EP0271480B1 - Flare-carrying projectile - Google Patents

Flare-carrying projectile Download PDF

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Publication number
EP0271480B1
EP0271480B1 EP19870890276 EP87890276A EP0271480B1 EP 0271480 B1 EP0271480 B1 EP 0271480B1 EP 19870890276 EP19870890276 EP 19870890276 EP 87890276 A EP87890276 A EP 87890276A EP 0271480 B1 EP0271480 B1 EP 0271480B1
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EP
European Patent Office
Prior art keywords
grenade
charge
light
bevelling
fins
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP19870890276
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German (de)
French (fr)
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EP0271480A3 (en
EP0271480A2 (en
Inventor
Peter Schödlbauer
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Hirtenberger AG
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Hirtenberger AG
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Publication date
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Publication of EP0271480A3 publication Critical patent/EP0271480A3/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0838—Primers or igniters for the initiation or the explosive charge in a warhead
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/42—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of illuminating type, e.g. carrying flares
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F42B12/625—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile a single submissile arranged in a carrier missile for being launched or accelerated coaxially; Coaxial tandem arrangement of missiles which are active in the target one after the other

Definitions

  • the invention relates to a light grenade with a detonator, an ejection charge housed in a small bowl, a light body which is attached to a parachute, the light grenade having a propellant cartridge, partial charge body and stabilizer wing at its rear end, the stabilizer wing at its front end are chamfered and the edge is chamfered like a roof edge in the region of the chamfer.
  • the small bowl that contains the ejection charge is made of aluminum. If the ejection charge is ignited, the bowl breaks and the aluminum pieces may block the ignition opening of the filament, causing the filament not to ignite.
  • Stabilizer wings are provided on the tail of these light grenades for stabilization during flight. These Stabilizer blades are shaped differently at their front end, and bevels of up to 30 ° with respect to the axis of the illuminated grenade are also known.
  • the edge of the stabilizer wing runs in a straight line and parallel to the axis of the light grenade or in any curve shape with the maximum diameter at the end of the wing.
  • the known edge of the known light grenades is either flat, rounded or gabled.
  • light grenades are known in which the light body and parachute are accommodated in a separate container, which in turn is housed in the light grenade.
  • a first ejection charge is ignited, which separates the container from the illuminated grenade.
  • the container is shaped or elements are attached to it so that its rotational speed and its translational speed are greatly reduced in the next few seconds.
  • the container is then separated from the luminous element and the parachute with a second ejection charge, which is ignited by delay elements from the first ejection charge.
  • This second discharge charge also ignites the filament, so that the problems mentioned above also occur here.
  • US-A-1 347 125 describes a grenade, which, however, is not a fluorescent grenade, which has stabilizer wings which have a convex outer contour; in contrast to the illuminated grenade described at the beginning, however, these stabilizer wings have no bevel at their front end.
  • US-A-2 120 246 describes a light grenade where the propellant charge is housed in a housing which has openings at the rear end which are closed off by a disk.
  • the propellant cartridge is filled with a double-base, rolled plate powder in a light grenade of the type mentioned that the angle between the bevel of the stabilizer wing and the axis of the light grenade is about 50 °, that the outer contour of the stabilizer wing in The area below the bevel is convexly curved so that preferably the bowl containing the discharge charge Has openings which are covered on the inside by a foil, preferably an aluminum foil, so that predetermined breaking points result that the igniter is attached to the front housing part via a steel adapter and that a delay element is arranged between the ejection charge and the luminous element.
  • the ignition power of the cartridge could be increased so that the bulk powder contained in waterproof celluloid bodies ignites almost unaffected by external moisture and thus the initial speed and, as a result, the flight distance are almost independent of weather conditions.
  • the special shape of the stabilizer blades and the use of a steel adapter reduce the drag coefficient on the one hand and improve the stabilization behavior on the other hand, i.e. the maximum flight distance is increased.
  • the ignition of the filament is delayed, i.e. it takes place only after it has been ejected from the grenade housing and when it is already hanging on the parachute.
  • FIG. 1 shows a light grenade according to the invention, partly in section
  • FIG. 2 shows the igniter of the light grenade, partly in section.
