EP0421873B1 - 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
EP0421873B1
EP0421873B1 EP90402733A EP90402733A EP0421873B1 EP 0421873 B1 EP0421873 B1 EP 0421873B1 EP 90402733 A EP90402733 A EP 90402733A EP 90402733 A EP90402733 A EP 90402733A EP 0421873 B1 EP0421873 B1 EP 0421873B1
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EP
European Patent Office
Prior art keywords
bomb
cover
braking
propulsion
aircraft
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
EP90402733A
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German (de)
French (fr)
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EP0421873A1 (en
Inventor
Michel Mulleman
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Individual
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Individual
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Publication date
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Priority to AT90402733T priority Critical patent/ATE89073T1/en
Publication of EP0421873A1 publication Critical patent/EP0421873A1/en
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Anticipated expiration legal-status Critical
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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 it proposes for this purpose a device which, while being very simple, reliably ensures the effective braking of the bomb as soon as it is dropped.
  • Document US-A-3,058,304 describes a system for controlling the orientation of a propellant bomb, in which pivoting shells associated with the output of the propellant device can selectively deflect the gas jet forwards. produce a braking effect, or leave the said outlet free in order to obtain a propelling effect.
  • the device for braking a bomb dropped from an aircraft comprises at least one gas jet orifice directed towards the front of the bomb to exert a back-propelling effect, and an associated propellant device bomb and whose gas outlet is oriented towards the rear thereof, and it is characterized by a means of connecting the outlet of the propellant device to said gas jet orifice so that the back-propelling effect is provided by the gas jet leaving the propellant device, said connecting means comprising several pipes wrapped by a cap and located in the extension of the bomb stabilization fins, said fins being closed at their front part by a material destroying during the ignition of the propellant device.
  • 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 to 3 there is shown an 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 running 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)
  • Combustion & Propulsion (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Regulating Braking Force (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Braking Arrangements (AREA)
  • Braking Systems And Boosters (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
  • Valves And Accessory Devices For Braking Systems (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 il 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 it is 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 une 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 it proposes for this purpose a device which, while being very simple, reliably ensures the effective braking of the bomb as soon as it is dropped.

Par l'article "Concrete dibber Conceived in France" de Robert R. RODWELL, paru aux pages 1013-1014 de la revue FLIGHT INTERNATIONAL, vol. 92, de décembre 1967, on connaît une bombe destinée à être larguée à partir d'un aéronef, cette bombe comprenant au moins un orifice de jet de gaz orienté vers l'avant pour exercer un effet de rétropropulsion, et un dispositif propulseur qui lui est associé et dont la sortie de gaz est orientée vers l'arrière. Le dispositif de freinage a pour objet de rendre la trajectoire de la bombe plus verticale à partir d'un avion, alors que le dispositif propulseur est destiné à communiquer ensuite à la bombe une énergie par une accélération.By the article "Concrete dibber Conceived in France" by Robert R. RODWELL, published on pages 1013-1014 of the journal FLIGHT INTERNATIONAL, vol. 92, from December 1967, there is known a bomb intended to be dropped from an aircraft, this bomb comprising at least one gas jet orifice directed towards the front to exert a back-propelling effect, and a propellant device which is associated and whose gas outlet is oriented towards the rear. The purpose of the braking device is to make the trajectory of the bomb more vertical from an airplane, while the propellant device is intended to then communicate energy to the bomb by acceleration.

Le document US-A-3 058 304 décrit un système de commande de l'orientation d'une bombe à dispositif propulseur, dans lequel des coquilles pivotantes associées à la sortie du dispositif propulseur peuvent sélectivement dévier le jet de gaz vers l'avant pour produire un effet de freinage, ou laisser libre ladite sortie afin d'obtenir un effet de propulsion.Document US-A-3,058,304 describes a system for controlling the orientation of a propellant bomb, in which pivoting shells associated with the output of the propellant device can selectively deflect the gas jet forwards. produce a braking effect, or leave the said outlet free in order to obtain a propelling effect.

