 11 is placed with its extension 38 on a plate 41 and fastened to it by means of screw connections 42 or connected to it. Between the surface of the plate 41 and the hollow cylindrical projection 40 there is a gap 44, which corresponds to a gap between the insulating sleeve 21 and the surface of the plate 41; in the gap between the insulating sleeve 21 and the plate 41 there is a seal 43 (see FIGS. 8 and 9). Due to the different dimensions of the extension 38 and the projection 40, the seal 43 is prevented from being crushed when the screw connection 42 is tightened (several screws are provided).

In the plate 41 there is a nozzle ring 45 with a plurality of nozzles arranged on the plate edge, which, as can be seen in particular from FIGS. 8 and 9, are directed directly at the seal 43. There is also the possibility that they open into the annular space 39, which leaves access to the seal 43 via the gap 44.

The nozzle ring 45 is secured against the igniter 16 by means of a lead-tin foil 46.

In the case of the contact head 11 according to FIG. 2, the insert 32 is designed as a cup-shaped or cup-shaped threaded part with an external thread 47, which has an internal thread 48 in the area of its cup or pot edge, into which a second thread part 49, likewise cup-shaped or cup-shaped, is screwed can be. The two threaded parts thus form the entire insert 32 and delimit the receiving space 29 for the propellant charge. In the bottom part of the second threaded part 49, a bore 50 is provided which continues in a bore 51 in the bottom of a threaded bore 52. A delay set 53 is screwed into this threaded bore 52, which is described in more detail with reference to FIG. 10. This delay set 53 has, according to FIG. 10, a delay piece 54, which is provided with an external thread on the head side (without reference number) so that it can be screwed into the threaded bore 52, and a bore 56, which prevents undesired spontaneous burning and expulsion of the burning material opens in the assembled state in the two bores 50 and 51, and on the foot side a delay device 57 with a smaller bore 58. The delay set 53 is shown differently in FIG. the position of the delay set 53 is only to be shown schematically there. The bridge igniter 26 (FIG. 2) is surrounded by a steel cap 59 which, together with the bridge igniter 26, is screwed into a threaded bore 60. The threaded bore 60 continues in the bores 27 and 28 and a transverse bore 28 'in the insert 32 in the receiving space 29. The electrical connecting lines 24 and 25 are inserted through the steel cap 59, specifically through a space 61 between the casing 21 and the contact head 11, which is filled with synthetic resin after the connecting lines 25 and 25 'have been inserted. The shock protection 36 is designed as an O-ring seal and at the same time serves to produce a vacuum seal. The vacuum tightness is achieved together with the synthetic resin in room 61.

6 shows the insert 32 in a top view of the bottom section. Three nozzles 34 can be seen here, which are evenly distributed over the circumference. 6, these nozzles 34 are shown axially parallel.

In another embodiment of the invention (see FIG. 5), the nozzles 34 are shown running obliquely inwards.

To generate a swirl, it is sufficient to drill the nozzles 34 at an angle a; the nozzle axes should preferably not intersect the projectile axis.

3 shows a further embodiment of the invention. The contact head 65 shown here has no extension 38; the hollow cylindrical projection 40 delimits a pot space 66 into which an insert 67 protrudes. A cover 68 can be screwed onto this insert 67, which then limits the receiving space 29 for the propellant charge 30 downwards. The delay set 53 is then screwed into the cover 68, a bore 69 corresponding to the bores 50 and 51 being made in the cover 68 between the delay set 53 and the receiving space 29. 3, both the insert 67 and the cover 68 supplementing the insert 67 are made of steel. The insert 32 or 67 is shown in FIGS. 1 to 3 as being screwed into the contact head 11 or 65. It is of course also possible to press it in or to fix it in the contact head 11 or 65 using a conical design and a counter-cone.