  • the light grenade has two housing parts made of aluminum, a front housing part 1 and a rear housing part 2. At the front end of the light grenade there is an igniter 5 which is designed according to the prior art and is therefore not described in detail. Its mode of operation is that an ejection charge 11 is ignited after an adjustable time from the firing of the light grenade. According to the invention, this discharge charge 11 is accommodated in a small bowl 13 made of steel, which has a plurality of eccentric openings 25 (see FIG. 2), which are covered on the inside, that is to say on the side of the bowl 13 facing the discharge charge 11, with an aluminum foil 24.
  • This aluminum foil 24 closes the bowl 13 tightly. If the ejection charge 11 is ignited, the small dish 13 made of steel withstands, but the aluminum foil 24 tears in the region of the openings 25. This makes it possible to predict where the aluminum will settle after the ejection charge 11 has been ignited. A suitable choice of the position of the openings can ensure that it never lies in front of the ignition opening of the luminous element 7 (see FIG. 1) and thereby prevents its ignition.
  • the igniter 5 is screwed into an adapter 16, which is essentially a ring made of steel. He carries the detonator 5 and supports the interior structures. A spiral spring 10 is used for tolerance compensation. The use of steel causes the center of gravity to be moved forward, which results in better flight behavior.
  • a delay element 18 is also provided between the luminous element 7 and the steel bowl 13 with the ejection charge 11. It has been found that it is not expedient if the light set 7 is ignited immediately after the discharge charge has been ignited, which causes the separation of the two housing parts 1 and 2; the ejection process is made more difficult by the recoil effect of the burning light set and the lines of the parachute 19 may be scorched.
  • the luminous element 7 Due to the delay element 18, the luminous element 7 only begins to light up when it is already hanging on the parachute 19. When the luminous element 7 is ignited, it blows away the delay element which covers its front surface, and it can develop its full luminosity.
  • the front housing part 1 is connected to the rear housing part 2 by six shear pins 12.
  • the joint 14 between the two housing parts 1 and 2 is sealed with silicone compound. If the ejection charge 11 is ignited, which usually takes place at a height of approximately 350 m, the resulting pressure is sufficient for the shear pins 12 to break, the two housing parts 1 and 2 to be separated, and the front housing part 1 to be pulled away via the luminous element 7.
  • a spring plate 21 is fastened in the rear housing part 2 with a fixing screw 9. There is a sealing screw 15 behind the fixing screw 9.
  • a spiral spring 20 is anchored to the spring plate 21 with its last gear.
  • the spiral spring 20 surrounds the ejection bowl 8 and serves to eject the parachute 19 from the rear housing part 2.
  • the spiral spring 20 is anchored so that it does not jump out of the rear housing part 2 with the parachute and gets caught in the lines of the parachute 19.
  • the light grenade is fired from a corresponding tube.
  • the fluorescent grenade has a sealing ring 17 for sealing the tube.
  • the shot is fired by firing a propellant cartridge 4, whereupon the charge of the partial charge body 6 also ignites.
  • a maximum of six such partial load bodies 6 can be attached; In order to achieve smaller shot widths, the number of part-load bodies 6 can also be reduced accordingly.
  • rolled plate powder M8 (registered trademark) is used for the drive cartridge 4, which is a two-base plate powder. This powder has proven to be very powerful. If the cartridge 4 is made watertight, as is known, when this powder is used, the range is not or only slightly reduced when it is wet outside. Bulk powder, packed in watertight celluloid bodies, is used for the partial charge body 6.
  • the light grenade has stabilizer wing 3.
  • These stabilizer blades 3 are chamfered at their front end; in the area of this bevel 22, the edge of the stabilizer wing 3 is beveled like a roof edge.
  • the angle between the bevel 22 and the axis of the illuminated grenade is approximately 50 °.
  • the edge thereof is not exactly straight and parallel to the axis of the illuminated grenade, but is slightly convex in accordance with the invention.
  • a stabilizer wing 3 dimension of 80 mm a radius of curvature of 150 mm has proven to be very favorable.
  • the maximum flight range of the illuminated grenade is increased by this wing shape.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)

Description

Die Erfindung betrifft eine Leuchtgranate mit einem Zünder, einer in einem Schälchen untergebrachten Ausstoßladung, einem Leuchtkörper, der an einem Fallschirm befestigt ist, wobei die Leuchtgranate an ihrem hinteren Ende eine Treibpatrone, Teilladungskörper und Stabilisator-Flügel aufweist, wobei die Stabilisator-Flügel an ihrem vorderen Ende abgeschrägt sind und wobei die Kante im Bereich der Abschrägung dachkantenartig abgeschrägt ist.The invention relates to a light grenade with a detonator, an ejection charge housed in a small bowl, a light body which is attached to a parachute, the light grenade having a propellant cartridge, partial charge body and stabilizer wing at its rear end, the stabilizer wing at its front end are chamfered and the edge is chamfered like a roof edge in the region of the chamfer.

