EP0421873A1 - Device for the braking of a bomb after its release from an aircraft - Google Patents

Device for the braking of a bomb after its release from an aircraft Download PDF

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Publication number
EP0421873A1
EP0421873A1 EP90402733A EP90402733A EP0421873A1 EP 0421873 A1 EP0421873 A1 EP 0421873A1 EP 90402733 A EP90402733 A EP 90402733A EP 90402733 A EP90402733 A EP 90402733A EP 0421873 A1 EP0421873 A1 EP 0421873A1
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EP
European Patent Office
Prior art keywords
bomb
propellant
cap
cover
jet
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Granted
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EP90402733A
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German (de)
French (fr)
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EP0421873B1 (en
Inventor
Michel Mulleman
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Individual
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Individual
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Priority to AT90402733T priority Critical patent/ATE89073T1/en
Publication of EP0421873A1 publication Critical patent/EP0421873A1/en
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Publication of EP0421873B1 publication Critical patent/EP0421873B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding

Definitions

  • the invention relates to the dropping of bombs or other munitions from an aircraft and, more particularly, the control of the trajectory of the bombs after they have been dropped.
  • braking ensures the bomb better stability of its trajectory and, by increasing its angle of impact with respect to the ground, eliminates the risks of ricochet and gives it increased efficiency.
  • the object of the present invention is to remedy the drawbacks presented by known devices for braking bombs dropped from an aircraft and to this end it provides a device which, while being very simple, reliably ensures braking. effective of the bomb as soon as it is dropped.
  • the braking of the dropped bomb is ensured by a propellant associated with the bomb and whose gas jet is oriented towards the front of the latter to ensure a back-propelling effect.
  • the orientation of the jet of the propellant towards the front can, for example, be obtained by a system comprising pipes connected to the output of the propellant and wrapped in a cap supporting hatches which are deployable, under the action of the jet, between a retracted position corresponding to the state of rest of the propellant device and a forward inclined position orienting in this direction the jet leaving said pipes.
  • the orientation of the jet of the propellant can also be obtained by means of pipes, wrapped in a cap, which are connected to the output of the propellant and open in the extension of the bomb stabilization fins.
  • the front part of these fins is then closed by a material degradable under the effect of heat (eutectic alloy, synthetic resin) so that, when the propellant is at rest, the fins retain their aerodynamic profile and that, during the ignition of the propellant, the material is destroyed by allowing the evacuation of gases towards the front of the bomb.
  • the cap which envelops the device ensuring the forward orientation of the jet of the propellant can be automatically ejected, when the bomb has reached a predetermined position, thus causing the propulsion of the bomb in the terminal phase of its trajectory to communicate. to it an additional energy improving its effectiveness on impact against hardened objectives.
  • FIG. 1 there is shown in 1 the body of a bomb carrying at its rear part stabilizing fins 2.
  • the body 1 is equipped at its rear end of a propulsion system 3, the dimensional characteristics of which are adapted to those of the bomb.
  • a jet manifold 5 which has several pipes 6 and which is enveloped by a cap 7 conforming to the external profile of the bomb 1.
  • the cap 7 is held in position by means cables 8 which run inside the stabilization fins 2.
  • an equipment compartment 9 in which is housed a pyrotechnic device 10 connected to the cables 8 and cooperating with a device 11 measuring the speed of the bomb and selectively controlling the actuation of the pyrotechnic device 10 to ensure the cutting of the cables 8 and therefore the ejection of the cap 7.
  • the hatch 13 On the cover 7 are articulated, around axes 12, hatches 13 designed to take a retracted position before the ignition of the propulsion device 3 and to come to deploy forward under the effect of the pressure exerted by the jet leaving the pipe 6 with which the hatch 13 is associated.
  • the hatch 13 is articulated at its lower part, by an axis 14, to a moving part 15 of substantially triangular shape and comprises, also at its lower part, an axis 16 designed to cooperate with a extension 17 of the upper part of the part 15 so that the rise of the hatch 13 leads to that of the part 15.
  • the part 15 At its lower part the part 15 also has an extension 18 intended, at the end of the opening pivoting of the hatch 13, coming into abutment against a fixed part 19 to limit the pivoting of the hatch 13.
  • the pyrotechnic device After a predetermined period of time, corresponding to a drop in the speed of the bomb measured by the device 11, the pyrotechnic device is automatically controlled to ensure the cutting of the cables 8 and therefore the ejection of the cap 6 and the hatches 13 carried by it. Bomb 1 is thus propelled in the final part of its trajectory, which makes it possible to increase its impact effectiveness against hardened targets.
  • FIG. 4 to 6 there is shown a second embodiment of the device according to the invention.
  • a propellant device 23 comprising a nozzle 24 in the extension of which is disposed the jet manifold 25 with several pipes 26.
  • the manifold 25 is enveloped by the cap 27 which follows the external profile of the bomb 21 and which is held in position by the cables 28 traveling inside the fins 22 for stabilizing the bomb 21.
  • the pyrotechnic device connected to the cables 28 and housed inside the box with equipment 29, and at 31 the device measuring the speed of the bomb 21.
  • each pipe 26 forms a bend to be oriented towards the front of the bomb, and cooperates with the rear end of a fin 22 which serves as a final conduit.
  • the front part 32 of each fin 22 is closed by a thermally degradable material so that these fins maintain their aerodynamic profile during the ballistic phase of the trajectory, then that this material is then destroyed during the firing of the propellant device 23 thus allowing the evacuation of gases towards the front of the bomb and therefore the desired effect of back-propelling braking.
  • the measuring device 31 and the pyrotechnic device 30 control the cutting of the cables 28, and therefore the ejection of the cap 27 and of the conduits 26 which it maintains, so that the bomb is propelled during the final part of its trajectory.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid Mechanics (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Regulating Braking Force (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Valves And Accessory Devices For Braking Systems (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Braking Systems And Boosters (AREA)
  • Braking Arrangements (AREA)