Selon l'invention le dispositif pour le freinage d'une bombe larguée à partir d'un aéronef, comprend au moins un orifice de jet de gaz orienté vers l'avant de la bombe pour exercer un effet de rétropropulsion, et un dispositif propulseur associé à la bombe et dont la sortie de gaz est orientée vers l'arrière de celle-ci, et il se caractérisé par un moyen de liaison de la sortie du dispositif propulseur audit orifice de jet de gaz de façon que l'effet de rétropropulsion soit assuré par le jet de gaz sortant du dispositif propulseur, ledit moyen de liaison comprenant plusieurs canalisations enveloppées par une coiffe et situées dans le prolongement des ailettes de stabilisation de la bombe, lesdites ailettes étant obturées à leur partie avant par un matériau se détruisant lors de la mise à feu du dispositif propulseur.According to the invention the device for braking a bomb dropped from an aircraft, comprises at least one gas jet orifice directed towards the front of the bomb to exert a back-propelling effect, and an associated propellant device bomb and whose gas outlet is oriented towards the rear thereof, and it is characterized by a means of connecting the outlet of the propellant device to said gas jet orifice so that the back-propelling effect is provided by the gas jet leaving the propellant device, said connecting means comprising several pipes wrapped by a cap and located in the extension of the bomb stabilization fins, said fins being closed at their front part by a material destroying during the ignition of the propellant device.

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'exemple sans caractère limitatif, une forme d'exécution préférée en référence au dessin schématique annexé dans lequel :

  • la figure 1 est une vue de côté d'une bombe équipée d'une 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 associé à l'arrière de la bombe.
To clearly understand the device according to the invention, a preferred embodiment will be described below, by way of example, with reference to the appended schematic drawing in which:
  • Figure 1 is a side view of a bomb equipped with an 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 associated with the rear of the bomb.

En référence aux figures 1 à 3, on a représenté une 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 to Figures 1 to 3, there is shown an 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 running 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 3, 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 3, 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 (3)

  1. Device for braking a bomb launched from an aircraft, comprising at least one gas jet orifice directed towards the front of the bomb (1, 21) for exerting a drag effect, and a propulsion device (3, 23) which is associated with the bomb (1, 21), and of which the gas outlet is directed towards the rear thereof, characterised by a means of connecting the outlet of the propulsion device (3, 23) to the said gas jet orifice in such a manner that the drag effect is brought about by the gas jet leaving the propulsion device (3, 23), the said connecting means comprising a plurality of ducts (26) closed by a cover (27) and located in the extension of the stabiliser fins (22) of the bomb (21), the said fins (22) being sealed at their front part (32) by a material that self-destructs when the propulsion device (23) is fired.
  2. Device according to Claim 1,
    characterised in that the said cover (7, 27) is held by cables (8, 28) which can be ejected by means of a pyrotechnic device (10, 30).
  3. Device according to Claim 2,
    characterised in that the firing of the pyrotechnic device (10, 30) is controlled by a device (11, 31) for measuring the velocity of the bomb (1, 21) and detecting the position in which the cover (7, 27) is to be ejected.
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
FR8912954 1989-10-04
FR8912954A FR2652641B1 (en) 1989-10-04 1989-10-04 DEVICE FOR BRAKING A BOMB AFTER ITS RELEASE FROM AN AIRCRAFT.

Publications (2)

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

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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)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2702556B1 (en) * 1993-03-08 1995-04-28 Giat Ind Sa Incendiary military head.
CN111023916B (en) * 2019-12-31 2020-08-04 蓝箭航天空间科技股份有限公司 Arrow body connector capture device

Citations (1)

* Cited by examiner, † Cited by third party
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

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL67983C (en) * 1945-03-22 1900-01-01
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

Patent Citations (1)

* Cited by examiner, † Cited by third party
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Concrete Dibber conceived in France ("Flight International"), Vol. 92, p. 1013-1014, 14.12.92, R.R. Rodwell, London. *

Also Published As

Publication number Publication date
DE69001532T2 (en) 1993-12-02
EP0421873A1 (en) 1991-04-10
DE69001532D1 (en) 1993-06-09
ES2041516T3 (en) 1993-11-16
FR2652641B1 (en) 1994-04-29
ATE89073T1 (en) 1993-05-15
FR2652641A1 (en) 1991-04-05

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