Eine derartige Leuchtgranate wurde von der Anmelderin bzw. Patentinhaberin unter der Bezeichnung Mk2 in großen Stückzahlen verkauft; auch andere Unternehmen hatten zur Mk2 ähnliche Leuchtgranaten im Programm. Der Inhalt des Oberbegriffes stellt demnach einen Stand der Technik gemäß Artikel 54(2) EPÜ dar.Such a grenade was sold in large numbers by the applicant or patent owner under the name Mk2; other companies also had similar grenades to their Mk2 range. The content of the generic term therefore represents prior art in accordance with Article 54 (2) EPC.

Bei diesen Leuchtgranaten besteht das Schälchen, das die Ausstoßladung enthält, aus Aluminium. Wenn die Ausstoßladung gezündet wird, bricht das Schälchen, und die Aluminiumstücke können unter Umständen die Zündöffnung des Leuchtkörpers verlegen, wodurch der Leuchtkörper nicht zündet.In these light grenades, the small bowl that contains the ejection charge is made of aluminum. If the ejection charge is ignited, the bowl breaks and the aluminum pieces may block the ignition opening of the filament, causing the filament not to ignite.

Läuft die Anzündfunktion ungestört ab, so wird durch die unmittelbare Zündung des Leuchtkörpers und den dabei entstehenden Rückstoß der Ausstoßvorgang aus dem Heckteil erschwert. Dies kann außerdem dazu führen, daß durch die heißen Verbrennungsgase die Fallschirmleinen, die sich im gepackten Zustand unmittelbar hinter dem Leuchtkörper befinden, während des Entfaltens angesengt werden und letztlich reißen.If the ignition function runs undisturbed, the direct ignition of the lamp and the resulting recoil make it more difficult to eject from the rear section. This can also lead to the fact that the parachute lines, which are in the packed state immediately behind the luminous element, are singed during the unfolding and ultimately tear due to the hot combustion gases.

Bei diesen Leuchtgranaten sind entweder Treibpatrone oder Teilladungskörper oder sogar alle Elemente des Treibsystemes wasserdicht. Trotzdem ist die Flugweite bei äußerer Nässe wie z.B. starkem Regen wesentlich herabgesetzt und der Einsatzzweck somit verfehlt.With these fluorescent grenades, either the cartridge or part load or even all elements of the propulsion system are watertight. Nevertheless, the flight distance in external wetness, e.g. heavy rain significantly reduced and the purpose of use is therefore missed.

Zur Stabilisierung während des Fluges sind bei diesen Leuchtgranaten am Heck Stabilisator-Flügel vorgesehen. Diese Stabilisatorflügel sind an ihrem vorderen Ende unterschiedlich geformt, wobei auch Abschrägungen bis zu 30° bezogen auf die Achse der Leuchtgranate bekannt sind. Die Kante der Stabilisator-Flügel verläuft geradlinig und parallel zur Achse der Leuchtgranate oder in beliebiger Kurvenform mit dem Maximaldurchmesser am Ende des Flügels.
Die vordere Kante ist hei bekannten Leuchtgranaten entweder flach, abgerundet oder satteldachförmig gestaltet.Stabilizer wings are provided on the tail of these light grenades for stabilization during flight. These Stabilizer blades are shaped differently at their front end, and bevels of up to 30 ° with respect to the axis of the illuminated grenade are also known. The edge of the stabilizer wing runs in a straight line and parallel to the axis of the light grenade or in any curve shape with the maximum diameter at the end of the wing.
The known edge of the known light grenades is either flat, rounded or gabled.

Aus der FR-A-7 404 213 und aus der DE-A- 2 429 912 sind Leuchtgranaten bekannt, bei denen Leuchtkörper und Fallschirm in einem eigenen Behälter untergebracht sind, der seinerseits in der Leuchtgranate untergebracht ist. Bei einem vorgegebenen Punkt der Flugbahn wird eine erste Ausstoßladung gezündet, die den Behälter von der Leuchtgranate trennt. Der Behälter ist so geformt bzw. an ihm sind Elemente so angebracht, daß seine Rotationsgeschwindigkeit und seine Translationsgeschwindigkeit in den nächsten Sekunden stark herabgesetzt werden. Mit einer zweiten Ausstoßladung, die über Verzögerungselemente von der ersten Ausstoßladung gezündet wird, wird dann der Behälter von dem Leuchtkörper und dem Fallschirm getrennt.From FR-A-7 404 213 and from DE-A-2 429 912, light grenades are known in which the light body and parachute are accommodated in a separate container, which in turn is housed in the light grenade. At a predetermined point in the trajectory, a first ejection charge is ignited, which separates the container from the illuminated grenade. The container is shaped or elements are attached to it so that its rotational speed and its translational speed are greatly reduced in the next few seconds. The container is then separated from the luminous element and the parachute with a second ejection charge, which is ignited by delay elements from the first ejection charge.