Abstract

The bomb body is equipped at its rear end with a propulsion unit 3, at the outlet of which is arranged a jet collector 5 having a plurality of conduits 6 and encased in a cover 7. The cover 7 is kept in position by cables 8. Articulated on the cover 7 are traps 13 which, under the effect of the pressure of the jet issuing from the conduits 6, are unfolded forwards over a limited stroke, thereby deflecting said jet forwards in order to ensure the drag of the bomb. After a reduction in speed of the bomb, measured by a device 11, a pyrotechnic system 10 is controlled so as to ensure the severance of the cables 8 and therefore the ejection of the cover 7 and the restoration of the propulsion of the bomb. The device automatically ensures the braking back of a bomb after its release and the restoration of the propulsion of the latter when the speed of the bomb is below a predetermined value. <IMAGE>

Description

L'invention concerne le largage de bombes ou autres munitions à partir d'un aéronef et, plus particulièrement, le contrôle de la trajectoire des bombes après leur largage.The invention relates to the dropping of bombs or other munitions from an aircraft and, more particularly, the control of the trajectory of the bombs after they have been dropped.

Le tir d'une bombe à partir d'un aéronef exige, lorsque l'altitude de largage est faible, que cette bombe soit freinée. En effet, sans cette précaution, l'avion tireur risque d'être atteint par des éclats de la bombe car ils se trouve pratiquement à la verticale de l'impact.Firing a bomb from an aircraft requires, when the drop altitude is low, that bomb to be braked. Indeed, without this precaution, the gunner plane risks being hit by bomb fragments because they are practically vertical to the impact.

De plus, le freinage assure à la bombe une meilleure stabilité de sa trajectoire et, en augmentant son angle d'impact par rapport au sol, supprime les risques de ricochet et lui confère unes efficacité accrue.In addition, braking ensures the bomb better stability of its trajectory and, by increasing its angle of impact with respect to the ground, eliminates the risks of ricochet and gives it increased efficiency.

Différents dispositifs de freinage ont déjà été proposés à base de parachutes, de ballonnets gonflables où d'ailettes déployables. Cependant ces dispositifs manquent souvent d'efficacité et de fiabilité.Different braking devices have already been proposed based on parachutes, inflatable balloons or deployable fins. However, these devices often lack efficiency and reliability.

La présente invention a pour objet de remédier aux inconvénients présentés par les dispositifs connus de freinage de bombes larguées à partir d'un aéronef et elle propose à cet effet un dispositif qui, tout en étant d'une grande simplicité, assure avec fiabilité le freinage efficace de la bombe dès le largage de celle-ci.The object of the present invention is to remedy the drawbacks presented by known devices for braking bombs dropped from an aircraft and to this end it provides a device which, while being very simple, reliably ensures braking. effective of the bomb as soon as it is dropped.

