EP0908696B1 - Dispositif de commande automatique d'au moins un élément mobile tel qu'une dérive ventrale de missile - Google Patents
Dispositif de commande automatique d'au moins un élément mobile tel qu'une dérive ventrale de missile Download PDFInfo
- Publication number
- EP0908696B1 EP0908696B1 EP19980402267 EP98402267A EP0908696B1 EP 0908696 B1 EP0908696 B1 EP 0908696B1 EP 19980402267 EP19980402267 EP 19980402267 EP 98402267 A EP98402267 A EP 98402267A EP 0908696 B1 EP0908696 B1 EP 0908696B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- piston
- missile
- unlocking member
- rest position
- designed
- 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
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Classifications
-
- 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 invention relates to a device designed to automatically order at least one item mobile of a missile, such as a ventral drift, when the missile is fired from an aircraft.
- the device according to the invention can be installed on all types of missiles likely to be from an airplane or a helicopter, as soon as the ejection of the missile must be accompanied by the work of one or more moving elements.
- ventral fins A preferred application concerns the control of the ventral fins. Indeed, some types of missiles capable of being embarked on aircraft have ventral fins which are retracted as long as the missile remains attached to the aircraft, to limit the drag. These drifts must then be deployed immediately when the missile is pulled to stabilize it in the "separation" phase.
- the device according to the invention can however be used to control automatic implementation other mobile missile components such as control surfaces, or others.
- the attachment mechanism comprises usually a front ring and a rear ring linked to the missile body, as well as a front hook and a rear hook, both retractable, mounted in the mast so that it can engage with the missile rings.
- ejector pistons are also housed in the mast carrying, in order to apply a force to the missile downward ejection, when the hooks are retracted. Ejector pistons thus facilitate the separation of the missile and the aircraft.
- a known technique is to use the movement of retraction of one of the rings, for example the ring back, to let out a finger allowing the release of a spring acting as striker and triggering the ignition of a pyrotechnic line of control of the ventral fins.
- SL wires safety release wires
- the subject of the invention is precisely a device for controlling at least one element mobile of a missile, such as its ventral fins, in improving the safety of ground personnel, without reduce the reliability of the command, without causing major modification of the interfaces between the missile and the mast, and without requiring any intervention outside before or after the execution of a mission.
- the external face of the unlocking member is substantially flush with the outer face of the missile when the body of unlocking is in rest position.
- elastic means automatically bring the organ of unlocking in its rest position after the application of the ejection force.
- the unlocking member comprises a first piston, able to slide in a blind bore and on which the above-mentioned outer face is formed.
- the elastic means are interposed between the bottom of the blind bore and a second piston capable of sliding coaxially in the first piston.
- the organ of blocking then includes a frangible pin crossing the first and second simultaneously pistons.
- the unlocking member comprises also a ring surrounding the first piston and in which is formed a slot oriented parallel to the axis of the first piston.
- This slot has a enlarged part, on the side of the outer face of the first piston and a recess is delimited between this and the ring, at least in front of the slot.
- a control rod is mounted sliding in the first piston, parallel to its axis.
- This control rod is in support by its opposite ends respectively against the bottom of the blind bore and against a cover on the outside of the first piston, when it is in the rest position.
- the bringing of the first piston in active position by application of force ejection results in an ejection of the seal by the control rod.
- the actuator can then include a third piston capable of sliding in a bore opening into the blind bore.
- This third piston has an enlarged end which is held in the recess when the unlocking member is in the rest position, and which crosses the widened part of the slit, under the action of the second means elastic, when the unlocking member is in active position.
- the third piston includes a striker finger capable of fire this line in the active position of the actuator.
- the striker finger can be replaced by an electrical contact or any other system for implementing an order, electric or other, likely to replace the line pyrotechnic.
- the invention is advantageously applied to the control of daggerboards missiles.
- the reference 10 designates a structural element of an aircraft, such as a structural element wing or fuselage.
