EP0908696B1 - Automatic control device of at least a mobile element such as a ventral fin of a missile - Google Patents

Description

Technical area

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.

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.

State of the art

When a missile is carried on a aircraft it is suspended from a structural element of this, such as a wing or fuselage element, by a hanging mechanism integrated in a room called "carrying mast".

As illustrated in particular by the document FR-A-2 210 538, 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. To facilitate the separation of missile and aircraft when the missile is fired, 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.

On existing missiles, when firing of the missile must be accompanied by the implementation moving parts such as ventral fins, 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.

This existing technique is not satisfactory from a safety point of view ground staff. When the aircraft returns from mission without the missile being fired, an operator must lock the device by installing safety pins. If, for any reason, this operation is not performed, the device triggers when the missile is dropped, as it would during a shot. This constitutes an accident risk that it is desirable to eliminate.

Another technique consists of the use of SL (safety release) wires. During the one end of the SL wire (hooked to the mast) pulls on the other end to trigger an order. However, the use of SL wires implies the application of procedures before departure on mission and upon return from mission, what it is desirable to eliminate for avoid any risk of human error.

Statement of the invention

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.

• 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.

According to the invention, this result is obtained by means of an automatic control device for at least one mobile element of a missile capable of being ejected from an aircraft, when an ejection force is applied to the missile, this device being characterized by the fact that it is completely integrated into the body of the missile and comprises:

• an unlocking member, an outer face of which is arranged so as to undergo the ejection force, when the latter is applied, to move from a rest position to an active position, in which the movable element is actuated; and
• a blocking member normally holding the unlocking member in its rest position, and capable of breaking when the ejection force is applied to said outer face.

Preferably, so as not to disturb air flow around the missile in the area of implantation of the device, 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. In addition, elastic means automatically bring the organ of unlocking in its rest position after the application of the ejection force.

In a preferred embodiment of the invention, 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.

In this preferred embodiment of the invention, 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.

Preferably, 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. Visual inspection of the presence or absence of the seal, performed on the ground by an operator, so you can know immediately whether the device worked or not.

• 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.

In a particular embodiment of the invention, the device further comprises:

• an actuating member of the movable member, normally maintained in an inactive position by the unlocking member when the latter occupies its rest position, and automatically uncoupled from the unlocking member when the latter is in the active position ; and
• second elastic means urging the actuating member towards a position for controlling the movable element.

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.

When the control of the movable element is carried out by means of a pyrotechnic line, the third piston includes a striker finger capable of fire this line in the active position of the actuator. He is at note that as a variant, 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.

As already observed, the invention is advantageously applied to the control of daggerboards missiles.

Brief description of the drawings

• 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.

A preferred embodiment of the invention will now be described, by way of nonlimiting example, with reference to the appended drawings, in which:

• FIG. 1 is a side view schematically representing a missile suspended under an aircraft structure and the ventral fins of which are deployed automatically, when fired, by a control device according to the invention;
• Figure 2 is a longitudinal sectional view of a preferred embodiment of such an automatic control device; and
• Figure 3 is a sectional view along line III-III of Figure 2.

Detailed description of an embodiment favorite

In FIG. 1, the reference 10 designates a structural element of an aircraft, such as a structural element wing or fuselage.

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.

To facilitate the understanding of the invention, it will simply be recalled here that 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. One of these ejector pistons (near the rear hook) is shown schematically at 16 on Figure 1.

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.

According to the invention, 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.

A preferred embodiment of the control device 18 will now be described in detail with reference to Figures 2 and 3.

In the embodiment of 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).

Perpendicular to its upper side horizontal 24, provided for flush with the face upper part of the missile body, i.e. according to a vertical direction, the body 22 of the device control 18 is traversed over its entire thickness by a bore 26. At its lower end, 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.

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.

As illustrated in particular in Figure 2, 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.

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. When the device did not work and as illustrated by Figures 2 and 3, a locking member, consisting of a frangible pin 44, is received in a hole 46 radially passing through both pistons 30 and 42. More specifically, 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.

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. When the first piston 30 occupies its rest position illustrated in FIGS. 2 and 3, 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.

As illustrated in particular in the figure 2, 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.

Over most of its length, the third piston 58 has a diameter portion uniform that slides in part 56b of relatively small diameter of bore 56. At its end farthest from blind bore 26, 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. On its forming face the end of the piston 58, the part 59 in the form of disc has in its center a striker finger 60.

At its opposite end, turned towards the side of the bore 26, the third piston 58 has a extension 64, rod-shaped, terminated by a widened end 62, disc-shaped.

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.

As Figure 2 illustrates, when the unlocking member 29 occupies its position rest, the widened end 62 of the piston 58 is trapped in space 38 while resting on the ring 32, on either side of the slot 66. In on the other hand, when the unlocking member 29 occupies its active position, the enlarged end 62 of the piston 58 is in front of the widened part 68 of the slot 66, so that this piston 58 can move freely to the right considering figure 2.

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. For this purpose, 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.

Therefore, when the enlarged end 62 of the third piston 58 is located opposite the enlarged part 68 of slot 66, 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).

