EP0335761A1 - Airborne vehicle with at least one releasable propulsion unit - Google Patents

Airborne vehicle with at least one releasable propulsion unit Download PDF

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Publication number
EP0335761A1
EP0335761A1 EP89400663A EP89400663A EP0335761A1 EP 0335761 A1 EP0335761 A1 EP 0335761A1 EP 89400663 A EP89400663 A EP 89400663A EP 89400663 A EP89400663 A EP 89400663A EP 0335761 A1 EP0335761 A1 EP 0335761A1
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EP
European Patent Office
Prior art keywords
machine
propellant
rest
missile
accelerator
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EP89400663A
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German (de)
French (fr)
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EP0335761B1 (en
Inventor
Jean Marie Dupuis
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Airbus Group SAS
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Airbus Group SAS
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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

Definitions

  • the present invention relates to an aerial vehicle provided with at least one releasable thruster. It applies to any device, such as missile, rocket, rocket, provided with one or more releasable thrusters, that this or these thruster (s) is (are) mounted (s) coaxially to said device, or well disposed (s) on the periphery of the latter.
  • releasable thrusters are for example consumable accelerators intended to communicate to said machine a desired speed value.
  • the first which can be described as active, uses mechanical or pyrotechnic elements, such as cutting cords, explosive bolts, extraction springs, etc. controlled by a logic device.
  • Such active separation systems are therefore complex. In addition, their reliability is not perfect.
  • the second of said methods is called natural, because the separation takes place spontaneously under the action of the aerodynamic drag of said propellant.
  • the propellant is connected to the rest of the device by a precise interlocking, constituting a sliding connection parallel to the axis of said propellant, but making the latter integral in rotation with said device.
  • the propulsion force thereof reinforced by the aerodynamic drag of the rest of the machine and by the friction forces of the connection slippery, but reduced in the aerodynamic drag of said propellant, secures the propellant on said machine.
  • said propulsion force decreases very sharply (pushing tail) until it vanishes, so that it becomes insufficient to keep said propellant integral with the rest of the vehicle.
  • the aerodynamic drag of said propellant can then overcome the friction forces of the sliding link and, contrary to the action of aerodynamic drag of the rest of the vehicle, said propellant separates naturally from the rest of the vehicle.
  • the friction forces in a sliding connection depend on the state of the contact surface, on the possible lubrication and on the play, that is to say on the manufacturing tolerances of the engagement of the propellant on the rest of the craft.
  • a gumming phenomenon can appear, when the sliding link is immobilized for a prolonged period, as can be an ammunition in stock.
  • the sliding connection which ensures the rigidity of the whole of the machine and the propellant, can be subjected to a significant embedding moment during separation. This moment, which can result from the aerodynamics of the machine or from longitudinal mechanical vibrations, significantly affects the level of frictional forces.
  • immobilization in rotation of the sliding link can lead to additional friction due to torsional torques (also of aerodynamic or vibratory origin) in the interlocking.
  • the object of the present invention is to remedy these drawbacks. It allows to obtain, with safety, the natural separation of a temporary propellant from the rest of a machine, without requiring the intervention of auxiliary controllable devices.
  • the air vehicle comprising at least one propellant, temporary and releasable, linked to the rest of said vehicle by an adjustment capable of allowing said propellant to slide parallel to its axis in the direction opposite to said rest of the 'machine, is remarkable in that a communication is established between, on the one hand, the internal space to said adjustment and disposed between the front of said propellant and said rest of the machine, and, on the other hand, l aerodynamic flow around said machine.
  • this internal space is put under a pressure equal to at least a part of the total pressure of said aerodynamic flow, so that in this internal space is generated a force favorable to the natural separation of the propellant.
  • said propellant has a diameter greater than that of the part of said machine on which it is mounted and said part is connected to said propellant by a divergent wall linked to it, it is preferable that said communication be established through said divergent wall.
  • said communication is constituted by at least one conduit, the external orifice thereof is advantageously directed towards the front of said machine, so that the air intake is favored.
  • said communication is multiple.
  • the communication conduit is extended outside of said machine by an air intake.
  • said air intake is at least substantially parallel to the axis of the machine and directed towards the front thereof.
  • the aerodynamic symmetry of the assembly is respected.
  • the way of arranging the air intakes, to recover the desired pressure, then takes account of the presence of possible shock waves in supersonic flow.
  • a missile 1 comprising a propellant, or accelerator, temporary 2 (for example powder), the front part of which is mounted on the rear part, the rest 3 of said missile.
  • accelerator 2 is coaxial with the rest 3 of said missile, but it is clear that this feature is not essential for the invention.
  • the axis of the accelerator 2 while being parallel to the axis of said missile, could be eccentric with respect thereto.
  • the front part of the accelerator would not necessarily be connected to the rear extreme part of the remainder 3 of the missile 1.
  • FIGS. 1 and 2 it has also been assumed, which is also not compulsory, that the diameter of the accelerator was greater than that of the rest 3 of missile 1.
  • the rear part of the remainder 3 of said missile (remainder which could possibly include another accelerator) is provided with two ranges cylindrical 4 and 5 coaxial and stepped.
  • the front part of the accelerator 2 comprises a cylindrical portion 6, provided with internal cylindrical surfaces 7 and 8, intended respectively to bear on the cylindrical surfaces 4 and 5.
  • a transverse shoulder 9 of the rear part of the rest 3 of the missile 1 cooperates with the extreme front edge 10 of the cylindrical portion 6 to serve as a stop for the accelerator 2 towards the front.
  • the external contour 11 is also connected to the external contour 13 of the accelerator 2 by a conical skirt 14.
  • a longitudinal groove and rib system 15 makes the accelerator 2 and the rest 3 of the missile 1 integral in rotation with one another.
  • FIG 3 there is shown the missile 1 of Figures 1 and 2 improved according to the present invention.
  • the internal space 16 is then placed in communication with the outside by one or more ducts 17, provided with external air intakes 18.
  • the ducts 17 and the air intakes 18 are arranged in the conical skirt 14.
  • the air intakes 18 are arranged at least substantially parallel to the axis of the propellant and directed towards the front of said missile 1.
  • the thrust thereof acts so as to press the extreme front edge 10 of said accelerator 2 against the shoulder 9.
  • Said accelerator 2 is therefore integral longitudinally with the rest 3 of the missile 1.
  • the longitudinal rib 5 and groove 15 system it is integral with the latter in rotation.
  • the thrust action of the propellant 2 is then reinforced by the aerodynamic drag exerted on the rest 3 of the missile 1, as well as by the friction forces existing respectively between the ranges 4 and 5 and the cylindrical surfaces 7 and 8.
  • this action is counteracted by the aerodynamic drag exerted on the accelerator 2 and by the force, due to the pressure prevailing in the internal space 16.
  • the air intakes 18 and the conduits 17 allow to transmit to the latter at least part of the aerodynamic overpressure prevailing in the vicinity of missile 1 in flight.
  • a sealing lubricant between the surfaces 4 and 5, on the one hand, and the cylindrical surfaces 7 and 8, else go.
  • the volume of the internal space 16 and the diameter of the pressure taps 17, 18 are dimensioned so that the level of the pressure forces remains as long as the missile and the accelerator are in contact during the separation phase.
  • the diameter of the internal space 16 partly determines the level of the pressure forces.
  • the invention makes it possible to greatly increase the reliability of natural separation.
  • the latter is, in fact systematic, thanks to the added forces.
  • the speed of the relative separation movement removes all risk of shock between the rest 3 of the missile 1 and the accelerator 2, after disengagement of the embedding 4,7-5,8-9,10.
  • the instant of separation is no longer subject only to the dispersions inherent in the propulsion, that is to say the combustion time of the acceleration propellant 2.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Current-Collector Devices For Electrically Propelled Vehicles (AREA)