Diese zweite Ausstoßladung zündet gleichzeitig auch den Leuchtkörper, sodaß die oben erwähnten Probleme auch hier auftreten.This second discharge charge also ignites the filament, so that the problems mentioned above also occur here.

In der US-A- 1 347 125 ist eine Granate, die allerdings keine Leuchtgranate ist, beschrieben, die Stabilisatorflügel aufweist, die eine konvexe Außenkontur aufweisen; diese Stabilisatorflügel weisen jedoch im Gegensatz zu der eingangs beschriebenen Leuchtgranate keine Abschrägung an ihrem vorderen Ende auf.US-A-1 347 125 describes a grenade, which, however, is not a fluorescent grenade, which has stabilizer wings which have a convex outer contour; in contrast to the illuminated grenade described at the beginning, however, these stabilizer wings have no bevel at their front end.

Schließlich ist in der US-A-2 120 246 eine Leuchtgranate beschrieben, wo die Treibladung in einem Gehäuse untergebracht ist, das am hinteren Ende Öffnungen aufweist, die durch eine Scheibe abgeschlossen sind. Dadurch wird beim Zünden der Treibladung zunächst ein Druck aufgebaut, der infolge der speziellen Ausbildung der Seitenwand dazu führt, daß die Leuchtgranate dicht am Granatwerferrohr anliegt; danach bricht die Scheibe, und die Granate wird infolge des Überdrucks, den die Treibladung erzeugt, aus dem Granatwerferrohr mit hoher Geschwindigkeit ausgestoßen; Leckverluste, die dadurch entstehen, daß die Leuchtgranate nicht dicht am Granatwerferrohr anliegt, werden dadurch vermieden. Mit dem Problem, daß die Ausstoßladung den Leuchtkörper nicht zuverlässig zündet. hat dies nichts zu tun.Finally, US-A-2 120 246 describes a light grenade where the propellant charge is housed in a housing which has openings at the rear end which are closed off by a disk. As a result, when the propellant charge is ignited, a pressure is initially built up which, owing to the special design of the side wall, results in the light grenade lying close to the grenade launcher tube; the disk then breaks and the grenade is released from the grenade launcher tube at high speed due to the excess pressure generated by the propellant pushed out; Leakage losses caused by the fact that the light grenade is not close to the grenade launcher tube are avoided. With the problem that the discharge charge does not reliably ignite the filament. this has nothing to do.

Es ist Aufgabe der vorliegenden Erfindung, eine Leuchtgranate zu schaffen, die unter allen Witterungsbedingungen bessere Flugeigenschaften, eine gesteigerte Reichweite und eine hohe Funktionszuverlässigkeit bei einfachem mechanischem Innenaufbau aufweist.It is an object of the present invention to provide a light grenade which has better flight characteristics, an increased range and a high degree of functional reliability with a simple mechanical internal structure under all weather conditions.

Diese Aufgabe wird erfindungsgemäß dadurch gelöst, daß bei einer Leuchtgranate der eingangs genannten Art die Treibpatrone mit einem zweibasigen, gerollten Plattenpulver gefüllt ist, daß der Winkel zwischen der Abschrägung der Stabilisatorflügel und der Achse der Leuchtgranate etwa 50° beträgt, daß die Außenkontur der Stabilisatorflügel im Bereich unterhalb der Abschrägung konvex gekrümmt ist, daß vorzugsweise das die Ausstoßladung enthaltende Schälchen Öffnungen aufweist, die auf der Innenseite durch eine Folie, vorzugsweise eine Aluminiumfolie, abgedeckt sind, sodaß sich Sollbruchstellen ergeben, daß der Zünder über einen Stahladapter am vorderen Gehäuseteil befestigt ist und daß ein Verzögerungselement zwischen Ausstoßladung und Leuchtkörper angeordnet ist.This object is achieved in that the propellant cartridge is filled with a double-base, rolled plate powder in a light grenade of the type mentioned that the angle between the bevel of the stabilizer wing and the axis of the light grenade is about 50 °, that the outer contour of the stabilizer wing in The area below the bevel is convexly curved so that preferably the bowl containing the discharge charge Has openings which are covered on the inside by a foil, preferably an aluminum foil, so that predetermined breaking points result that the igniter is attached to the front housing part via a steel adapter and that a delay element is arranged between the ejection charge and the luminous element.