Selon l'invention, le freinage de la bombe larguée est assuré par un propulseur associé à la bombe et dont le jet de gaz est orienté vers l'avant de celle-ci pour assurer un effet de rétropropulsion.According to the invention, the braking of the dropped bomb is ensured by a propellant associated with the bomb and whose gas jet is oriented towards the front of the latter to ensure a back-propelling effect.

L'orientation du jet du propulseur vers l'avant peut, par exemple, être obtenue par un système comprenant des canalisations branchées à la sortie du propulseur et enveloppées dans une coiffe supportant des trappes qui sont déployables, sous l'action du jet, entre une position rétractée correspondant à l'état de repos du dispositif propulseur et une position inclinée vers l'avant orientant dans cette direction le jet sortant desdites canalisations.The orientation of the jet of the propellant towards the front can, for example, be obtained by a system comprising pipes connected to the output of the propellant and wrapped in a cap supporting hatches which are deployable, under the action of the jet, between a retracted position corresponding to the state of rest of the propellant device and a forward inclined position orienting in this direction the jet leaving said pipes.

L'orientation du jet du propulseur peut aussi être obtenue au moyen de canalisations, enveloppées dans une coiffe, qui sont branchées à la sortie du propulseur et débouchent dans le prolongement des ailettes de stabilisation de la bombe. La partie avant de ces ailettes est alors obturée par un matériau dégradable sous l'effet de la chaleur (alliage eutectique, résine synthétique) de façon que, lorsque le propulseur est au repos, les ailettes conservent leur profil aérodynamique et que, lors de la mise à feu du propulseur, le matériau soit détruit en permettant l'évacuation des gaz vers l'avant de la bombe.The orientation of the jet of the propellant can also be obtained by means of pipes, wrapped in a cap, which are connected to the output of the propellant and open in the extension of the bomb stabilization fins. The front part of these fins is then closed by a material degradable under the effect of heat (eutectic alloy, synthetic resin) so that, when the propellant is at rest, the fins retain their aerodynamic profile and that, during the ignition of the propellant, the material is destroyed by allowing the evacuation of gases towards the front of the bomb.

Avantageusement, la coiffe qui enveloppe le dispositif assurant l'orientation vers l'avant du jet du propulseur peut être éjectée automatiquement, lorsque la bombe a atteint une position prédéterminée, provoquant ainsi la propulsion de la bombe dans la phase terminale de sa trajectoire pour communiquer à celle-ci une énergie supplémentaire améliorant son efficacité à l'impact contre des objectifs durcis.Advantageously, the cap which envelops the device ensuring the forward orientation of the jet of the propellant can be automatically ejected, when the bomb has reached a predetermined position, thus causing the propulsion of the bomb in the terminal phase of its trajectory to communicate. to it an additional energy improving its effectiveness on impact against hardened objectives.

Pour bien faire comprendre le dispositif selon l'invention on en décrira ci-après, à titre d'exemples sans caractère limitatif, deux formes d'exécution préférées en référence au dessin schématique annexé dans lequel :

  • la figure 1 est une vue de côté d'une bombe équipée d'une première forme d'exécution du dispositif de freinage selon l'invention ;
  • la figure 2 est, à plus grande échelle, une vue en bout de la bombe de la figure 1 ;
  • la figure 3 est une coupe partielle prise selon la ligne III-III de la figure 2 montrant le dispositif de freinage monté à l'arrière de la bombe ;
  • la figure 4 est une vue de côté, analogue à la figure 1, d'une bombe équipée d'une seconde forme d'exécution du dispositif de freinage selon l'invention
  • la figure 5 est, à plus grande échelle, une vue en bout de la bombe de la figure 4 ;
  • la figure 6 est une coupe partielle prise selon la ligne VI-VI de la figure 5, montrant le dispositif de freinage associé à l'arrière de la bombe.
To clearly understand the device according to the invention, two preferred embodiments will be described below, by way of examples without limitation, with reference to the appended schematic drawing in which:
  • Figure 1 is a side view of a bomb equipped with a first embodiment of the braking device according to the invention;
  • Figure 2 is, on a larger scale, an end view of the bomb of Figure 1;
  • Figure 3 is a partial section taken along line III-III of Figure 2 showing the braking device mounted at the rear of the bomb;
  • Figure 4 is a side view, similar to Figure 1, of a bomb equipped with a second embodiment of the braking device according to the invention
  • Figure 5 is, on a larger scale, an end view of the bomb of Figure 4;
  • Figure 6 is a partial section taken on the line VI-VI of Figure 5, showing the braking device associated with the rear of the bomb.