Abstract

- Airborne vehicle (1) comprising at least one temporary releasable propulsion unit (2) connected to the rest (3) of said vehicle by means of a fit (4, 7-5,8-9, 10) capable of allowing said propulsion unit to slide parallel to its axis in the opposite direction to the rest (3) of the vehicle. <??>- According to the invention, this vehicle is notable in that communication (17) is established between, on the one hand, the space (16) located within said fit and arranged between the front of said propulsion unit and said rest (3) of the vehicle and, on the other hand, the aerodynamic flow around said vehicle (1). <??>- The natural separation of said propulsion unit (2) from the rest (3) of said missile (1). <IMAGE>

Description

La présente invention concerne un engin aérien pourvu d'au moins un propulseur largable. Elle s'applique à tout engin, tel que missile, fusée, roquette, pourvu d'un ou de plu­sieurs propulseurs largables, que ce ou ces propulseur (s) soi(en)t monté(s) coaxialement audit engin, ou bien disposé(s) à la périphérie de ce dernier. De tels propulseurs largables sont par exemple des accélérateurs consommables destinés à communiquer audit engin une valeur de vitesse désirée.The present invention relates to an aerial vehicle provided with at least one releasable thruster. It applies to any device, such as missile, rocket, rocket, provided with one or more releasable thrusters, that this or these thruster (s) is (are) mounted (s) coaxially to said device, or well disposed (s) on the periphery of the latter. Such releasable thrusters are for example consumable accelerators intended to communicate to said machine a desired speed value.

On sait que pour séparer un tel propulseur du reste de l'engin, après qu'il a rempli son office, il existe essentiellement deux méthodes.We know that to separate such a propellant from the rest of the machine, after it has fulfilled its function, there are essentially two methods.

La première, qui peut être qualifiée d'active, met en oeuvre des éléments mécaniques ou pyrotechniques, tels que des cordons découpeurs, des boulons explosifs, des ressorts d'extraction, etc... commandés par un dispositif logique. De tels systèmes de séparation active sont donc complexes. De plus, leur fiabilité n'est pas parfaite.The first, which can be described as active, uses mechanical or pyrotechnic elements, such as cutting cords, explosive bolts, extraction springs, etc. controlled by a logic device. Such active separation systems are therefore complex. In addition, their reliability is not perfect.

La seconde desdites méthodes est appelée naturelle, car la séparation s'effectue spontanément sous l'action de la traînée aérodynamique dudit propulseur.The second of said methods is called natural, because the separation takes place spontaneously under the action of the aerodynamic drag of said propellant.

Dans les engins prévus pour mettre en oeuvre une telle séparation naturelle, le propulseur est relié au reste de l'engin par un emboîtement précis, constituant une liaison glissante parallèlement à l'axe dudit propulseur, mais rendant ce dernier solidaire en rotation dudit engin.In the devices intended to implement such a natural separation, the propellant is connected to the rest of the device by a precise interlocking, constituting a sliding connection parallel to the axis of said propellant, but making the latter integral in rotation with said device.