Durch die Verwendung von zweibasigem, gerolltem Plattenpulver konnte die Zündkraft der Treibpatrone so verstärkt werden, daß das in wasserdichten Zelluloidkörpern enthaltene Schüttpulver nahezu unbeeinflußt von äußerer Nässe durchzündet und somit die Anfangsgeschwindigkeit und daraus resultierend die Flugweite nahezu unabhängig von Witterungsbedingungen sind.Through the use of double-base, rolled plate powder, the ignition power of the cartridge could be increased so that the bulk powder contained in waterproof celluloid bodies ignites almost unaffected by external moisture and thus the initial speed and, as a result, the flight distance are almost independent of weather conditions.

Durch die besondere Form der Stabilisatorflügel und die Verwendung eines Stahladapters werden einerseits der Widerstandsbeiwert verringert, andererseits das Stabilisierungsverhalten verbessert, d.h. die maximale Flugweite wird vergrößert.The special shape of the stabilizer blades and the use of a steel adapter reduce the drag coefficient on the one hand and improve the stabilization behavior on the other hand, i.e. the maximum flight distance is increased.

Bei der Verwendung eines erfindungsgemäßen Schälchens kann es nicht mehr vorkommen, daß die Zündkette von der Ausstoßladung zum Leuchtkörper unterbrochen wird. Es ist genau vorherzusehen, wo sich die (Aluminium)-Folie ablagern kann, nämlich nur im Bereich der exzentrischen Öffnungen. Das Schälchen selbst hält der Ausstoßladung stand.When using a small bowl according to the invention, it can no longer happen that the ignition chain is interrupted by the discharge charge to the filament. It must be predicted exactly where the (aluminum) foil can deposit, namely only in the area of the eccentric openings. The bowl itself withstands the discharge charge.

Durch die Verwendung eines Verzögerungselementes zwischen Ausstoßladung und Leuchtkörper wird die Zündung des Leuchtkörpers verzögert, d.h. sie erfolgt erst, nachdem er aus dem Granatengehäuse ausgestoßen wurde und wenn er bereits am Fallschirm hängt.By using a delay element between the discharge charge and the filament, the ignition of the filament is delayed, i.e. it takes place only after it has been ejected from the grenade housing and when it is already hanging on the parachute.

An Hand der beiliegenden Zeichnungen wird die Erfindung näher erläutert. Es zeigt: Fig. 1 eine erfindungsgemäße Leuchtgranate zum Teil im Schnitt und Fig. 2 den Zünder der Leuchtgranate zum Teil im Schnitt.The invention is explained in more detail with reference to the accompanying drawings. 1 shows a light grenade according to the invention, partly in section, and FIG. 2 shows the igniter of the light grenade, partly in section.

Die Leuchtgranate weist zwei Gehäuseteile aus Aluminium auf, einen vorderen Gehäuseteil 1 und einen hinteren Gehäuseteil 2. Am vorderen Ende der Leuchtgrante befindet sich ein Zünder 5, der gemäß dem Stand der Technik ausgebildet ist und daher nicht näher beschrieben wird. Seine Wirkungsweise besteht darin, daß nach einer einstellbaren Zeit ab dem Abschuß der Leuchtgranate eine Ausstoßladung 11 gezündet wird. Diese Ausstoßladung 11 ist erfindungsgemäß in einem Schälchen 13 aus Stahl untergebracht, welches mehrere exzentrische Öffnungen 25 aufweist (siehe Fig. 2), die an der Innenseite, also an der der Ausstoßladung 11 zugekehrten Seite des Schälchens 13, mit einer Aluminiumfolie 24 abgedeckt sind.The light grenade has two housing parts made of aluminum, a front housing part 1 and a rear housing part 2. At the front end of the light grenade there is an igniter 5 which is designed according to the prior art and is therefore not described in detail. Its mode of operation is that an ejection charge 11 is ignited after an adjustable time from the firing of the light grenade. According to the invention, this discharge charge 11 is accommodated in a small bowl 13 made of steel, which has a plurality of eccentric openings 25 (see FIG. 2), which are covered on the inside, that is to say on the side of the bowl 13 facing the discharge charge 11, with an aluminum foil 24.

