EP0434549B1 - Haltesystem für am Trägergeschoss angebrachte Submunition - Google Patents

Haltesystem für am Trägergeschoss angebrachte Submunition Download PDF

Info

Publication number
EP0434549B1
EP0434549B1 EP90403653A EP90403653A EP0434549B1 EP 0434549 B1 EP0434549 B1 EP 0434549B1 EP 90403653 A EP90403653 A EP 90403653A EP 90403653 A EP90403653 A EP 90403653A EP 0434549 B1 EP0434549 B1 EP 0434549B1
Authority
EP
European Patent Office
Prior art keywords
strap
barrel
straps
barrels
carrier
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
EP90403653A
Other languages
English (en)
French (fr)
Other versions
EP0434549A1 (de
Inventor
Jean-François Denis
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0434549A1 publication Critical patent/EP0434549A1/de
Application granted granted Critical
Publication of EP0434549B1 publication Critical patent/EP0434549B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • the present invention relates to systems for retaining submunitions on board vectors such as rockets, missiles, etc., these systems being of the strap type.
  • these are generally housed in individual compartments or receptacles, associated with an ejection means such as an airbag, and immobilized for transport by retaining means which are released for ejection.
  • an ejection means such as an airbag
  • the release of the retaining means is obtained by rupture: the submunitions are surrounded by straps having weakened zones, or wedged by screws breaking under traction. Compared to the previous ones, these systems have the advantage that the release is caused by the ejection pulse itself.
  • the object of the invention is to provide a system for retaining submunitions in a vector, the release of which induces shocks and stresses as low as possible.
  • the present invention aims to provide such a system which makes it possible to subject the submunitions at several points, so as to have a satisfactory distribution of the forces thereon, without this multiple subjugation having a harmful influence on the 'ejection.
  • the subject of the invention is a vector comprising a system for retaining submunitions as defined in claims 1 to 8.
  • all the barrels are coupled in series by means of connecting bars, and all the barrels are connected to a single resistant torque generating device to which associated with said torque limiting device.
  • the barrels are divided into two identical groups in each of which they are coupled in series, the two groups being connected respectively to one and to the other of two identical resistive torque generating devices, connected to a single torque limiting device, on each side thereof.
  • the barrels are divided into two identical groups in each of which they are coupled in series, the two groups being connected respectively to one and to the other of two identical resistive torque generating devices, connected to a single torque limiting device, on each side thereof.
  • the barrels act perfectly identical and perfectly synchronous, so that on the submunitions, the forces produced by the restraint system are well distributed, and that ejection, the straps are released perfectly concomitantly.
  • the vector for transporting submunitions represented in the drawings conventionally comprises a basic structure defining around the longitudinal axis X a plurality of compartments or receptacles 1 bounded by two radial walls 1a and 1b, and closed by an integrated external wall 1c to the fuselage.
  • a compartment. 1 on the radial walls 1a and 1b, are provided supports 2 on which rest the submunitions 3.
  • ejection means such as air bags, not shown.
  • Each submunition 3 is secured in its own compartment by a strap 4 or, more often, by a group of such straps distributed longitudinally.
  • Each of the straps 4 is fixed, by a first end 4a, to a hooking means 5 mounted on one of the radial partitions la of the compartment, towards the outside relative to the support 2.
  • the attachment means 5 is provided with a device allowing a progressive tensioning of the strap, for example by screwing.
  • a barrel 6 of axis parallel to the longitudinal axis X of the vector and having at its periphery a groove 7 oriented along a generator and intended to receive an element 8 of complementary shape, which is integral with the second end 4b of the strap 4, the element 8 forming a means of engagement of the strap 4 in the barrel 6.
  • the barrel 6 is mounted in a yoke 9, a wall 9a of which covers part of the circumference, at a distance slightly greater than the thickness of the strap 4.
  • the barrel 6 is made integral with a device 10 generating a torque resistant to the tension exerted on the strap 4.
  • this device is a torsion bar 10.
  • At the other end of the bar 10, is associated with a torque limiting device 11 which, beyond a predetermined threshold, releases it in rotation on itself.