En référence aux figures 1 à 3, on a représenté en 1 le corps d'une bombe portant à sa partie arrière des ailettes de stabilisation 2. Comme on l'a représenté en détail à la figure 3, le corps 1 est équipé à son extrémité arrière d'un système de propulsion 3, dont les caractéristiques dimensionnelles sont adaptées à celles de la bombe. Dans le prolongement de la tuyère 4 du système de propulsion 3 est disposé un collecteur de jet 5 qui présente plusieurs canalisations 6 et qui est enveloppé par une coiffe 7 épousant le profil extérieur de la bombe 1. La coiffe 7 est maintenue en position au moyen de câbles 8 qui cheminent à l'intérieur des ailettes de stabilisation 2. En avant du système de propulsion 3 est ménagée une case à équipement 9 dans laquelle est logé un dispositif pyrotechnique 10 relié aux câbles 8 et coopérant avec un dispositif 11 mesurant la vitesse de la bombe et commandant sélectivement l'actionnement du dispositif pyrotechnique 10 pour assurer le sectionnement des câbles 8 et donc l'éjection de la coiffe 7.Referring to Figures 1 to 3, there is shown in 1 the body of a bomb carrying at its rear part stabilizing fins 2. As shown in detail in Figure 3, the body 1 is equipped at its rear end of a propulsion system 3, the dimensional characteristics of which are adapted to those of the bomb. In the extension of the nozzle 4 of the propulsion system 3 is disposed a jet manifold 5 which has several pipes 6 and which is enveloped by a cap 7 conforming to the external profile of the bomb 1. The cap 7 is held in position by means cables 8 which run inside the stabilization fins 2. In front of the propulsion system 3 is provided an equipment compartment 9 in which is housed a pyrotechnic device 10 connected to the cables 8 and cooperating with a device 11 measuring the speed of the bomb and selectively controlling the actuation of the pyrotechnic device 10 to ensure the cutting of the cables 8 and therefore the ejection of the cap 7.

Sur la coiffe 7 sont articulées, autour d'axes 12, des trappes 13 conçues pour prendre une position escamotée avant la mise à feu du dispositif de propulsion 3 et pour venir se déployer vers l'avant sous l'effet de la pression exercée par le jet sortant de la canalisation 6 à laquelle la trappe 13 est associée. Comme on l'a représenté au dessin, la trappe 13 est articulée à sa partie inférieure, par un axe 14, à une pièce mobile 15 de forme sensiblement triangulaire et comporte, également à sa partie inférieure, un axe 16 conçu pour coopérer avec un prolongement 17 de la partie supérieure de la pièce 15 de façon que la montée de la trappe 13 entraîne celle de la pièce 15. A sa partie inférieure la pièce 15 comporte également un prolongement 18 destiné, a la fin du pivotement d'ouverture de la trappe 13, à venir en butée contre une pièce fixe 19 pour limiter le pivotement de la trappe 13.On the cover 7 are articulated, around axes 12, hatches 13 designed to take a retracted position before the ignition of the propulsion device 3 and to come to deploy forward under the effect of the pressure exerted by the jet leaving the pipe 6 with which the hatch 13 is associated. As shown in the drawing, the hatch 13 is articulated at its lower part, by an axis 14, to a moving part 15 of substantially triangular shape and comprises, also at its lower part, an axis 16 designed to cooperate with a extension 17 of the upper part of the part 15 so that the rise of the hatch 13 leads to that of the part 15. At its lower part the part 15 also has an extension 18 intended, at the end of the opening pivoting of the hatch 13, coming into abutment against a fixed part 19 to limit the pivoting of the hatch 13.