Diese Aluminiumfolie 24 schließt das Schälchen 13 dicht ab. Wird die Ausstoßladung 11 gezündet , so hält das Schälchen 13 aus Stahl stand, die Aluminiumfolie 24 reißt aber im Bereich der Öffnungen 25. Dadurch kann vorhergesehen werden, wo sich das Aluminium nach dem Zünden der Ausstoßladung 11 absetzt. Durch geeignete Wahl der Lage der Öffnungen kann erreicht werden, daß es sich nie vor die Zündöffnung des Leuchtkörpers 7 (siehe Fig. 1) legt und dadurch dessen Zündung verhindert.This aluminum foil 24 closes the bowl 13 tightly. If the ejection charge 11 is ignited, the small dish 13 made of steel withstands, but the aluminum foil 24 tears in the region of the openings 25. This makes it possible to predict where the aluminum will settle after the ejection charge 11 has been ignited. A suitable choice of the position of the openings can ensure that it never lies in front of the ignition opening of the luminous element 7 (see FIG. 1) and thereby prevents its ignition.

Der Zünder 5 ist in einem Adapter 16, der im wesentlichen ein Ring aus Stahl ist, eingeschraubt. Er trägt den Zünder 5 und stützt die Innenaufbauten ab. Eine Spiralfeder 10 dient zum Toleranzausgleich. Die Verwendung von Stahl bewirkt eine Verlegung des Schwerpunktes nach vorne, was ein besseres Flugverhalten bewirkt.The igniter 5 is screwed into an adapter 16, which is essentially a ring made of steel. He carries the detonator 5 and supports the interior structures. A spiral spring 10 is used for tolerance compensation. The use of steel causes the center of gravity to be moved forward, which results in better flight behavior.

Erfindungsgemäß ist zwischen dem Leuchtkörper 7 und dem Stahlschälchen 13 mit der Ausstoßladung 11 noch ein Verzögerungselement 18 vorgesehen. Es hat sich nämlich herausgestellt, daß es nicht zweckmäßig ist, wenn unmittelbar nach dem Zünden der Ausstoßladung, was die Trennung der beiden Gehäuseteile 1 und 2 bewirkt, bereits der Leuchtsatz 7 gezündet wird; es wird der Ausstoßvorgang durch die Rückstoßwirkung des brennenden Leuchtsatzes erschwert und unter Umständen werden die Leinen des Fallschirmes 19 angesengt.According to the invention, a delay element 18 is also provided between the luminous element 7 and the steel bowl 13 with the ejection charge 11. It has been found that it is not expedient if the light set 7 is ignited immediately after the discharge charge has been ignited, which causes the separation of the two housing parts 1 and 2; the ejection process is made more difficult by the recoil effect of the burning light set and the lines of the parachute 19 may be scorched.

Durch das Verzögerungselement 18 beginnt der Leuchtkörper 7 erst zu leuchten, wenn er bereits am Fallschirm 19 hängt. Wenn der Leuchtkörper 7 gezündet wird, sprengt er das Verzögerungselement, welches seine vordere Fläche abdeckt, weg, und er kann seine volle Leuchtkraft entfalten. Der vordere Gehäuseteil 1 ist mit dem hinteren Gehäuseteil 2 durch sechs Scherstifte 12 verbunden. Die Stoßstelle 14 zwischen den beiden Gehäuseteilen 1 und 2 ist mit Silikonmasse gedichtet.
Wird die Ausstoßladung 11 gezündet, was üblicherweise in etwa 350 m Höhe erfolgt, so reicht der dadurch entstehende Druck aus, daß die Scherstifte 12 brechen, die beiden Gehäuseteile 1 und 2 getrennt werden und der vordere Gehäuseteil 1 über den Leuchtkörper 7 weggezogen wird.Due to the delay element 18, the luminous element 7 only begins to light up when it is already hanging on the parachute 19. When the luminous element 7 is ignited, it blows away the delay element which covers its front surface, and it can develop its full luminosity. The front housing part 1 is connected to the rear housing part 2 by six shear pins 12. The joint 14 between the two housing parts 1 and 2 is sealed with silicone compound.
If the ejection charge 11 is ignited, which usually takes place at a height of approximately 350 m, the resulting pressure is sufficient for the shear pins 12 to break, the two housing parts 1 and 2 to be separated, and the front housing part 1 to be pulled away via the luminous element 7.