  • a strap 4 is put in place by first housing, from the side, the element 8 secured to its second end 4b in the groove 7 of the barrel, in the position of FIG. 4a. The other end 4a of the strap is then hooked to the means 5.
  • a tension represented by the arrow F1 in FIG. 4b is exerted on the strap 4, for example by screwing as previously mentioned, which has the effect of moving the barrel 6 in rotation, to a locking position, FIG. 4b, against the resisting torque F2 of the torsion bar 10.
  • This locking position is fairly clearly below the release position, illustrated by the groove 7 in dashed lines, which corresponds to the resisting torque threshold for which the device 11 releases the bar 10 in rotation on itself.
  • the ammunition 3 is attached with a plurality of straps 4 distributed longitudinally, only two of which are shown.
  • the barrels 6, in their respective yokes 9, are all aligned and coupled in series by means of connecting bars. They therefore form an assembly, connected to the torsion bar 10 on the other side with respect to the torque limiter 11, in which they operate in a perfectly identical and perfectly simultaneous manner, from the fact that at all times their angular position in rotation is substantially the same for all.
  • the submunition 3 is only secured by two straps 4.
  • the two corresponding barrels 6 are then each connected to a clean torsion bar, respectively 10a and 10b, the two bars being identical and associated with the torque limiter 11 , opposite one another.
  • the barrels will act, as in the embodiment of FIG. 2, perfectly identical and perfectly simultaneous.
  • Figs. 5 to 8 illustrate a development of the invention, offering the possibility of ejecting submunitions with a certain incidence relative to the trajectory of the vector, and of controlling this incidence.
  • the submunition 3 of FIG. 5 is secured in its receptacle 1 by a front strap 40 and a rear strap 41, to which correspond the barrels 60 and 61 of FIG. 6, or, alternatively, those of FIG. 7.
  • An ejection means such as an inflatable bag is disposed between the submunition 3 and the bottom of the receptacle 1.
  • Fig. 6 the barrels 60 and 61 are shown in the locked state.
  • the angular positions of their notches, respectively 70 and 71 are different, namely that the angle ⁇ 0 is smaller than the angle ⁇ 1 and, consequently, the angular positions of the grooves at the time of unlocking, shown in broken lines, are shifted accordingly. It follows that from the simultaneous unlocking of the two barrels, the angular strokes of the notches 70 and 71, and therefore of the elements 80 and 81 at the ends of the straps 40 and 41, until complete release on passage of the upper ends of the walls 90a, 91a, will be different.
  • one of the straps here the front strap 40
  • the ejection means will give a certain incidence ⁇ to the submunition 3, the value of which will depend on the difference ⁇ 1 - ⁇ 0, on the one hand, and the spacing L between the straps 40 and 41, on the other hand.
  • the angular offset will be obtained during assembly.
  • the strap 40 will be provided slightly shorter than the strap 41.
  • the offset will be obtained, here again with straps of different lengths, by stretching one of the straps more than the other, or else, if it is preferred that the tensions of the two straps are substantially equal, by choosing non-identical torsion bars 10a and 10b.
  • Fig. 7 illustrates another means of obtaining delayed complete release of the two straps 40 and 41.
  • the difference in angular travel of the elements 80 and 81 between the unlocked position and the fully released position is obtained by the fact that the walls 90a and 91a of the yokes 90 and 91 stop at different heights, the value of the angle of incidence printed on the submunition then being a function of the difference in height H, FIG. 7, and the spacing L of the straps 40 and 41.
  • the barrels 60 and 61 are mounted and used exactly as in the systems of FIGS. 2 and 3.
  • FIG. 8 An application in which the arrangement which has just been described is particularly advantageous is shown in FIG. 8: a vector transports a plurality of submunitions 3, which must be ejected simultaneously. By printing different incidences to them on ejection, a better distribution is achieved, and thereby a better spread over the area to be saturated.
  • the invention in addition to providing considerably improved stowage and ejection conditions for submunitions, therefore offers a wider range of possibilities, with the additional advantage, already mentioned, that no adjustment is necessary on the submunition itself.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Purses, Travelling Bags, Baskets, Or Suitcases (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Transmission Devices (AREA)
  • Prostheses (AREA)