- a carrying mast 12 Under the structural element 10 is mounted a carrying mast 12, on which a missile 14 is suspended.
- attachment mechanism by which the missile 14 is held under the carrying mast 12 is a mechanism of classic hooking, comparable to that which is described in document FR-A-2 210 538. This mechanism does not is not part of the invention and therefore will not be made of detailed description.
- such hanging mechanism usually includes a front ring and a rear ring secured to the missile, one front hook and one rear hook, all two retractable, mounted in the carrying mast 12, as well as ejector pistons also mounted in the carrying mast, usually near the hooks retractable.
- ejector pistons near the rear hook is shown schematically at 16 on Figure 1.
- the hooks When firing the missile, the hooks are brought into their retracted position, usually by swiveling, using a control system appropriate. The retraction of the hooks is accompanied by a actuation of the ejector pistons 16. These then move down to help with separation missile and aircraft, repelling the missile in the same direction by their underside, which is in contact with the upper face of missile 14.
- a device 18 for automatic control of the deployment of daggerboards ventral 20, placed at the rear of missile 14, is fully integrated into the body and located opposite the ejector piston 16, as illustrated in figure 1. More specifically, the control device 18 is integrated into the upper part of the body missile, so that its upper surface is flush the upper face of the missile body.
- control device 18 A preferred embodiment of the control device 18 will now be described in detail with reference to Figures 2 and 3.
- the device 18 comprises a body 22 provided for be fixed in a housing provided for this purpose in the upper part of the missile body. This fixation can in particular be made by means of screws (not shown).
- the body 22 of the device control 18 is traversed over its entire thickness by a bore 26.
- this bore 26 is closed by a plate 28 attached to the body 22, for example by means of screws (not shown). bore 26 thus forms a blind bore closed towards down and open up.
- An unlocking member 29, comprising a first piston 30 and a ring 32, is mounted sliding in the blind bore 26, so that move between a high rest position, illustrated in Figures 2 and 3 and a low position active (not shown).
- the first piston 30 is presented under the shaped like a hollow cylinder, closed at its end higher.
- the upper face 36 of the piston 30 forms the outer face of the unlocking member 29. It is in contact with the underside of the piston ejection 16 (FIG. 1) when the missile 14 is hung under the carrying mast 12.
- the piston 30 On its outer peripheral surface, the piston 30 has a hollow annular part, on which is mounted the ring 32. This assembly is such that an annular space 38 is delimited between the piston 30 and the ring 32.
- balls 34 can advantageously be trapped in notches formed at the ends of the ring 32. In order to reduce friction, the release 29 is then in contact with the bore blind 26 by these balls 34.
- the piston 30 In the high rest position of the organ unlocking 29, the piston 30 is pressed against a shoulder 35 formed in the blind bore 26, near the high end of it.
- the position of the unlocking device corresponds to contrary to its coming to bear against the plate 28.
- the first piston 30 delimits internally a blind bore 40, open downwards and closed up.
- a second piston 42 is mounted in this blind bore 40, so as to be arranged coaxially with the first piston 30.
- a locking member consisting of a frangible pin 44
- the pin 44 is arranged to so as to be placed partly in the first piston 30 and partly in the second piston 42. In these conditions, the upper end of the second piston 42 is spaced from the closed top end of the blind bore 40, while the lower end of this second piston is flush with the plate 28 forming the bottom of the bore blind 26.
- the pin 44 is dimensioned so as to break or shear automatically when a predetermined ejection force is applied towards the bottom, by the ejector piston 16, on the upper face 36 of the first piston 30. A relative sliding between the pistons 30 and 42 then become possible.
- the second piston 42 is presented under the shaped like a hollow cylinder, closed at its upper end.
- Elastic means constituted by a spring compression helical 48 are placed inside of this second piston 42, so that their low end is in abutment against plate 28 and that their upper end is in abutment against the part high closed piston 42.