Im hinteren Gehäuseteil 2 ist ein Federteller 21 mit einer Fixierschraube 9 befestigt. Hinter der Fixierschraube 9 befindet sich eine Dichtschraube 15. An dem Federteller 21 ist eine Spiralfeder 20 mit ihrem letzten Gang verankert. Die Spiralfeder 20 umgibt das Ausstoß-Schälchen 8 und dient dazu, den Fallschirm 19 aus dem hinteren Gehäuseteil 2 auszustoßen. Die Spiralfeder 20 ist verankert, damit sie nicht mit dem Fallschirm aus dem hinteren Gehäuseteil 2 springt und sich in den Leinen des Fallschirmes 19 verfängt.A spring plate 21 is fastened in the rear housing part 2 with a fixing screw 9. There is a sealing screw 15 behind the fixing screw 9. A spiral spring 20 is anchored to the spring plate 21 with its last gear. The spiral spring 20 surrounds the ejection bowl 8 and serves to eject the parachute 19 from the rear housing part 2. The spiral spring 20 is anchored so that it does not jump out of the rear housing part 2 with the parachute and gets caught in the lines of the parachute 19.

Der Abschuß der Leuchtgranate erfolgt aus einem entsprechenden Rohr. Zum Abdichten des Rohres weist die Leuchtgranate einen Dichtring 17 auf. Der Abschuß erfolgt durch Zündung einer Treibpatrone 4, worauf auch die Ladung der Teilladungskörper 6 zündet. Es können maximal sechs solche Teilladungskörper 6 angebracht werden; zur Erzielung geringerer Schußweiten kann die Anzahl der Teilladungskörper 6 auch entsprechend verringert werden.The light grenade is fired from a corresponding tube. The fluorescent grenade has a sealing ring 17 for sealing the tube. The shot is fired by firing a propellant cartridge 4, whereupon the charge of the partial charge body 6 also ignites. A maximum of six such partial load bodies 6 can be attached; In order to achieve smaller shot widths, the number of part-load bodies 6 can also be reduced accordingly.

Erfindungsgemäß wird für die Treibpatrone 4 gerolltes Plattenpulver M8 (eingetragenes Warenzeichen) verwendet, das ist ein zweibasiges Plattenpulver. Dieses Pulver hat sich als sehr zündkräftig erwiesen. Wenn die Treibpatrone 4 wasserdicht ausgeführt ist, wie das bekannt ist, so wird, wenn dieses Pulver verwendet wird, bei äußerer Nässe die Schußweite nicht oder nur unwesentlich vermindert. Für die Teilladungskörper 6 wird Schüttpulver, in wasserdichten Zelluloidkörpern verpackt, verwendet.According to the invention, rolled plate powder M8 (registered trademark) is used for the drive cartridge 4, which is a two-base plate powder. This powder has proven to be very powerful. If the cartridge 4 is made watertight, as is known, when this powder is used, the range is not or only slightly reduced when it is wet outside. Bulk powder, packed in watertight celluloid bodies, is used for the partial charge body 6.

An seinem hinteren Ende weist die Leuchtgranate Stabilisator-Flügel 3 auf. Diese Stabilisator-Flügel 3 sind an ihrem vorderen Ende abgeschrägt; im Bereich dieser Abschrägung 22 ist die Kante der Stabilisator-Flügel 3 dachkantenartig abgeschrägt. Der Winkel zwischen der Abschrägung 22 und der Achse der Leuchtgranate beträgt erfindungsgemäß etwa 50°. Im restlichen Bereich 23 der Stabilisator-Flügel 3 ist deren Kante nicht exakt gerade und parallel zur Achse der Leuchtgranate, sondern erfindungsgemäß leicht konvex gekrümmt. Bei einer Abmessung der Stabilisator-Flügel 3 von 80 mm hat sich ein Krümmungsradius von 150 mm als sehr günstig erwiesen. Die maximale Flugweite der Leuchtgranate wird durch diese Flügelform gesteigert. Diese Stabilisator-Flügel 3 liefern einen optimalen Auftrieb, was das Flugverhalten positiv beeinflußt, tragen jedoch kaum zum Gesamtluftwiderstand bei.At its rear end, the light grenade has stabilizer wing 3. These stabilizer blades 3 are chamfered at their front end; in the area of this bevel 22, the edge of the stabilizer wing 3 is beveled like a roof edge. According to the invention, the angle between the bevel 22 and the axis of the illuminated grenade is approximately 50 °. In the remaining area 23 of the stabilizer wing 3, the edge thereof is not exactly straight and parallel to the axis of the illuminated grenade, but is slightly convex in accordance with the invention. With a stabilizer wing 3 dimension of 80 mm, a radius of curvature of 150 mm has proven to be very favorable. The maximum flight range of the illuminated grenade is increased by this wing shape. These stabilizer wings 3 provide optimal lift, which has a positive influence on the flight behavior, but hardly contribute to the overall air resistance.