It should be noted that, as a variant, 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.

Operation of the control device which has just been described with reference to FIGS. 2 and 3 will now be explained.

As already mentioned, 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.

Consequently, the actuation of the pistons missile latching mechanism ejectors 14, which occurs automatically when fired, has the effect of break pin 44 and move the first piston 30 down from its rest position illustrated on Figures 2 and 3 in its active position (not shown).

In the active position of the first piston 30, its underside bears against the plate 28 sealing the bore 26. The enlarged end 62 of the third piston 58 is then opposite the enlarged upper part 68 of slot 66. By therefore, the third piston 58 is no longer retained by the ring 32 and the spring 70 has the effect of propel this piston 58 towards the detonator 72. When the striker finger 60 strikes the detonator 72, the pyrotechnic line controlling the operation of pyrotechnic cylinders for the ventral missile fins is ignited. The ventral fins are thus automatically brought into their active position, and the missile can execute its mission.

Since the length of the rod witness 52 is greater than the thickness of the first piston 30, the passage of the latter in its active state also results in an ejection of the cover 54 by the control rod 52. The latter, which is received without play in the hole 50, then protrudes from the upper face 36 of the first piston 30. By therefore, assuming that the implementation of the control device intervened on the ground by inadvertently or during a preliminary test, a simple visual examination allows an observer on the ground to be informed.

Immediately after the separation of the missile from its carrying mast 12, the ejection force exerted by the ejector piston 16 on the upper face 36 of the first piston 30 disappears. Compression spring 48 a then the effect of moving up the whole constituted by the second piston 42, the first piston 30 and ring 32, until the first one comes to bear piston 30 against the shoulder 35 formed in the bore blind 26. Consequently, the upper face 36 of the piston 30 is brought back to the surface exterior of the missile body in the adjacent part to device 18. As a result, the flow of air around the body of the missile in flight is not disturbed by the control device 18 according to the invention.

The foregoing description makes it appear clearly that the control device according to the invention guarantees maximum security for staff on the ground. Indeed, 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.

In addition, the reliability of the functioning is preserved, since the pin 44 is calibrated so as to rupture under the effect of actuation of the ejection piston, when firing the missile.

As already observed, the device is thus constantly in working order, without that no intervention is necessary for the lock or unlock it.

Finally, 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.

Finally, as already noted, 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.

Claims (10)

1. Automatic control device of at least one mobile element (20) of a missile (14) intended to be ejected from an aircraft, when an ejection force is applied to the missile, this device being characterised by the fact that it is totally integrated into the body of the missile and comprises:

   an unlocking member (29) of which one external face (36) is arranged in such a way as to receive the ejection force, when the latter is applied, to shift it from a rest position into an active position, in which the mobile element (20) is activated; and

   a blocking member (44) normally maintaining the unlocking member (29) in its rest position and designed to rupture when the ejection force is applied to the said external face (36).
2. Device according to Claim 1, in which the external face (36) of the unlocking member (29) is substantially flush with the external face of the missile when the unlocking member is in its rest position.
3. Device according to one of Claims 1 and 2, in which elastic means (48) automatically restore the unlocking member (29) to its rest position after the application of the said ejection force.
4. Device according to Claim 3, in which the unlocking member comprises a first piston (30) designed to slide in a blind bore (26) and on which is formed the said external face (36), the elastic means (48) being interposed between the base of this blind bore and a second piston (42) designed to slide coaxially within the first piston, the blocking member comprising a frangible pin (44) passing simultaneously through the first and second pistons.
5. Device according to Claim 4, in which the unlocking member (29) also includes a ring (32) surrounding the first piston (30) and in which is formed a slot (66) orientated parallel to the axis of the first piston, the said slot having an enlarged portion (68) at the end towards the external face (36) of the first piston (30) and a recess (38) being defined between the first piston (30) and the ring (30), at least opposite the slot (66).
6. Device according to one of Claims 4 and 5, in which a tell-tale pin (52), designed to slide in the first piston (30) parallel to its axis, has its opposite ends in engagement respectively against the end of the blind bore (26) and against a cover (54) placed on the external face of the first piston when the latter is in its rest position.
7. Device according to any one of the foregoing Claims, comprising in addition:

   an actuating member (58) for the mobile element, normally maintained in an inactive position by the unlocking member (30, 32) when the latter occupies its rest position, and automatically disengaged from the unlocking member when the latter is in its active position; and

   second elastic means (70) urging the actuating member (58) towards a position for controlling the mobile element.
8. Device according to Claims 6 and 7 taken together, in which the actuating member comprises a third piston (58) designed to slide in a bore (56) opening into the blind bore (26), this third piston having an enlarged end (62) held in the said recess (38) when the unlocking member (30, 32) is in its rest position, and designed to enter the enlarged portion (68) of the slot (66) when the unlocking member is in its active position.
9. Device according to Claim 8, in which the third piston (58) has a firing pin (60), designed to initiate the firing of a pyrotechnic control line of the mobile element in the active position of the actuating member.
10. Device according to any one of the foregoing Claims, applied to the control of a ventral fin (20) of a missile (14).

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