- the spring 48 makes it possible to maintain the first piston 30 bearing against the shoulder 35 of blind bore 26, via pin frangible 44, when it is intact.
- the first piston 30 In parallel to its axis, the first piston 30 is traversed over its entire length by a hole 50, in which a control rod 52 is placed.
- the control rod 52 protrudes down beyond the underside piston 30, so as to be in abutment against the plate 28 by its lower end.
- the upper end of the control rod 52 is then located near a cover 54, housed in an enlarged end of the bore 50, so as to be flush with the upper face 36 of the piston 30.
- the body 22 of the control device 18 is crossed by a second bore 56, which opens into the blind bore 26 and whose horizontal axis is perpendicular to the vertical axis of this blind bore.
- This second bore 56 slidably receives a third piston 58, which constitutes an organ actuating the ventral daggerboards 20 of the missile.
- the second bore 56 includes a part 56a, of relatively large diameter, closed by a screw cap 74 at its end remote from the bore blind 26, and part 56b, of relatively small diameter, opening into the blind bore 26.
- the third piston 58 has a diameter portion uniform that slides in part 56b of relatively small diameter of bore 56.
- the third piston 58 includes a part 59 in the form of disc, which slides in part 56a of relatively large diameter of bore 56.
- the part 59 in the form of disc has in its center a striker finger 60.
- the third piston 58 has a extension 64, rod-shaped, terminated by a widened end 62, disc-shaped.
- slot 66 As illustrated in Figure 2, the ring 32 is crossed by a slot 66, parallel to the axis of the first piston 30, in an area opposite the third piston 58. Over most of its height, slot 66 has a uniform width slightly greater than the diameter of the extension 64, piston rod 58, but less than diameter of the widened end 62. The slot 66 however has an enlarged upper part 68, of circular shape, the diameter of which is greater than that of the end 62 of the piston 58.
- Elastic means consisting of a compression helical spring 70, are interposed between the body 22 of the device and the third piston 58, so as to urge it to the right in considering Figure 2.
- the spring 70 is mounted in part 56a of bore 56, around the piston 58, so as to be supported by one of its ends against the disc-shaped part 59 and, by its opposite end, against the separating shoulder the parts 56a and 56b of the bore 56.
- spring 70 moves the third piston 58 to the right considering the Figure 2.
- the striker finger 60 then strikes a detonator 72, mounted in the plug 74.
- the detonator 72 constitutes in this case the firing element of a pyrotechnic line used to operate pyrotechnic cylinders (not shown) for controlling the ventral fins 20 of the missile 14 (figure 1).
- the finger of the striker 60 can be replaced, for example, by a electrical contact likely to close a circuit electric implementation of electric cylinders actuation of the ventral fins, or by any other technically equivalent control system.
- the pin frangible 44 is designed to break automatically under the effect of the ejection force which is applied to the upper face 36 of the first piston 30, when the ejector piston 16 of FIG. 1 is activated.
- control device according to the invention guarantees maximum security for staff on the ground.
- the pin 44 is calibrated so that it prohibits any setting untimely work of the device on the ground, for example when the missile is off the mast, without that no human intervention is necessary during when the aircraft returns from mission.
- the device is thus constantly in working order, without that no intervention is necessary for the lock or unlock it.
- the interfaces between the missile and the carrying mast remain practically unchanged by compared to those that equip structures existing. From this point of view, it should be noted that the device is reduced in height and adaptable under all the types of carrying masts fitted with ejector pistons, depending on the location of these pistons and the minimum ejection force guaranteed by the manufacturer.
- the device can be used to control the setting work of one or more moving elements such as ventral fins, by means of systems pyrotechnic, electric or other.