Le fonctionnement du dispositif se comprend immédiatement d'après la description qui précède. Avant le largage de la bombe 1, la trappe 13 et la pièce 15 qui lui est liée se trouvent dans la position rétractée représentée en trait mixte à la figure 3. Lorsque la bombe 1 est larguée, son dispositif de propulsion 3 est mis à feu et le jet de gaz sortant de la tuyère 4 et canalisé par les conduits 6 vient agir sur la face intérieure des trappes 13. Sous cette force chaque trappe 13 pivote vers l'avant jusqu'à sa position déployée, représentée en trait plein à la figure 3, dans laquelle elle est immobilisée par engagement du prolongement 18 de la pièce 15 sous la partie fixe 19 de la bombe. Le jet de gaz sortant des conduits 6 est alors dévié vers l'avant par les trappes 13 en assurant ainsi une rétropropulsion de la bombe provoquant une brusque décélération de celle-ci.The operation of the device is immediately understood from the above description. Before the bomb 1 is dropped, the hatch 13 and the part 15 which is linked to it are in the retracted position shown in phantom in Figure 3. When the bomb 1 is dropped, its propulsion device 3 is ignited and the gas jet leaving the nozzle 4 and channeled through the conduits 6 acts on the inside face of the hatches 13. Under this force each hatch 13 pivots forward until its deployed position, shown in solid lines at the Figure 3, in which it is immobilized by engagement of the extension 18 of the part 15 under the fixed part 19 of the bomb. The gas jet leaving the conduits 6 is then deflected forward by the hatches 13, thus ensuring a back-propulsion of the bomb causing a sudden deceleration of the latter.

Au bout d'un laps de temps prédéterminé, correspondant à une baisse de la vitesse de la bombe mesurée par le dispositif 11, le dispositif pyrotechnique est automatiquement commandé pour assurer le sectionnement des câbles 8 et donc l'éjection de la coiffe 6 et des trappes 13 portées par celle-ci. La bombe 1 se trouve ainsi propulsée dans la partie finale de sa trajectoire, ce qui permet d'augmenter son efficacité à l'impact contre des objectifs durcis.After a predetermined period of time, corresponding to a drop in the speed of the bomb measured by the device 11, the pyrotechnic device is automatically controlled to ensure the cutting of the cables 8 and therefore the ejection of the cap 6 and the hatches 13 carried by it. Bomb 1 is thus propelled in the final part of its trajectory, which makes it possible to increase its impact effectiveness against hardened targets.

En référence maintenant aux figures 4 à 6, on a représenté une seconde forme d'exécution du dispositif selon l'invention. A l'extrémité arrière de la bombe 21 est monté un dispositif propulseur 23 comprenant une tuyère 24 dans le prolongement de laquelle est disposé le collecteur de jet 25 à plusieurs canalisations 26. Le collecteur 25 est enveloppé par la coiffe 27 qui épouse le profil extérieur de la bombe 21 et qui est maintenue en position par les câbles 28 cheminant à l'intérieur des ailettes 22 de stabilisation de la bombe 21. On a représenté en 30 le dispositif pyrotechnique relié aux câbles 28 et logé à l'intérieur de la case à équipement 29, et en 31 le dispositif mesurant la vitesse de la bombe 21.Referring now to Figures 4 to 6, there is shown a second embodiment of the device according to the invention. At the rear end of the bomb 21 is mounted a propellant device 23 comprising a nozzle 24 in the extension of which is disposed the jet manifold 25 with several pipes 26. The manifold 25 is enveloped by the cap 27 which follows the external profile of the bomb 21 and which is held in position by the cables 28 traveling inside the fins 22 for stabilizing the bomb 21. At 30 is shown the pyrotechnic device connected to the cables 28 and housed inside the box with equipment 29, and at 31 the device measuring the speed of the bomb 21.

Comme on le voit à la figure 6, chaque canalisation 26 forme un coude pour être orientée vers l'avant de la bombe, et coopère avec l'extrémité arrière d'une ailette 22 qui sert de conduit final. La partie avant 32 de chaque ailette 22 est obturée par un matériau dégradable thermiquement de telle sorte que ces ailettes conservent leur profil aérodynamique pendant la phase balistique de la trajectoire, puis que ce matériau est ensuite détruit lors de la mise à feu du dispositif propulseur 23 permettant ainsi l'évacuation des gaz vers l'avant de la bombe et donc l'effet recherché de freinage par rétropropulsion. A une vitesse déterminée de la bombe 21, le dispositif de mesure 31 et le dispositif pyrotechnique 30 commandent le sectionnement des câbles 28, et donc l'éjection de la coiffe 27 et des conduits 26 qu'elle maintient, de façon que la bombe soit propulsée pendant la partie finale de sa trajectoire.As seen in Figure 6, each pipe 26 forms a bend to be oriented towards the front of the bomb, and cooperates with the rear end of a fin 22 which serves as a final conduit. The front part 32 of each fin 22 is closed by a thermally degradable material so that these fins maintain their aerodynamic profile during the ballistic phase of the trajectory, then that this material is then destroyed during the firing of the propellant device 23 thus allowing the evacuation of gases towards the front of the bomb and therefore the desired effect of back-propelling braking. At a determined speed of the bomb 21, the measuring device 31 and the pyrotechnic device 30 control the cutting of the cables 28, and therefore the ejection of the cap 27 and of the conduits 26 which it maintains, so that the bomb is propelled during the final part of its trajectory.