Another embodiment of the invention is shown in FIG. 4. The contact head 70 has an opening 71 in its central region with an internal thread, into which an insert 72 is screwed. This insert 72 is again pot-shaped and has a pot bottom 73 at its upper end, in which two bores 74 and 75 and a slot 76 are made on the outer surface (see also FIG. 7). The bores 74 and 75 correspond to the nozzles 34 and are dimensioned practically the same as these. A propellant charge 77 is introduced into the interior of the insert 72 and, as can be seen from FIGS. 13 and 14, is designed as a star burner. This propellant charge 77 is arranged at a distance from the pot bottom 73 and surrounds a star-shaped space 78 in which a bridge igniter 79 in the form of a squib is housed. It can be seen from FIG. 13 that the bridge igniter 79 is arranged in the region of the upper end of the propellant charge 77. In contrast to this, in the embodiment according to FIG. 4, the bridge igniter 79 is arranged approximately in the central region of the star-shaped space 78.

The propellant charge 77, designed as a star burner, has a weight of approx. 2 g. The bridge igniter 79 designed as a squib has an insulation body 80, to the front end of which explosive 81 and to the rear end of which connection conductors 82 and 83 are connected. These two connection conductors 82 and 83 are led out of the interior of the insert 72 through the bores 74 and 75 and lie in a guide channel 84 which extends in the axial direction between the contact head 70 and the insert 72. The connecting lines 82 and 83 enter a pot space 86 corresponding to the pot space 66 and are led out via two channel bores 85 into a channel 87 corresponding to the space 61. From there, the connecting conductors 82 and 83 reach the contact rings 22 and 23 through the insulating sheath 21. The insert 72 is screwed into the aluminum contact head 70 via the slot 76 and is deepened relative to the surface of the contact head 70, so that a silicone rubber seal 88s can be inserted into the depression formed. The insert 72, like the other inserts 32, 67, is also made of high-strength material, in this case steel.

A steel threaded piece 90 is screwed into the end of the insert 72 opposite the pot bottom 73 and has an inner bore 91 which is divided into two spaces 93 and 94 by an intermediate wall 92 approximately in the central area. In the intermediate wall 92 there is a small through opening 95 and above the intermediate wall 92, that is to say towards the combustion chamber or the propellant charge 77 (star burner), there is a delay set 96 and on the opposite, lower side an ignition charge 97. If after ignition the Ignition cap burns the propellant charge 77, the ignition charge 97 is ignited via the delay set 96, as a result of which the fog charge is ignited.

8 and 9 show sections A of FIG. 1 in an enlarged representation in two variants. You can see the insulating sleeve 21 with a contact ring 23 and the plate 41 with the nozzle ring 45. In the gap between the sleeve 21 and the surface of the plate 41, the seal 43 is inserted, which due to a chamfer 100 on the insulating sleeve 21 and one conical projection 101 on the can 12 an obliquely ko niche upwardly bent portion 102. Accordingly, the seal 43 is turned over at its edge with a section 102 designed as a cone. This section 102 lies in the extension of the nozzle openings 103 of the nozzle ring 45.

9, the angled section 102 is not formed. The seal 43 is flat in a ring shape and only seals the nozzle openings 103 of the nozzle ring 45. Here, the combustion of the sealing material takes place much faster, which means that, in addition to the faster burn-up of the deceleration set, the fog can also be accelerated if desired.

11 and 12 show the plate 41 sealing the can 12 with the nozzle ring 45 and the nozzle openings 103. A collar 104 is provided on the plate 41, which is provided with an external thread 105 and is screwed into the upper edge of the can 12 can be. In the plate 41 there are a threaded bore 106 for receiving the deceleration set 53 (see FIG. 1) and three threaded bores 107 into which screw connections 42 can be screwed. The longitudinal direction or longitudinal axis of the nozzle openings 103 can run through the center of the plate 41. There is also the possibility, as indicated in FIG. 12, of allowing the longitudinal axes to run at an angle β (here 25 °), as a result of which, in addition to the additional thrust, a swirl is generated when the mist, which can be a driving mist, emerges. The fact that the connecting lines 82, 83 are guided through the bores 74, 75 (FIG. 4) serving as nozzles has the advantage that no sealing problems have to be taken into account, as is necessary when the connecting lines are led through to the side. According to the invention, the spacing of the bores 74, 75 is preferably 5 mm and their diameter is 0.8 to 1.5 mm, whereas the thickness of the connecting lines is preferably also 0.8 to 1.5 mm.