Claims (8)

  1. Flugkörper mit einem Haltesystem für Munitionskörper (3), die auf dem Flugkörper transportiert werden, wobei das Haltesystem ein Gurtsystem (4) ist und ein erstes Ende (4a) des Gurts (4) am Flugkörper über ein Mittel (5) zum Gurtstraffen verankert ist, dadurch gekennzeichnet, daß jeder Gurt einen Munitionskörper (3) in einem Behälter (1) des Flugkörpers festhält, daß der Behälter mindestens zwei Wände (1a, 1b) aufweist, wobei das erste Ende (4a) des Gurts an einer ersten dieser Wände (1a) über das Mittel zum Gurtstraffen befestigt ist, während das zweite Ende (4b) ein Mittel (8) zur Kopplung mit einem Walzenschloß (6) aufweist, das auf der zweiten Wand (1b) des Behälters montiert ist, daß das Walzenschloß mit einer Vorrichtung (10) verbunden ist, die ein Widerstandsmoment bei der Drehung des Walzenschlosses in Richtung der Straffung des Gurts erzeugt, und daß die Vorrichtung (10) zur Erzeugung des Widerstandsmoments ihrerseits mit einer Vorrichtung zur Drehmomentbegrenzung (11) verbunden ist, die bei einem bestimmten Schwellwert auslöst und die Drehung des Walzenschlosses (6) freigibt, um das zweite Ende (4b) des Gurtes (4) freizugeben.
  2. Flugkörper nach Anspruch 1, dadurch gekennzeichnet, daß alle Walzenschlösser (6) in Reihe über Verbindungsstangen (12) gekoppelt sind und die Gesamtheit der Walzenschlösser (6) an eine gemeinsame Vorrichtung (10) zur Erzeugung eines Widerstandsmoments angeschlossen sind, der die Vorrichtung (11) zur Drehmomentbegrenzung zugeordnet ist.
  3. Flugkörper nach Anspruch 1, dadurch gekennzeichnet, daß die Walzenschlösser (6) in zwei gleiche Gruppen aufgeteilt sind und innerhalb ihrer Gruppe in Reihe gekoppelt sind, wobei die beiden Gruppen je an eine der beiden identischen Vorrichtungen zur Erzeugung eines Widerstandsmoments angeschlossen sind und diese mit einer gemeinsamen Vorrichtung zur Drehmomentbegrenzung an dessen beiden Seiten verbunden sind.
  4. Flugkörper nach Anspruch 1, dadurch gekennzeichnet, daß er zwei Walzenschlösser (6) aufweist, die an je eine von zwei Vorrichtungen zur Erzeugung identischer Widerstandsmomente (10a, 10b) angeschlossen sind, die ihrerseits mit einer gemeinsamen Vorrichtung zur Drehmomentbegrenzung (11) zu beiden Seiten dieser Vorrichtung verbunden sind.
  5. Flugkörper nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die Vorrichtungen zur Erzeugung eines Widerstandsmoments (10) Torsionsstäbe sind.
  6. Flugkörper nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die Vorrichtungen zum Straffen der Gurte (4) Schraubvorrichtungen sind.
  7. Flugkörper nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß der Sockel (9) jedes Walzenschlosses (6) ein Mittel (9a) aufweist, um das Ende (4a) des entsprechenden Gurts im Walzenschloß festzuhalten, und zwar bis zu einer Stellung jenseits der Stellung, die erreicht wird, wenn das Walzenschloß in Drehrichtung von der Drehmomentbegrenzungsvorrichtung (11) freigegeben wurde.
  8. Flugkörper nach Anspruch 7, dadurch gekennzeichnet, daß er mindestens zwei Gurte (40, 41) besitzt, daß das Mittel (8) zum Koppeln jedes Gurts sich in einer Nut (7) des Walzenschlosses (6) befindet und daß im Walzenschloß (61), das einem der Gurte zugeordnet ist, die Winkelstrecke der Nut (71) zwischen der Stellung, die sie bei der Verriegelung der Walzenschlösser (60, 61) einnimmt, und der Stellung der vollkommenen Freigabe der Gurte gegenüber dem Ende der Mittel (9a) länger ist als in den den anderen Gurten zugewiesenen Walzenschlössern, um dem Munitionskörper beim Auswurf bezüglich der Bahn des ihn transportierenden Flugkörpers einen Winkel zu verleihen.
EP90403653A 1989-12-22 1990-12-18 Haltesystem für am Trägergeschoss angebrachte Submunition Expired - Lifetime EP0434549B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8917088A FR2656414B1 (fr) 1989-12-22 1989-12-22 Systemes de retenue de sous-munitions embarquees dans un vecteur.
FR8917088 1989-12-22

Publications (2)

Publication Number Publication Date
EP0434549A1 EP0434549A1 (de) 1991-06-26
EP0434549B1 true EP0434549B1 (de) 1994-08-17

Family

ID=9388891

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90403653A Expired - Lifetime EP0434549B1 (de) 1989-12-22 1990-12-18 Haltesystem für am Trägergeschoss angebrachte Submunition

Country Status (5)

Country Link
US (1) US5078053A (de)
EP (1) EP0434549B1 (de)
CA (1) CA2032544A1 (de)
DE (1) DE69011641T2 (de)
FR (1) FR2656414B1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2753786B1 (fr) * 1996-09-20 1998-12-11 Dispositif pour l'arrimage a l'interieur d'un conteneur de sous-munitions embarquees
US6672220B2 (en) 2001-05-11 2004-01-06 Lockheed Martin Corporation Apparatus and method for dispersing munitions from a projectile