On comprendra que la description ci-dessus a été donnée à simple titre d'exemple, sans caractère limitatif, et que des adjonctions ou des modifications constructives pourraient y être apportées sans sortir du cadre de l'invention définie par les revendications qui suivent.It will be understood that the above description has been given by way of example, without limitation, and that additions or constructive modifications could be made without departing from the scope of the invention defined by the claims which follow.

Claims (7)

1. Dispositif pour le freinage d'une bombe larguée à partir d'un aéronef, comprenant au moins un orifice de jet de gaz orienté vers l'avant de la bombe (1, 21) pour exercer un effet de rétropropulsion, caractérisé par un dispositif propulseur (3, 23) associé à la bombe (1, 21) et dont la sortie de gaz est orientée vers l'arrière de celle-ci, et par un moyen reliant sélectivement la sortie du dispositif propulseur (3, 23) audit orifice de jet de gaz de façon que l'effet de rétropropulsion soit assuré par le jet de gaz sortant du dispositif propulseur (3, 23).1. Device for braking a bomb dropped from an aircraft, comprising at least one gas jet orifice oriented towards the front of the bomb (1, 21) to exert a back-propelling effect, characterized by propellant device (3, 23) associated with the bomb (1, 21) and the gas outlet of which is oriented towards the rear thereof, and by means selectively connecting the outlet of the propellant device (3, 23) to said gas jet orifice so that the back-propelling effect is provided by the gas jet leaving the propellant device (3, 23). 2. Dispositif selon la revendication 1, caractérisé en ce que le moyen d'orientation des jets de gaz vers l'avant de la bombe (1, 21) comprend plusieurs canalisations (6) branchées à la sortie du dispositif propulseur (3) et enveloppées dans une coiffe (7) supportant des trappes (13) déployables sous l'action du jet.2. Device according to claim 1, characterized in that the means for orienting the gas jets towards the front of the bomb (1, 21) comprises several pipes (6) connected to the outlet of the propellant device (3) and wrapped in a cover (7) supporting hatches (13) deployable under the action of the jet. 3. Dispositif selon la revendication 2, caractérisé en ce que chaque trappe (13) est montée pivotante sur la coiffe (7) et est articulée à une pièce mobile (15) limitant le déploiement de la trappe (13).3. Device according to claim 2, characterized in that each hatch (13) is pivotally mounted on the cover (7) and is articulated to a movable part (15) limiting the deployment of the hatch (13). 4. Dispositif selon la revendication 1, caractérisé en ce que le moyen d'oriéntation des jets de gaz vers l'avant de la bombe (21) comprend plusieurs canalisations (26) enveloppées par une coiffe (27) et situées dans le prolongement des ailettes (22) de stabilisation de la bombe (21), lesdites ailettes (22) étant obturées à leur partie avant (32) par un matériau se détruisant lors de la mise à feu du dispositif propulseur (23).4. Device according to claim 1, characterized in that the means for orienting the gas jets towards the front of the bomb (21) comprises several pipes (26) wrapped by a cap (27) and located in the extension of the bomb stabilization fins (22) (21), said fins (22) being closed at their front part (32) by a material destroying when the propellant device (23) is ignited. 5. Dispositif selon l'une quelconque des revendications 2 à 4, caractérisé en ce que ladite coiffe (7, 27) est maintenue par des câbles (8, 28) éjectables au moyen d'un dispositif pyrotechnique (10,30).5. Device according to any one of claims 2 to 4, characterized in that said cap (7, 27) is held by cables (8, 28) ejectable by means of a pyrotechnic device (10,30). 6. Dispositif selon la revendication 5, caractérisé en ce que la mise à feu du dispositif pyrotechnique (10, 30) est contrôlée par un dispositif (11, 31) de mesure de la vitesse de la bombe (1, 21), détectant la position dans laquelle doit s'effectuer l'éjection de la coiffe (7, 27).6. Device according to claim 5, characterized in that the ignition of the pyrotechnic device (10, 30) is controlled by a device (11, 31) for measuring the speed of the bomb (1, 21), detecting the position in which the cap ejection (7, 27) must be carried out. 7. Dispositif selon la revendication 6, caractérisé en ce que l'éjection de la coiffe (7, 27) provoque la propulsion de la bombe (1, 21), dans la phase terminale de la trajectoire de celle-ci, lui communiquant une énergie supplémentaire qui améliore son efficacité à l'impact contre des objectifs durcis.7. Device according to claim 6, characterized in that the ejection of the cap (7, 27) causes the propulsion of the bomb (1, 21), in the terminal phase of the trajectory thereof, giving it a additional energy which improves its impact efficiency against hardened targets.
EP90402733A 1989-10-04 1990-10-03 Device for the braking of a bomb after its release from an aircraft Expired - Lifetime EP0421873B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT90402733T ATE89073T1 (en) 1989-10-04 1990-10-03 DEVICE FOR BRAKING BOMBS AFTER RELEASED FROM AN AIRCRAFT.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8912954A FR2652641B1 (en) 1989-10-04 1989-10-04 DEVICE FOR BRAKING A BOMB AFTER ITS RELEASE FROM AN AIRCRAFT.
FR8912954 1989-10-04