Landscapes
- 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)
- Bidet-Like Cleaning Device And Other Flush Toilet Accessories (AREA)
Description
- un organe de déverrouillage dont une face extérieure est agencée de façon à subir la force d'éjection, lorsque celle-ci est appliquée, pour se déplacer d'une position de repos dans une position active, dans laquelle l'élément mobile est actionné ; et
- un organe de blocage maintenant normalement l'organe de déverrouillage dans sa position de repos, et apte à se rompre lorsque la force d'éjection est appliquée sur ladite face extérieure.
- un organe d'actionnement de l'élément mobile, maintenu normalement dans une position inactive par l'organe de déverrouillage lorsque celui-ci occupe sa position de repos, et automatiquement désaccouplé de l'organe de déverrouillage lorsque celui-ci est en position active ; et
- des deuxièmes moyens élastiques sollicitant l'organe d'actionnement vers une position de commande de l'élément mobile.
- la figure 1 est une vue de côté représentant schématiquement un missile suspendu sous une structure d'aéronef et dont les dérives ventrales sont déployées automatiquement, lors d'un tir, par un dispositif de commande conforme à l'invention ;
- la figure 2 est une vue en coupe longitudinale d'une forme de réalisation préférée d'un tel dispositif de commande automatique ; et
- la figure 3 est une vue en coupe selon la ligne III-III de la figure 2.
Claims (10)
- Dispositif de commande automatique d'au moins un élément mobile (20) d'un missile (14) apte à être éjecté d'un aéronef, lorsqu'une force d'éjection est appliquée sur le missile, ce dispositif étant caractérisé par le fait qu'il est totalement intégré dans le corps du missile et comprend :un organe de déverrouillage (29) dont une face extérieure (36) est agencée de façon à subir la force d'éjection, lorsque celle-ci est appliquée, pour se déplacer d'une position de repos dans une position active, dans laquelle l'élément mobile (20) est actionné ; etun organe de blocage (44) maintenant normalement l'organe de déverrouillage (29) dans sa position de repos, et apte à se rompre lorsque la force d'éjection est appliquée sur ladite face extérieure (36).
- Dispositif selon la revendication 1, dans lequel la face extérieure (36) de l'organe de déverrouillage (29) affleure sensiblement la face extérieure du missile, lorsque l'organe de déverrouillage est en position de repos.
- Dispositif selon l'une quelconque des revendications 1 et 2, dans lequel des moyens élastiques (48) ramènent automatiquement l'organe de déverrouillage (29) dans sa position de repos, après l'application de ladite force d'éjection.
- Dispositif selon la revendication 3, dans lequel l'organe de déverrouillage comprend un premier piston (30), apte à coulisser dans un alésage borgne (26) et sur lequel est formé ladite face extérieure (36), les moyens élastiques (48) étant interposés entre le fond de cet alésage borgne et un deuxième piston (42), apte à coulisser coaxialement dans le premier piston, l'organe de blocage comprenant une goupille frangible (44) traversant simultanément le premier et le deuxième pistons.
- Dispositif selon la revendication 4, dans lequel l'organe de déverrouillage (29) comprend également une bague (32) entourant le premier piston (30) et dans laquelle est formée une fente (66) orientée parallèlement à l'axe du premier piston, ladite fente présentant une partie élargie (68), du côté de la face extérieure (36) du premier piston (30) et un évidement (38) étant délimité entre le premier piston (30) et la bague (32), au moins en face de la fente (66).
- Dispositif selon l'une quelconque des revendications 4 et 5, dans lequel une tige témoin (52), apte à coulisser dans le premier piston (30) parallèlement à son axe, est en appui par ses extrémités opposées respectivement contre le fond de l'alésage borgne (26) et contre un opercule (54) placé sur la face extérieure du premier piston, lorsque celui-ci est en position de repos.
- Dispositif selon l'une quelconque des revendications précédentes, comprenant de plus :un organe d'actionnement (58) de l'élément mobile, maintenu normalement dans une position inactive par l'organe de déverrouillage (30,32) lorsque celui-ci occupe sa position de repos, et automatiquement désaccouplé de l'organe de déverrouillage, lorsque celui-ci est en position active ; etdes deuxièmes moyens élastiques (70) sollicitant l'organe d'actionnement (58) vers une position de commande de l'élément mobile.