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2395913A (en) * 1942-09-18 1946-03-05 Schultze Fred Cluster bomb rack

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US395913A (en) * 1889-01-08 Hammer for fire-arms
US2690122A (en) * 1945-11-15 1954-09-28 Us Navy Bomb cluster
US2604043A (en) * 1946-05-16 1952-07-22 Foster Wheeler Corp Bomb
US2972946A (en) * 1950-07-07 1961-02-28 Thomas C Poulter Bomb cluster
US3513512A (en) * 1968-10-21 1970-05-26 G & H Technology Fastening assembly with quick release
DE3142313A1 (de) * 1981-10-24 1983-05-05 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
DE3301873A1 (de) * 1983-01-21 1984-07-26 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
FR2562998B1 (fr) * 1984-04-13 1988-07-29 Alkan R & Cie Sangle largable de torpille
FR2617464B1 (fr) * 1987-07-03 1990-02-16 Thomson Brandt Armements Dispositif de fermeture ejectable, notamment pour roquettes a sous-munitions

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2395913A (en) * 1942-09-18 1946-03-05 Schultze Fred Cluster bomb rack

Also Published As

Publication number Publication date
DE69011641D1 (de) 1994-09-22
CA2032544A1 (fr) 1991-06-23
FR2656414A1 (fr) 1991-06-28
FR2656414B1 (fr) 1993-01-22
US5078053A (en) 1992-01-07
DE69011641T2 (de) 1994-11-24
EP0434549A1 (de) 1991-06-26

Similar Documents

Publication Publication Date Title
EP0424198B1 (de) Trägergeschoss mit einem Modulbehälter zum Abwerfen von Submunitionskörpern
EP0270401B1 (de) Trägergeschoss zum Abwerfen von Tochtergeschossen in kontrollierter Weise
FR2664038A1 (fr) Dispositif pour deverrouiller et deployer les surfaces de gouverne d'un projectile.
EP0541411B1 (de) Vorrichtung zum Auswerfen der Submunitionen aus einem Trägergeschoss
EP0690284B1 (de) Aufspreizvorrichtung für den Flügel eines Geschosses
EP1006335B1 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
EP1045221B1 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
EP0130893B1 (de) Trägergeschoss für Streumunition
EP0434549B1 (de) Haltesystem für am Trägergeschoss angebrachte Submunition
EP0277445B1 (de) Trägergeschoss zum Belegen einer vorgewählten Fläche mit Streumunition
EP0539257B1 (de) Trägergeschoss
WO2006048565A1 (fr) Dispositif de commande du deploiement de structures gonflables
EP0235028B1 (de) Zündeinrichtung für Raketendüsen
FR2514124A1 (fr) Munitions reunies en botte, pouvant etre ejectees de conteneurs
EP2863164B1 (de) Rotationsbremsvorrichtung eines Mantels einer Nutzlast, und drallstabilisiertes Geschoss, das mit einer solchen Vorrichtung ausgestattet ist
EP0367815B1 (de) Aerodynamische bremsvorrichtung für einen körper
FR2647892A1 (fr) Aileron deployable de missile
EP1034411B1 (de) Generator zur pyrotechnischen erzeugung von akustischen druckwellen zum schutz von schiffen und unterseeboten
EP0546888B1 (de) Geschosshülle, bei der der Boden Fallschirmbehälter für eine Submunition ist
FR2769083A1 (fr) Procede de guidage d'un missile et missile pour la mise en oeuvre du procede
FR2654822A1 (fr) Dispenseur de sous-projectiles.
EP0831292B1 (de) Vorrichtung zur Befestigung von in einem Behälter angebrachter Submunition
EP3720771B1 (de) Verfahren zum ausstossen einer nutzlast von einem mit kontinuierlicher antriebskraft angetriebenen raumfahrzeug
FR2640372A1 (fr) Munition d'interdiction de zone et projectile equipe
FR2724222A1 (fr) Engin volant, notamment missile ou roquette, comprenant deux parties separables sur trajectoire

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE GB IT SE

17P Request for examination filed

Effective date: 19911220

17Q First examination report despatched

Effective date: 19921207

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE GB IT SE

ITF It: translation for a ep patent filed

Owner name: JACOBACCI CASETTA & PERANI S.P.A.

REF Corresponds to:

Ref document number: 69011641

Country of ref document: DE

Date of ref document: 19940922

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19941024

EAL Se: european patent in force in sweden

Ref document number: 90403653.0

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19951121

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19951123

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19961218

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19961219

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19961218

EUG Se: european patent has lapsed

Ref document number: 90403653.0

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20031229

Year of fee payment: 14

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050701

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20051218