For the star burner serving as a propellant charge according to FIG. 14, rocket fuel is preferably used, which consists of nitrocellulose powder or nitroglycerin powder as base components and a binder. This star burner can be pressed or extruded. The material is chosen so that all rocket propellants for such smoke launchers are designed with degressive combustion so that they do not burn as spontaneously as loose powder.

Hexachloroethane is used for the main fog sets (13, 14). This evaporates and can close the primer by means of precipitation and react with it with a delayed effect. 4, the bore 91 in the intermediate wall 92 is 0.5 to 1 mm thick and at the bottom, that is to say towards the fog sets, the ignition set is closed with a foil 98 based on a lead-tin alloy , wherein it can also cover (not shown) the entire threaded piece 90.

Due to the passage of the connecting lines 82 and 83 through the bores 74 and 75, which represent the nozzles, a pressure of no higher than 13.5 bar is established inside the cup during the first 2 milliseconds.

The sentences listed below have proven particularly useful in the present invention.

Propellant and mist set mixture (15)

Mit IR-Deckung (15)

With IR coverage (15)

Propellant and mist sentence mixture

Claims (26)

1. Smoke projectile, especially for shooting from launchers, with centrally arranged propellant charge (30, 77), consisting of a container (12) with smoke composition (13, 14, 15) present therein, as well as ignition charge (16, 97) and a contact head (11, 65, 70) with bridge igniter (79) connected with the container (12), delay charge (53, 96) and a collar (21), surrounding the contact head (11, 65, 70), preferably of polyamide. with contact rings (22, 23), characterised in that the contact head (11, 65, 70) has an assembly (32, 67, 72), including reception chamber (29) for the residue-free burnable propellant charge (30, 77) of nitrocellulose or nitroglycerol powder or blocks, on one end of which follows the delay charge (53, 96) and on its end lying opposite the delay charge (53, 96) are arranged concentric off-centre arranged nozzles and that the reception chamber (29) is enclosed by high-strength material.

2. Smoke projectile according to claim 1, characterised in that the contact head (11,65,70) consists of aluminium or steel and the assembly (32, 67, 72) with the contact head (11, 65, 70) of high-strength steel and that the assembly (32, 67, 72) is firmly attached to the contact head (11, 65, 70).

3. Smoke projectile according to claim 2, characterised in that the contact head (11, 65, 70) and the assembly (32,67,72) are made in one piece.

4. Smoke projectile according to claim 1 or 2, characterised in that the contact head (65, 70) is formed ring-shaped, whereby the assembly (67, 72) passes through this and is screwed with a cover (68) or threaded pice (90), whereby the cover (68) or the threaded piece (90) carries the delay charge (53, 96).

5. Smoke projectile according to one of claims 1 to 4, characterised in that the assembly (32) has a first saucer-shaped part which is fixed in the contact head (11) and a second threaded part (49, 90) which is fixed within the first threaded part and is in connection with the delay charge (53, 96).

6. Smoke projectile according to one of claims 1 to 5, characterised in that the delay charge (53, 96) is in connection, via a bore (50, 51, 69), with the propellant charge (30), whereby the delay charge (53, 96) is arranged in the second threaded part (49, 90).

7. Smoke projectile according to claim 6, characterised in that the delay charge (96) and the ignition charge (97), together forming a unit, are accommodated in a bore (91) in a housing element (29) formed as threaded piece (90), whereby the bore (91) has a narrowed opening passage (95).

8. Smoke projectile according to claim 7, characterised in that the housing piece (90), for the reception of the delay and ignition charge (96, 97), is the second threaded part of the assembly (72).

9. Smoke projectile according to claim 8, characterised in that the delay charge (96) is connected directly, without narrowing, with the chamber for the reception of the propellant charge (77).

10. Smoke projectile according to one of claims 1 to 9, characterised in that the nozzles or bores (34, 74, 75) are cast with a synthetic resin, preferably with epoxide resin.