Publications (2)

Publication Number Publication Date
EP0421873A1 true EP0421873A1 (en) 1991-04-10
EP0421873B1 EP0421873B1 (en) 1993-05-05

Family

ID=9386071

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Application Number Title Priority Date Filing Date
EP90402733A Expired - Lifetime EP0421873B1 (en) 1989-10-04 1990-10-03 Device for the braking of a bomb after its release from an aircraft

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EP (1) EP0421873B1 (en)
AT (1) ATE89073T1 (en)
DE (1) DE69001532T2 (en)
ES (1) ES2041516T3 (en)
FR (1) FR2652641B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2702556A1 (en) * 1993-03-08 1994-09-16 Giat Ind Sa Military incendiary head
CN111023916A (en) * 2019-12-31 2020-04-17 蓝箭航天空间科技股份有限公司 Arrow body connector capture device

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Publication number Priority date Publication date Assignee Title
US2539643A (en) * 1946-05-08 1951-01-30 William R Smythe Apparatus for decelerating torpedoes
US2637164A (en) * 1945-03-22 1953-05-05 Power Jets Res & Dev Ltd Jet spoiling means for aircraft gas turbines
US3058304A (en) * 1959-03-02 1962-10-16 Thompson Ramo Wooldridge Inc Steering control for rocket
DE2803036A1 (en) * 1978-01-25 1979-07-26 Messerschmitt Boelkow Blohm ARTICULATED BOMB FOR DEEP FLIGHT DEPLOYMENT

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Publication number Priority date Publication date Assignee Title
US3177655A (en) * 1961-01-24 1965-04-13 Thiokol Chemical Corp Rocket motor thrust termination and reversal device

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2637164A (en) * 1945-03-22 1953-05-05 Power Jets Res & Dev Ltd Jet spoiling means for aircraft gas turbines
US2539643A (en) * 1946-05-08 1951-01-30 William R Smythe Apparatus for decelerating torpedoes
US3058304A (en) * 1959-03-02 1962-10-16 Thompson Ramo Wooldridge Inc Steering control for rocket
DE2803036A1 (en) * 1978-01-25 1979-07-26 Messerschmitt Boelkow Blohm ARTICULATED BOMB FOR DEEP FLIGHT DEPLOYMENT

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2702556A1 (en) * 1993-03-08 1994-09-16 Giat Ind Sa Military incendiary head
CN111023916A (en) * 2019-12-31 2020-04-17 蓝箭航天空间科技股份有限公司 Arrow body connector capture device

Also Published As

Publication number Publication date
ATE89073T1 (en) 1993-05-15
FR2652641B1 (en) 1994-04-29
FR2652641A1 (en) 1991-04-05
DE69001532T2 (en) 1993-12-02
EP0421873B1 (en) 1993-05-05
DE69001532D1 (en) 1993-06-09
ES2041516T3 (en) 1993-11-16

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