Ainsi, au lancement de l'engin et pendant son vol sous l'action dudit propulseur, la force de propulsion de celui-ci, renforcée par la traînée aérodynamique du reste de l'engin et par les forces de frottement de la liaison glissante, mais diminuée de la trainée aérodynamique dudit propulseur, assure la solidarisation du propulseur sur ledit engin.Thus, at launch of the machine and during its flight under the action of said propellant, the propulsion force thereof, reinforced by the aerodynamic drag of the rest of the machine and by the friction forces of the connection slippery, but reduced in the aerodynamic drag of said propellant, secures the propellant on said machine.

En revanche, en fin de fonctionnement dudit propulseur, ladite force de propulsion décroît très fortement (queue de poussée) jusqu'à s'annuler, de sorte qu'elle devient insuffisante pour maintenir ledit propulseur solidaire du reste de l'engin. La traînée aérodynamique dudit propulseur peut alors vaincre les forces de frottement de la liaison glissante et, à l'encontre de l'action de la traînée aérodynamique du reste de l'engin, ledit propulseur se sépare naturellement du reste de l'engin.On the other hand, at the end of operation of said propellant, said propulsion force decreases very sharply (pushing tail) until it vanishes, so that it becomes insufficient to keep said propellant integral with the rest of the vehicle. The aerodynamic drag of said propellant can then overcome the friction forces of the sliding link and, contrary to the action of aerodynamic drag of the rest of the vehicle, said propellant separates naturally from the rest of the vehicle.

Une telle méthode naturelle de séparation présente donc d'importants avantages de simplicité, à la fois dans la réalisation et dans la mise en oeuvre. Cependant, elle comporte également des inconvénients importants, liés au fait que les forces qu'elle met en jeu sont difficilement maîtrisables.Such a natural method of separation therefore has significant advantages of simplicity, both in the production and in the implementation. However, it also has significant drawbacks, linked to the fact that the forces it brings into play are difficult to control.

En effet, les forces de frottement dans une liaison glissante dépendent de l'état de la surface de contact, de l'éventuelle lubrification et du jeu, c'est-à-dire des tolérances de fabrication de l'emboîtement du propulseur sur le reste de l'engin. De plus, un phénomène de gommage peut apparaître, lorsque la liaison glissante est immobilisée de manière prolongée, comme peut l'être une munition en stock.In fact, the friction forces in a sliding connection depend on the state of the contact surface, on the possible lubrication and on the play, that is to say on the manufacturing tolerances of the engagement of the propellant on the rest of the craft. In addition, a gumming phenomenon can appear, when the sliding link is immobilized for a prolonged period, as can be an ammunition in stock.

Par ailleurs, la liaison glissante, qui assure la rigidité de l'ensemble de l'engin et du propulseur, peut être soumise à un moment d'encastrement important pendant la séparation. Ce moment, qui peut résulter de l'aérodynamique de l'engin ou de vibrations mécaniques longitudinales, affecte de manière considérable le niveau des forces de frottement. Enfin, l'immobilisation en rotation de la liaison glissante peut amener des frottements supplémentai­res dus à des couples de torsion (d'origine aérodynamique ou vibratoire également) dans l'emboîtement.In addition, the sliding connection, which ensures the rigidity of the whole of the machine and the propellant, can be subjected to a significant embedding moment during separation. This moment, which can result from the aerodynamics of the machine or from longitudinal mechanical vibrations, significantly affects the level of frictional forces. Finally, immobilization in rotation of the sliding link can lead to additional friction due to torsional torques (also of aerodynamic or vibratory origin) in the interlocking.

Quant aux forces de propulsion du propulseur en queue de poussée, elles aussi sont mal connues, tout comme les forces aérodynamiques et, plus particulièrement, leur répartition entre l'engin et le propulseur.As for the propulsion forces of the thruster at the tail end, they are also poorly known, as are the aerodynamic forces and, more particularly, their distribution between the craft and the propellant.

En outre, la traînée aérodynamique du propulseur, seule force sur laquelle on mise pour séparer et que l'on souhaiterait grande pour favoriser la séparation, doit être, bien évidemment, aussi réduite que possible par soucis d'économie.In addition, the aerodynamic drag of the propellant, the only force on which we put to separate and which we would like great to promote separation, must, of course, be as reduced as possible for reasons of economy.

Il apparaît donc un certain nombre d'incertitudes relatives au niveau des forces mises en jeu dans la séparation naturelle. Elles se traduisent par une dispersion très importante de l'instant de séparation. Une telle séparation peut même dans certains cas ne pas se produire du tout. Dans tous les cas, la suite du programme de vol de l'engin s'en trouve très perturbée. En l'état, la méthode de séparation naturelle quoique très séduisante, laisse donc supposer des aléas de fonctionnement difficilement acceptables, notamment pour un système d'arme moderne.There therefore appears a certain number of uncertainties relating to the level of the forces involved in natural separation. They result in a very significant dispersion of the moment of separation. Such separation may even in some cases not occur at all. In any case, the rest of the craft's flight program is very disturbed. As it stands, the method of natural separation, although very attractive, therefore suggests the vagaries of functioning that are difficult to accept, especially for a modern weapon system.

Pour pallier ces inconvénients, diverses améliorations ont été envisagées consistant à introduire de nouvelles forces propices à la séparation, telles que celles engendrées par l'ouverture d'un parachute frein ou par des ressorts d'extraction prévus dans la liaison glissante.To overcome these drawbacks, various improvements have been envisaged consisting in introducing new forces conducive to separation, such as those generated by the opening of a brake parachute or by extraction springs provided in the sliding connection.

