EP0271480B1 - Projectile à fusée éclairante - Google Patents

Projectile à fusée éclairante 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
Authority
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
Other languages
German (de)
English (en)
Other versions
EP0271480A2 (fr
EP0271480A3 (en
Inventor
Peter Schödlbauer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hirtenberger AG
Original Assignee
Hirtenberger AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hirtenberger AG filed Critical Hirtenberger AG
Publication of EP0271480A2 publication Critical patent/EP0271480A2/fr
Publication of EP0271480A3 publication Critical patent/EP0271480A3/de
Application granted granted Critical
Publication of EP0271480B1 publication Critical patent/EP0271480B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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.

Landscapes

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

Claims (1)

  1. Grenade éclairante comprenant un détonateur, une charge d'éjection logée dans une cuvette, un élément éclairant qui est fixé à un parachute, la grenade éclairante comportant à son extrémité arrière une cartouche propulsive, des éléments de charge fractionnaire et des ailettes de stabilisation, l'extrémité antérieure de ces ailettes de stabilisation étant inclinée et l'arête dans la région de l'inclinaison étant chanfreinée à la manière d'un toit, caractérisée en ce que la cartouche propulsive (4) est garnie d'une poudre à double base, comprimée en galette, en ce que l'angle de l'inclinaison (22) des ailettes de stabilisation (3) par rapport à l'axe de la grenade éclairante est d'environ 50°, en ce que le contour extérieur des ailettes de stabilisation (3) dans la zone (23) derrière l'inclinaison (22) présente un courbure convexe, en ce que la cuvette (13) contenant la charge d'éjection comporte des lumières (25) qui sont couvertes sur la face intérieure par une feuille, de préférence une feuille d'aluminium, de sorte qu'il existe des emplacements de rupture, en ce que le détonateur (5) est fixé à une pièce antérieure de boîtier (1) par un raccord d'adaptation en acier (16) et en ce qu'un élément retardateur (18) est monté entre la charge d'éjection (11) et l'élément éclairant (7).
EP19870890276 1986-12-04 1987-12-03 Projectile à fusée éclairante Expired - Lifetime EP0271480B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT323386A AT396992B (de) 1986-12-04 1986-12-04 Leuchtgranate
AT3233/86 1986-12-04

Publications (3)

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

Family

ID=3547441

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870890276 Expired - Lifetime EP0271480B1 (fr) 1986-12-04 1987-12-03 Projectile à fusée éclairante

Country Status (3)

Country Link
EP (1) EP0271480B1 (fr)
AT (1) AT396992B (fr)
DE (1) DE3787792D1 (fr)

Cited By (2)

* 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
CN111238310A (zh) * 2020-01-21 2020-06-05 北京理工大学 一种电容式装甲车辆振动测量装置及其测量方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3835150A1 (de) * 1988-10-15 1990-04-26 Diehl Gmbh & Co Geschoss mit einer ausstossladung
CN101949669B (zh) * 2010-08-10 2013-03-13 吉林保利科技中试有限公司 60毫米迫击炮微型电视侦察弹
CN102162712A (zh) * 2010-12-20 2011-08-24 吉林保利科技中试有限公司 63-1式60毫米迫击炮照明弹

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1250305B (fr) *
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 (de) * 1936-05-29 1941-11-07 Deutsches Reich Vertreten Durc Geschoss, insbesondere Wurfmine
DE1091002B (de) * 1959-09-30 1960-10-13 Baronin Ilyana Von Thyssen Bor Treibladungspatrone fuer Granatwerfergeschosse
AT224510B (de) * 1961-09-29 1962-11-26 Heinrich Fister Zündpatrone
BE773633A (fr) * 1970-04-10 1972-01-31 Foerenade Fabriksverken Charge de propulsion, notamment pour des munitions de grand diametre
DE2142076A1 (de) * 1971-08-21 1973-03-01 Friedrich W Odenberg Im wickelverfahren herzustellende feststofftreibsaetze fuer selbstvortriebgeschosse und raketen
SE373939B (fr) * 1973-06-21 1975-02-17 Bofors Ab
FR2260772B1 (fr) * 1974-02-08 1976-06-25 France Etat
NO147159L (fr) * 1979-09-08 1900-01-01
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 (zh) * 2020-01-21 2020-06-05 北京理工大学 一种电容式装甲车辆振动测量装置及其测量方法

Also Published As

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

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