11. Smoke projectile according to claim 10, characterised in that the nozzles (34) are additionally covered with a plate, preferably of silicone rubber.

12. Smoke projectile according to one of claims 10 or 11, characterised in that at least three outwardly directed nozzles (34) are provided which have a diameter of 2 mm.

13. Smoke projectile according to one of claims 1 to 11, characterised in that the nozzle axes, for the production of a twist, run at an angle (a or P) to the axis of the smoke projectile.

14. Smoke projectile according to one of claims 10 to 12, characterised in that the assembly (32) has a bore (28) to the lateral bridge igniter (26) running obliquely to the axis of the contact head (11), the diameter of which is smaller than that of the bridge igniter (26).

15. Smoke projectile according to one of claims 1 to 14, characterised in that the propellant charge (77) is formed within the assembly (72) as radial burner consisting of rocket propellant.

16. Smoke projectile according to claim 15, characterised in that the radial burner is a retrogressive mini-radial burner.

17. Smoke projectile according to claim 15 or 16, characterised in that the radial burner is arranged at a distance from the pot bottom (73) of the assembly (72) having the bores (74, 75), that the bridge igniter (79) is arranged in the inner chamber of the radial burner and that the connection pipes (82, 83) are passed through to the igniter through the bores (74, 75), whereby the thicknesses of the connection pipes (82, 83) correspond approximately to the diameter of the bores (74, 75) and that the bridge igniter (79) is arranged in the region of the radial burner lying towards the pot bottom (73) of the assembly (72) and is suspended on the connection pipes (82, 83).

18. Smoke projectile according to one of the preceding claims, characterised in that the propellant charge (77) consists of nitrocellulose or ni- troglycol powder as basic component with binding agent with retrogressive burning and is extruded or pressed.

19. Smoke projectile according to one of claims 1 to 18, characterised in that on the assembly (32) is attached a nozzle ring (45) connected with this at a distance via an edge-sided seal (43) and that the container (12) ends at the seal (43) in such a manner or overlaps it with slight distance that, in the case of burning of the smoke composition, the hot smoke flows out peripherally through the nozzle openings (103) of the nozzle ring (45) with destruction of the seal (43) between contact head (11) and container (12), possibly through an annular chamber (39) provided in the contact head (11).

20. Smoke projectile according to one of claims 7 to 19, characterised in that the nozzle openings (103) are arranged cone-shaped and coaxially in the edge region of the nozzle ring (45) and are closed by the seal (43), whereby the seal (43), with the help of a projection (101) of the upper container edge and of a chamfer (100) of the lower edge of the contact head (11), forms a conical-shaped section (102) lying between these, in the extension of which are present the nozzle openings (103).

21. Smoke projectile according to claim 19 or 20, characterised in that the middle axes of the nozzle openings (103) form with the projectile axis an angle of about 45 degrees and possibly preferably run twisted at an angle (β) to the middle axis of the smoke projectile for torque formation.

22. Smoke projectile according to one of claims 19 to 21, characterised in that the nozzle openings (103) of the nozzle ring (45) are closed with a foil.

23. Smoke projectile according to one of claims 8 to 12, characterised in that the smoke composition is made as propellant smoke composition, whereby the first smoke composition (15) is a propellant smoke composition.

24. Smoke projectile according to claim 23, characterised in that the propellant smoke composition consists of 40wt.% hexachloroethane, 38wt.% zinc oxide, 7wt.% iron (III) oxide and 15wt.% aluminium powder of a grain size of <100 Il-m.

25. Smoke projectile according to claim 23, characterised in that the propellant smoke composition with IR cover consists of 46 wt.% hexachloroethane, 12 wt.% calcium silicide, 7 wt.% iron oxide and 20 wt.% caesium nitrate and 15 wt.% aluminium powder of a grain size of <100 µm.

26. Smoke projectile according to one of claims 1 to 25, characterised in that at least the first burning off smoke composition (15) has a convex or cone-shaped projecting contact surface (20) with the correspondingly depressed- formed second smoke composition (14).

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