Cependant, de telles dispositions nécessitent une logique de déclenchement et réintroduisent les inconvénients mentionnés ci-dessus à propos de la méthode active de séparation. D'ailleurs, il ne s'agit déjà plus de séparation naturelle.However, such arrangements require a trigger logic and reintroduce the drawbacks mentioned above with regard to the active method of separation. Besides, it is no longer a question of natural separation.

La présente invention a pour objet de remédier à ces inconvénients. Elle permet d'obtenir, avec sûreté, la séparation naturelle d'un propulseur temporaire du reste d'un engin, sans faire intervenir de dispositifs auxiliai­res commandables.The object of the present invention is to remedy these drawbacks. It allows to obtain, with safety, the natural separation of a temporary propellant from the rest of a machine, without requiring the intervention of auxiliary controllable devices.

A cette fin, selon l'invention, l'engin aérien comportant au moins un propulseur, temporaire et largable, lié au reste dudit engin par un ajustement susceptible de permettre audit propulseur de glisser parallèlement à son axe dans le sens opposé audit reste de l'engin, est remarquable en ce qu'une communication est établie entre, d'une part, l'espace interne audit ajustement et disposé entre l'avant dudit propulseur et ledit reste de l'engin, et, d'autre part, l'écoulement aérodynamique autour dudit engin.To this end, according to the invention, the air vehicle comprising at least one propellant, temporary and releasable, linked to the rest of said vehicle by an adjustment capable of allowing said propellant to slide parallel to its axis in the direction opposite to said rest of the 'machine, is remarkable in that a communication is established between, on the one hand, the internal space to said adjustment and disposed between the front of said propellant and said rest of the machine, and, on the other hand, l aerodynamic flow around said machine.

Ainsi, cet espace interne est mis sous une pression égale au moins à une partie à la pression totale dudit écoulement aérodynamique, de sorte que dans cet espace interne est engendrée une force favorable à la séparation naturelle du propulseur.Thus, this internal space is put under a pressure equal to at least a part of the total pressure of said aerodynamic flow, so that in this internal space is generated a force favorable to the natural separation of the propellant.

Un tel espace interne existe généralement par construction entre ledit propulseur et le reste dudit engin. Bien entendu, dans le cas où il n'existerait pas, il serait nécessaire de l'aménager spécialement en vue de la mise en oeuvre de l'invention.Such an internal space generally exists by construction between said propellant and the rest of said machine. Of course, if it does not exist, it would be necessary to arrange it specially for the implementation of the invention.

Afin de ne pas perturber l'aérodynamique du reste de l'engin par la disposition de prises de pression externes, il est préférable que ladite communication soit établie à travers ledit propulseur. En effet, puisque celui-ci n'est généralement destiné qu'à propulser ledit engin lors de son lancement et sur la partie initiale de sa trajectoire avant d'être largué, il est moins perturbant que ce soit l'aéro­dynamisme dudit propulseur qui soit modifié par ladite communication. De plus, de telles prises de pression augmentent la trainée aérodynamique et il est donc préfé­rable de les disposer sur le propulseur, puisqu'alors elles favorisent la séparation de celui-ci.In order not to disturb the aerodynamics of the rest of the machine by the provision of external pressure taps, it is preferable that said communication is established at through said propellant. In fact, since the latter is generally only intended to propel said vehicle during its launch and on the initial part of its trajectory before being released, it is less disturbing that it is the aerodynamics of said propellant which is modified by said communication. In addition, such pressure taps increase the aerodynamic drag and it is therefore preferable to have them on the propellant, since then they promote the separation thereof.

Lorsque, comme cela est courant, ledit propulseur a un diamètre supérieur à celui de la partie dudit engin sur laquelle il est monté et que ladite partie est raccordée audit propulseur par une paroi divergente liée à celui-ci, il est préférable que ladite communication soit établie à travers ladite paroi divergente. Ainsi, lorsque ladite communication est constituée par au moins un conduit, l'orifice extérieur de celui-ci est avantageusement dirigé vers l'avant dudit engin, de sorte que l'entrée d'air est favorisée.When, as is common, said propellant has a diameter greater than that of the part of said machine on which it is mounted and said part is connected to said propellant by a divergent wall linked to it, it is preferable that said communication be established through said divergent wall. Thus, when said communication is constituted by at least one conduit, the external orifice thereof is advantageously directed towards the front of said machine, so that the air intake is favored.

De préférence, ladite communication est multiple.Preferably, said communication is multiple.

Dans un mode avantageux de réalisation, le conduit de communication est prolongé à l'extérieur dudit engin par une prise d'air. Dans ce cas, il est préférable que ladite prise d'air soit au moins sensiblement parallèle à l'axe de l'engin et dirigée vers l'avant de celui-ci.In an advantageous embodiment, the communication conduit is extended outside of said machine by an air intake. In this case, it is preferable that said air intake is at least substantially parallel to the axis of the machine and directed towards the front thereof.

Bien entendu, dans le cas où ladite communication est multiple, il est préférable que la symétrie aérodynamique de l'ensemble soit respectée. La manière de disposer les prises d'air, pour récupérer la pression désirée, tient alors compte de la présence d'ondes de choc éventuelles en écoulement supersonique.Of course, in the case where said communication is multiple, it is preferable that the aerodynamic symmetry of the assembly is respected. The way of arranging the air intakes, to recover the desired pressure, then takes account of the presence of possible shock waves in supersonic flow.

Les figures du dessin annexé feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.