- Dispositif selon les revendications 6 et 7 combinées, dans lequel l'organe d'actionnement comprend un troisième piston (58) apte à coulisser dans un alésage (56) débouchant dans l'alésage borgne (26), ce troisième piston présentant une extrémité élargie (62) maintenue dans ledit évidement (38)lorsque l'organe de déverrouillage (30,32) est en position de repos, et apte à traverser la partie élargie (68) de la fente (66) lorsque l'organe de déverrouillage est en position active.
- Dispositif selon la revendication 8, dans lequel le troisième piston (58) comprend un doigt de percuteur (60), apte à déclencher la mise à feu d'une ligne pyrotechnique de commande de l'élément mobile, dans la position active de l'organe d'actionnement.
- Dispositif selon l'une quelconque des revendications précédentes, appliqué à la commande de dérives ventrales (20) d'un missile (14).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9711493A FR2768503B1 (fr) | 1997-09-16 | 1997-09-16 | Dispositif de commande automatique d'au moins un element mobile tel qu'une derive ventrale de missile |
FR9711493 | 1997-09-16 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0908696A1 EP0908696A1 (fr) | 1999-04-14 |
EP0908696B1 true EP0908696B1 (fr) | 2002-04-24 |
Family
ID=9511116
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19980402267 Expired - Lifetime EP0908696B1 (fr) | 1997-09-16 | 1998-09-15 | Dispositif de commande automatique d'au moins un élément mobile tel qu'une dérive ventrale de missile |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0908696B1 (fr) |
DE (1) | DE69805034T2 (fr) |
ES (1) | ES2175634T3 (fr) |
FR (1) | FR2768503B1 (fr) |
NO (1) | NO317638B1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110775277B (zh) * | 2019-12-06 | 2024-04-19 | 中国工程物理研究院总体工程研究所 | 一种具有同步性的无人机机载微小型导弹投放分离装置 |
CN115493462A (zh) * | 2022-08-29 | 2022-12-20 | 中国兵器工业第二一三研究所 | “十”字型四路弹翼同步解锁机构 |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2261173C3 (de) | 1972-12-14 | 1979-06-13 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Vorrichtung zum lösbaren Festlegen |
DE2648523C3 (de) * | 1976-10-27 | 1979-09-27 | Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen | Gleitgeschoß mit abwerfbarer Kielflosse |
DE2827781C2 (de) * | 1978-06-24 | 1985-11-14 | Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn | Ankopplungskopf für Außenlasten an Flugzeugen |
US5141175A (en) * | 1991-03-22 | 1992-08-25 | Harris Gordon L | Air launched munition range extension system and method |
-
1997
- 1997-09-16 FR FR9711493A patent/FR2768503B1/fr not_active Expired - Fee Related
-
1998
- 1998-09-11 NO NO19984215A patent/NO317638B1/no not_active IP Right Cessation
- 1998-09-15 EP EP19980402267 patent/EP0908696B1/fr not_active Expired - Lifetime
- 1998-09-15 ES ES98402267T patent/ES2175634T3/es not_active Expired - Lifetime
- 1998-09-15 DE DE1998605034 patent/DE69805034T2/de not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
ES2175634T3 (es) | 2002-11-16 |
DE69805034D1 (de) | 2002-05-29 |
NO317638B1 (no) | 2004-11-29 |
NO984215L (no) | 1999-03-17 |
DE69805034T2 (de) | 2002-11-28 |
FR2768503A1 (fr) | 1999-03-19 |
FR2768503B1 (fr) | 1999-12-03 |
EP0908696A1 (fr) | 1999-04-14 |
NO984215D0 (no) | 1998-09-11 |
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