Claims (1)

  1. Star shell with an igniter, an expelling charge housed in a small dish, an illuminant which is fixed to a parachute, the rear end of the star shell having a propellant cartridge, a partial charge body and stabiliser fins, the front end of the stabiliser fins being bevelled and the edge in the region of the bevelling being bevelled in a ridge-shaped manner, characterised in that the propellant cartridge (4) is filled with a dibasic, rolled compacted powder, that the angle between the bevelling (22) of the stabiliser fins (3) and the axis of the star shell is approximately 50°, that the outer contour of the stabilizer fins (3) in the region (23) underneath the bevelling (22) is convex, that the small dish (13) containing the expelling charge has openings (25) which are covered on the inside by a foil, preferentially an aluminium foil, so that predetermined points of break are produced, that the igniter (5) is fixed to the front casing portion (1) via a steel adapter (16) and that a time-delay element (18) is arranged between the expelling charge (11) and the illuminant (7).
EP19870890276 1986-12-04 1987-12-03 Flare-carrying projectile Expired - Lifetime EP0271480B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT323386A AT396992B (en) 1986-12-04 1986-12-04 LUMINOUS GRENADE
AT3233/86 1986-12-04

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EP0271480A2 EP0271480A2 (en) 1988-06-15
EP0271480A3 EP0271480A3 (en) 1989-05-10
EP0271480B1 true EP0271480B1 (en) 1993-10-13

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Application Number Title Priority Date Filing Date
EP19870890276 Expired - Lifetime EP0271480B1 (en) 1986-12-04 1987-12-03 Flare-carrying projectile

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EP (1) EP0271480B1 (en)
AT (1) AT396992B (en)
DE (1) DE3787792D1 (en)

Cited By (2)

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Publication number Priority date Publication date Assignee Title
US7469640B2 (en) 2006-09-28 2008-12-30 Alliant Techsystems Inc. Flares including reactive foil for igniting a combustible grain thereof and methods of fabricating and igniting such flares
CN111238310A (en) * 2020-01-21 2020-06-05 北京理工大学 Capacitive armored vehicle vibration measuring device and measuring method thereof

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DE3835150A1 (en) * 1988-10-15 1990-04-26 Diehl Gmbh & Co FLOOR WITH AN EXHAUST
CN101949669B (en) * 2010-08-10 2013-03-13 吉林保利科技中试有限公司 Microtelevision reconnaissance projectile of 60mm mortar
CN102162712A (en) * 2010-12-20 2011-08-24 吉林保利科技中试有限公司 63-1 type 60mm mortar star shell

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US1347125A (en) * 1919-02-28 1920-07-20 Schneider & Cie Projectile for bomb-throwers
US2120246A (en) * 1935-11-27 1938-06-14 Max W Fischer Pyrotechnic device
DE713464C (en) * 1936-05-29 1941-11-07 Deutsches Reich Vertreten Durc Bullet, especially a mine
DE1091002B (en) * 1959-09-30 1960-10-13 Baronin Ilyana Von Thyssen Bor Propellant cartridge for grenade launcher projectiles
AT224510B (en) * 1961-09-29 1962-11-26 Heinrich Fister Ignition cartridge
BE773633A (en) * 1970-04-10 1972-01-31 Foerenade Fabriksverken PROPULSION CHARGE, ESPECIALLY FOR LARGE DIAMETER AMMUNITION
DE2142076A1 (en) * 1971-08-21 1973-03-01 Friedrich W Odenberg Spiral wound solid fuel propellant core - for rocket propulsion units
SE373939B (en) * 1973-06-21 1975-02-17 Bofors Ab
FR2260772B1 (en) * 1974-02-08 1976-06-25 France Etat
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GB8709802D0 (en) * 1987-04-24 1987-05-28 Haircloth Weaving & Finishing Sheet material

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7469640B2 (en) 2006-09-28 2008-12-30 Alliant Techsystems Inc. Flares including reactive foil for igniting a combustible grain thereof and methods of fabricating and igniting such flares
US7690308B2 (en) 2006-09-28 2010-04-06 Alliant Techsystems Inc. Methods of fabricating and igniting flares including reactive foil and a combustible grain
CN111238310A (en) * 2020-01-21 2020-06-05 北京理工大学 Capacitive armored vehicle vibration measuring device and measuring method thereof

Also Published As

Publication number Publication date
EP0271480A3 (en) 1989-05-10
DE3787792D1 (en) 1993-11-18
ATA323386A (en) 1993-05-15
AT396992B (en) 1994-01-25
EP0271480A2 (en) 1988-06-15

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