  • La figure 1 est une vue en coupe axiale, schématique et partielle, d'un exemple de réalisation de missile auquel l'invention peut être appliquée.
  • La figure 2 est une coupe transversale, selon la ligne II-II de la figure 1.
  • La figure 3 est une vue analogue à la figure 1, illustrant la présente invention.
  • La figure 4 illustre une variante de réalisation de l'invention, en vue semblable à la figure 3.
The figures of the appended drawing will make it clear how the invention can be implemented. In these figures, identical references designate similar elements.
  • Figure 1 is an axial sectional view, schematic and partial, of an exemplary missile embodiment to which the invention can be applied.
  • Figure 2 is a cross section along the line II-II of Figure 1.
  • Figure 3 is a view similar to Figure 1 illustrating the present invention.
  • FIG. 4 illustrates an alternative embodiment of the invention, in a view similar to FIG. 3.

Sur les figures 1 et 2, on a représenté, schématiquement et partiellement en coupe, un missile 1 comportant un propulseur, ou accélérateur, temporaire 2 (par exemple à poudre), dont la partie avant est montée sur la partie arrière, du reste 3 dudit missile. Dans cet exemple de réalisation, on a supposé que l'accélérateur 2 était coaxial au reste 3 dudit missile, mais il est clair que cette particularité n'est pas essentielle pour l'invention. Par exemple, l'axe de l'accélérateur 2, tout en étant parallèle à l'axe dudit missile, pourrait être excentré par rapport à celui-ci. Dans ce cas, la partie avant de l'accélérateur ne serait pas forcément reliée à la partie extrême arrière du reste 3 du missile 1. Sur les figures 1 et 2, on a supposé de plus, ce qui n'est également pas obligatoire, que le diamètre de l'accélérateur était supérieur à celui du reste 3 du missile 1.In Figures 1 and 2, there is shown, schematically and partially in section, a missile 1 comprising a propellant, or accelerator, temporary 2 (for example powder), the front part of which is mounted on the rear part, the rest 3 of said missile. In this exemplary embodiment, it has been assumed that the accelerator 2 is coaxial with the rest 3 of said missile, but it is clear that this feature is not essential for the invention. For example, the axis of the accelerator 2, while being parallel to the axis of said missile, could be eccentric with respect thereto. In this case, the front part of the accelerator would not necessarily be connected to the rear extreme part of the remainder 3 of the missile 1. In FIGS. 1 and 2, it has also been assumed, which is also not compulsory, that the diameter of the accelerator was greater than that of the rest 3 of missile 1.

Dans l'exemple représenté, la partie arrière du reste 3 dudit missile (reste qui pourrait éventuellement comporter un autre accélérateur) est pourvue de deux portées cylindriques 4 et 5 coaxiales et étagées. La partie avant de l'accélérateur 2 comporte une portion cylindrique 6, pourvue de surfaces cylindriques internes 7 et 8, destinés respecti­vement à s'appuyer sur les portées cylindriques 4 et 5. Un épaulement transversal 9 de la partie arrière du reste 3 du missile 1 coopère avec le bord extrême avant 10 de la portion cylindrique 6 pour servir de butée à l'accélérateur 2 vers l'avant.In the example shown, the rear part of the remainder 3 of said missile (remainder which could possibly include another accelerator) is provided with two ranges cylindrical 4 and 5 coaxial and stepped. The front part of the accelerator 2 comprises a cylindrical portion 6, provided with internal cylindrical surfaces 7 and 8, intended respectively to bear on the cylindrical surfaces 4 and 5. A transverse shoulder 9 of the rear part of the rest 3 of the missile 1 cooperates with the extreme front edge 10 of the cylindrical portion 6 to serve as a stop for the accelerator 2 towards the front.

L'ajustement entre les portées 4 et 5 et les surfaces cylindriques 7 et 8 est serré et, lorsque lesdites surfaces cylindriques sont en appui sur lesdites portées et que le bord extrême 10 est en butée contre l'épaulement 9, le contour extérieur 11 de la portion cylindrique 6 constitue le prolongement du contour extérieur 12 de la partie arrière du reste 3 du missile 1.The fit between the bearing surfaces 4 and 5 and the cylindrical surfaces 7 and 8 is tight and, when the said cylindrical surfaces are in abutment on the said bearing surfaces and the end edge 10 is in abutment against the shoulder 9, the outer contour 11 of the cylindrical portion 6 constitutes the extension of the external contour 12 of the rear part of the remainder 3 of the missile 1.

Le contour extérieur 11 est par ailleurs relié au contour extérieur 13 de l'accélérateur 2 par une jupe conique 14.The external contour 11 is also connected to the external contour 13 of the accelerator 2 by a conical skirt 14.

Un système longitudinal de rainure et de nervure 15 rend l'accélérateur 2 et le reste 3 du missile 1 solidaires en rotation l'un de l'autre.A longitudinal groove and rib system 15 makes the accelerator 2 and the rest 3 of the missile 1 integral in rotation with one another.

Entre les parties arrière du reste 3 du missile 1 et la partie avant de l'accélérateur 2, à l'intérieur de la portion cylindrique 6, est ménage un espace interne clos 16.Between the rear parts of the remainder 3 of the missile 1 and the front part of the accelerator 2, inside the cylindrical portion 6, there is a closed internal space 16.

Sur la figure 3, on a représenté le missile 1 des figures 1 et 2 perfectionné selon la présente invention. Comme on peut le voir, conformément à l'invention, l'espace interne 16 est alors mis en communication avec l'extérieur par un ou plusieurs conduits 17, pourvus de prises d'air extérieures 18. Dans l'exemple représenté, les conduits 17 et les prises d'air 18 sont agencés dans la jupe conique 14. Les prises d'air 18 sont disposées au moins sensiblement parallèlement à l'axe du propulseur et dirigées vers l'avant dudit missile 1.In Figure 3, there is shown the missile 1 of Figures 1 and 2 improved according to the present invention. As can be seen, in accordance with the invention, the internal space 16 is then placed in communication with the outside by one or more ducts 17, provided with external air intakes 18. In the example shown, the ducts 17 and the air intakes 18 are arranged in the conical skirt 14. The air intakes 18 are arranged at least substantially parallel to the axis of the propellant and directed towards the front of said missile 1.

Ainsi, au lancement du missile 1 ou pendant son vol sous l'action de l'accélérateur 2, la poussée de celui-ci agit de façon à presser le bord avant extrême 10 dudit accélé­rateur 2 contre l'épaulement 9. Ledit accélérateur 2 est donc solidaire longitudinalement du reste 3 du missile 1. De plus, par le système longitudinal de nervure 5 et de rainure 15, il est solidaire de celui-ci en rotation.Thus, when the missile 1 is launched or during its flight under the action of the accelerator 2, the thrust thereof acts so as to press the extreme front edge 10 of said accelerator 2 against the shoulder 9. Said accelerator 2 is therefore integral longitudinally with the rest 3 of the missile 1. In addition, by the longitudinal rib 5 and groove 15 system, it is integral with the latter in rotation.

L'action de la poussée du propulseur 2 est alors renforcée par la traînée aérodynamique s'exerçant sur le reste 3 du missile 1, ainsi que par les forces de frottements existant respectivement entre les portées 4 et 5 et les surfaces cylindriques 7 et 8. En revanche, cette action est contrecarrée par la traînée aérodynamique s'exerçant sur l'accélérateur 2 et par la force, due à la pression régnant dans l'espace interne 16. En effet, les prises d'air 18 et les conduits 17 permettent de transmettre à celui-ci au moins une partie de la surpression aérodynamique régnant au voisinage du missile 1 en vol.The thrust action of the propellant 2 is then reinforced by the aerodynamic drag exerted on the rest 3 of the missile 1, as well as by the friction forces existing respectively between the ranges 4 and 5 and the cylindrical surfaces 7 and 8. On the other hand, this action is counteracted by the aerodynamic drag exerted on the accelerator 2 and by the force, due to the pressure prevailing in the internal space 16. In fact, the air intakes 18 and the conduits 17 allow to transmit to the latter at least part of the aerodynamic overpressure prevailing in the vicinity of missile 1 in flight.

Ainsi, lorsque l'accélérateur arrive à la fin de son fonctionnement, sa poussée décroît fortement, alors que la vitesse du missile est grande. Par suite, la force due à la surpression dans l'espace interne 16 peut, aidée par la traînée aérodynamique de l'accélérateur 2, vaincre l'action des forces tendant à maintenir l'accélérateur 2 solidaire du reste 3 dudit missile 1. Le bord extrême avant 10 se décolle de l'épaulement 9 et les surfaces 7 et 8 glissent vers l'arrière sur les portées 4 et 5 en étant guidées longitudinalement par le système de nervure et de rainure 15. L'accélérateur peut poursuivre ce mouvement de recul jusqu'à séparation complète d'avec le reste 3 du missile 1.Thus, when the accelerator reaches the end of its operation, its thrust decreases sharply, while the speed of the missile is high. Consequently, the force due to the overpressure in the internal space 16 can, aided by the aerodynamic drag of the accelerator 2, overcome the action of the forces tending to keep the accelerator 2 integral with the rest 3 of said missile 1. The extreme front edge 10 comes off the shoulder 9 and the surfaces 7 and 8 slide backwards on the surfaces 4 and 5 while being guided longitudinally by the rib and groove system 15. The accelerator can continue this movement of retreat until complete separation from the rest 3 of missile 1.

Pour améliorer l'action de la forme due à la surpression à l'intérieur de l'espace interne 16, on peut prévoir de disposer un lubrifiant d'étanchéité entre les portées 4 et 5, d'une part, et les surfaces cylindriques 7 et 8, d'autre part. Ainsi, on évite les fuites intempestives de fluide à ces niveaux, tant qu'une partie desdites surfaces cylindri­ques 7 et 8 reste au contact desdites portées 4 et 5.To improve the action of the shape due to the overpressure inside the internal space 16, provision may be made to have a sealing lubricant between the surfaces 4 and 5, on the one hand, and the cylindrical surfaces 7 and 8, else go. Thus, untimely leakage of fluid is avoided at these levels, as long as part of said cylindrical surfaces 7 and 8 remains in contact with said spans 4 and 5.

Le volume de l'espace interne 16 et le diamètre des prises de pression 17,18 sont dimensionnés pour que le niveau des forces de pression subsiste tant que missile et accéléra­teur sont en contact pendant la phase de séparation. Le diamètre de l'espace interne 16 détermine en partie le niveau des forces de pression.The volume of the internal space 16 and the diameter of the pressure taps 17, 18 are dimensioned so that the level of the pressure forces remains as long as the missile and the accelerator are in contact during the separation phase. The diameter of the internal space 16 partly determines the level of the pressure forces.

On remarquera que la pression totale (statique et dynamique) fonction de la vitesse de l'écoulement, est transmise à l'espace interne 16. Cette pression s'exerce à la fois sur la face avant 19 de l'accélérateur 2 et sur le culot 20 du reste 3 du missile 1. Elle développe sur l'avant de l'accélérateur, une force tendant à le freiner et sur l'arrière du missile, une force tendant à l'éjecter de l'encastrement 4,7-5,8-9,10. Ces forces, de par leur origine même, sont de l'ordre de grandeur des forces de traînée intervenant par leur différence dans le bilan des forces favorables à la séparation. Mais c'est leur somme qui s'ajoute à ce bilan de forces. Il en résulte un mouvement relatif très dynamique du reste 3 du missile 1 par rapport à l'accélérateur 2, qui survient dès le début de la queue de poussée d'accélération de ce dernier.It will be noted that the total pressure (static and dynamic) as a function of the speed of the flow, is transmitted to the internal space 16. This pressure is exerted both on the front face 19 of the accelerator 2 and on the base 20 of the rest 3 of the missile 1. It develops on the front of the accelerator, a force tending to brake it and on the rear of the missile, a force tending to eject it from the embedding 4,7-5 , 8-9.10. These forces, by their very origin, are of the order of magnitude of the drag forces involved in their difference in the balance of forces favorable to separation. But it is their sum which is added to this balance of forces. This results in a very dynamic relative movement of the remainder 3 of the missile 1 relative to the accelerator 2, which occurs from the start of the acceleration thrust tail of the latter.

Dans la variante de réalisation de la figure 4, les prises de pression saillantes 18 ont été supprimées et remplacées par des prises de pression arasantes 21.In the alternative embodiment of FIG. 4, the protruding pressure taps 18 have been eliminated and replaced by leveling pressure taps 21.

L'invention permet d'accroître fortement la fiabilité de la séparation naturelle. Cette dernière est, en effet systématique, grâce aux forces ajoutées. De plus, la rapidité du mouvement relatif de séparation supprime tout risque de choc entre le reste 3 du missile 1 et l'accéléra­teur 2, après déboîtement de l'encastrement 4,7-5,8-9,10. En outre, l'instant de séparation n'est plus soumis qu'aux dispersions inhérentes à la propulsion, c'est-à-dire au temps de combustion du propulseur d'accélération 2.The invention makes it possible to greatly increase the reliability of natural separation. The latter is, in fact systematic, thanks to the added forces. In addition, the speed of the relative separation movement removes all risk of shock between the rest 3 of the missile 1 and the accelerator 2, after disengagement of the embedding 4,7-5,8-9,10. In addition, the instant of separation is no longer subject only to the dispersions inherent in the propulsion, that is to say the combustion time of the acceleration propellant 2.

Le coût de ce gain de fiabilité est quasiment nul, étant donné la simplicité de mise en oeuvre de l'invention. Il n'y a ni augmentation de poids, ni pièces mécaniques en mouvement, ni commande de mise en service ou d'armement avant le tir du missile 1. Entièrement statique et inerte, le dispositif de l'invention est évidemment très fiable.The cost of this gain in reliability is almost zero, given the simplicity of implementing the invention. There is no increase in weight, no mechanical moving parts, no command to commission or arm before the firing of missile 1. Fully static and inert, the device of the invention is obviously very reliable.

De plus, puisque le rôle de la traînée du propulseur 2 n'est plus prépondérant dans la séparation, cette traînée peut être volontairement réduite, par exemple par diminution du diamètre de l'accélérateur ou amélioration aérodynamique du contour de celui-ci. Il en résulte un gain de poids et une économie de l'énergie de propulsion.In addition, since the role of the propellant 2 drag is no longer preponderant in the separation, this drag can be voluntarily reduced, for example by reducing the diameter of the accelerator or aerodynamic improvement of the contour thereof. This results in weight gain and savings in propulsion energy.

Par ailleurs, dans le cas où le prévoierait un dispositif de verrouillage longitudinal (non représenté) entre l'accélérateur 2 et le reste 3 du missile 1, on voit que l'on peut utiliser la pression à l'intérieur de l'espace interne 16 pour déverrouiller ledit dispositif de verrouil­lage de la liaison glissante 4,7-5,8 en vol, après mise à feu.Furthermore, in the case where a longitudinal locking device (not shown) is provided between the accelerator 2 and the rest 3 of the missile 1, it can be seen that the pressure can be used inside the internal space 16 to unlock said sliding link locking device 4,7-5,8 in flight, after firing.

Bien entendu, la présente invention s'applique à d'autres modes de réalisation que celui représenté sur les figures. Divers ajustements du type de celui décrit peuvent être utilisés, avec des surfaces de guidage variables, selon le contrôle désiré pendant la course d'extraction et les moments d'encastrement à supporter pendant le vol.Of course, the present invention applies to other embodiments than that shown in the figures. Various adjustments of the type described can be used, with variable guide surfaces, depending on the control desired during the extraction run and the embedding moments to be supported during the flight.

Claims (8)

1 - Engin aérien (1) comportant au moins un propulseur (2), temporaire et largable, lié au reste (3) dudit engin par un ajustement (4,7-5,8-9,10) susceptible de permettre audit propulseur de glisser parallèlement à son axe dans le sens opposé audit reste (3) de l'engin,
caractérisé en ce qu'une communication (17) est établie entre, d'une part, l'espace (16) interne audit ajustement et disposé entre l'avant dudit propulseur et ledit reste (3) de l'engin, et, d'autre part, l'écoulement aérodynami­que autour dudit engin (1).1 - Air vehicle (1) comprising at least one propellant (2), temporary and releasable, linked to the rest (3) of said machine by an adjustment (4,7-5,8-9,10) capable of allowing said propellant to slide parallel to its axis in the direction opposite to said rest (3) of the machine,
characterized in that a communication (17) is established between, on the one hand, the space (16) internal to said adjustment and arranged between the front of said propellant and said rest (3) of the machine, and, d 'other hand, the aerodynamic flow around said machine (1). 2- Engin selon la revendication 1,
caractérisé en ce que ladite communication est établie à travers ledit propulseur (2).2- A machine according to claim 1,
characterized in that said communication is established through said thruster (2). 3 - Engin selon la revendication 2, dans lequel ledit propulseur (2) a un diamètre supérieur à celui de la partie (3) dudit engin sur laquelle il est monté et dans lequel ladite partie (3) est raccordée audit propulseur (2) par une paroi divergente (14) liée à celui-ci,
caractérisée en ce que ladite communication est établie à travers ladite paroi divergente.3 - Machine according to claim 2, wherein said propellant (2) has a diameter greater than that of the part (3) of said machine on which it is mounted and in which said part (3) is connected to said propellant (2) by a divergent wall (14) linked thereto,
characterized in that said communication is established through said divergent wall. 4- Engin selon l'une quelconque des revendications 1 à 3, caractérisé en ce que ladite communication est multiple.4- Machine according to any one of claims 1 to 3, characterized in that said communication is multiple. 5- Engin selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'il comprend au moins un conduit (17) débouchant à la périphérie dudit engin.5- Machine according to any one of claims 1 to 4, characterized in that it comprises at least one conduit (17) opening at the periphery of said machine. 6 - Engin selon la revendication 5,
caractérisé en ce que ledit conduit (17) est prolongé à l'extérieur dudit engin par une prise d'air (18).6 - Machine according to claim 5,
characterized in that said duct (17) is extended outside of said machine by an air intake (18). 7 - Engin selon la revendication 6,
caractérisé en ce que ladite prise d'air (18) est sensible­ment parallèle à l'axe de l'engin et dirigée vers l'avant de celui-ci.7 - Machine according to claim 6,
characterized in that said air intake (18) is substantially parallel to the axis of the machine and directed towards the front thereof. 8 - Engin selon l'une quelconque des revendications 1 à 7, caractérisé en ce que l'étanchéité dudit ajustement glissant est réalisée à l'aide d'un lubrifiant.8 - Machine according to any one of claims 1 to 7, characterized in that the sealing of said sliding adjustment is carried out using a lubricant.
EP89400663A 1988-03-30 1989-03-09 Airborne vehicle with at least one releasable propulsion unit Expired - Lifetime EP0335761B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8804213 1988-03-30
FR8804213A FR2629583B1 (en) 1988-03-30 1988-03-30 AIRCRAFT PROVIDED WITH AT LEAST ONE WIDTHABLE PROPELLER

Publications (2)

Publication Number Publication Date
EP0335761A1 true EP0335761A1 (en) 1989-10-04
EP0335761B1 EP0335761B1 (en) 1993-01-20

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EP89400663A Expired - Lifetime EP0335761B1 (en) 1988-03-30 1989-03-09 Airborne vehicle with at least one releasable propulsion unit

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US (1) US4903605A (en)
EP (1) EP0335761B1 (en)
JP (1) JP2954948B2 (en)
CA (1) CA1332537C (en)
DE (1) DE68904453T2 (en)
ES (1) ES2037972T3 (en)
FR (1) FR2629583B1 (en)

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FR2791130A1 (en) 1999-03-19 2000-09-22 Celerg MACHINE PROVIDED WITH A WIDE PYROTECHNIC EJECTOR
WO2018017166A1 (en) * 2016-07-22 2018-01-25 Raytheon Company Stage separation mechanism and method

Families Citing this family (3)

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SE508475C2 (en) * 1993-03-30 1998-10-12 Bofors Ab Method and apparatus for spreading combat parts
EP2002198B1 (en) * 2006-03-30 2013-04-24 Raytheon Company Methods and apparatus for integrated locked thruster mechanism
JP5634785B2 (en) * 2010-07-30 2014-12-03 株式会社Ｉｈｉエアロスペース Flying object

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Publication number Priority date Publication date Assignee Title
FR2791130A1 (en) 1999-03-19 2000-09-22 Celerg MACHINE PROVIDED WITH A WIDE PYROTECHNIC EJECTOR
DE10013745C2 (en) * 1999-03-19 2002-12-05 Celerg Immeuble Jura Ct D Affa Missile equipped with a detachable, pyrotechnic ejector
WO2018017166A1 (en) * 2016-07-22 2018-01-25 Raytheon Company Stage separation mechanism and method
US10222189B2 (en) 2016-07-22 2019-03-05 Raytheon Company Stage separation mechanism and method
US10514241B1 (en) 2016-07-22 2019-12-24 Raytheon Company Stage separation mechanism and method
EP3663704A1 (en) * 2016-07-22 2020-06-10 Raytheon Company Stage separation mechanism and method

Also Published As

Publication number Publication date
JP2954948B2 (en) 1999-09-27
US4903605A (en) 1990-02-27
EP0335761B1 (en) 1993-01-20
DE68904453T2 (en) 1993-06-03
JPH0210100A (en) 1990-01-12
FR2629583A1 (en) 1989-10-06
ES2037972T3 (en) 1993-07-01
CA1332537C (en) 1994-10-18
DE68904453D1 (en) 1993-03-04
FR2629583B1 (en) 1993-06-18

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