EP3667225B1 - Projectile with deployable wing plans - Google Patents

Description

The technical field of the invention is that of projectiles comprising deployable sail plans.

It has long been known to equip projectiles with sail plans to increase their range, we will then speak of fins, or to be able to direct them, we will then speak of control surfaces.

Such sail plans when folded are arranged in housings located in the body of the projectile. A projectile of this type is described in the patent FR2952712 .

Once the planes have been deployed, it is necessary to optimize the flow of air along the projectile so as not to disrupt or degrade its aerodynamic behavior. The patent FR2952712 proposes to equip the projectile with hatches at the level of each housing opening housing a plane and opening towards the outside and to slide them in a first direction to allow the deployment of the plane outside the body then to slide the hatch again in the direction reverse to close the housing again, which poses the problem of requiring as many motors as there are hatches and of having to control them in different directions of rotation.

We also know from the patent US3853288 a projectile with deployable fins comprising a pivoting envelope which surrounds the body and has as many openings as there are fins. Each fin has an extra thickness at its pivot which is defined such that, once deployed, the assembly formed by the fin and the extra thickness of its pivot closes completely. the opening. Such a solution is difficult to implement since the dimensions, both of the fin and its extra thickness and of the opening, must be perfectly controlled. Furthermore, the assured closure remains imperfect since the fin and its bulge can only close the width of the slot in the envelope and not its entire length. Finally, this solution can only be implemented for stabilization fins which no longer move after deployment. It is unsuitable for control surfaces which have a sail plan that pivots relative to an axis perpendicular to the axis of the projectile.

The invention proposes a solution making it possible to simplify the process of opening and closing the housings of the sail plans and in particular rudder-type sail plans.

The solution proposed by the invention is independent of the fin itself and it can therefore be adapted to pivoting fins after deployment, such as control surfaces.

The invention relates to a projectile comprising at least one pair of sail planes, deployable from housings located inside the body and opening towards the outside of the projectile, projectile comprising an envelope of revolution surrounding at least one part of the body of the projectile and whose external surface is in profile continuity with the body of the projectile, envelope capable of pivoting thanks to a motor means around the body along the longitudinal axis thereof and comprising for each plane an opening, projectile characterized in that the opening comprises two zones, a first zone intended to be positioned by the pivoting of the envelope opposite a housing so as to let the plane pass to allow it to deploy, and a second zone forming a lateral clearance relative to the first zone, clearance oriented in a direction substantially perpendicular to the longitudinal direction of the first zone, second zone having a width allowing the passage of a foot of the sail plan once deployed, the envelope covering the housing by continuing its pivoting to prevent the plan from folding.

Advantageously, according to one embodiment, each sail plan deploys by pivoting around an axis of rotation perpendicular to the pivot axis of the envelope.

Each second zone of the opening is then located at one end of the first zone.

According to another embodiment, each sail plan deploys by radial translation.

For each opening the second zone of the opening is then located in an intermediate zone between the ends of the first zone.

• Fig. 1a représente une vue schématique partielle d'une partie de projectile selon un premier mode de réalisation de l'invention lors d'une première phase de déploiement.
• Fig. 1b représente une vue schématique partielle d'une partie de projectile selon ce premier mode de réalisation lors d'une seconde phase de déploiement.
• Fig. 1c représente une vue schématique partielle d'une partie de projectile selon ce premier mode de réalisation lors d'une troisième phase de déploiement.
• Fig. 2 représente une vue en coupe transversale selon le plan P de la figure 1a d'un projectile selon ce premier mode de réalisation avec les plans en position rentrée.
• Fig. 3 représente une vue partielle en coupe transversale d'un projectile selon ce premier mode de réalisation avec un plan en position sortie.
• Fig. 4 représente une vue partielle en coupe transversale d'un projectile selon ce premier mode de réalisation avec un plan en position sortie et verrouillé.
• Fig. 5a représente une vue schématique partielle d'une partie de projectile selon un second mode de réalisation de l'invention lors d'une première phase de déploiement.
• Fig. 5b représente une vue schématique partielle d'une partie de projectile selon ce second mode de réalisation lors d'une seconde phase de déploiement.
• Fig. 5c représente une vue schématique partielle d'une partie de projectile selon ce second mode de réalisation lors d'une troisième phase de déploiement.

The invention will be better understood on reading the following description, description made with reference to the appended drawings, drawings in which:

• Fig. 1a represents a partial schematic view of a projectile part according to a first embodiment of the invention during a first deployment phase.
• Fig. 1b represents a partial schematic view of a projectile part according to this first embodiment during a second deployment phase.
• Fig. 1 C represents a partial schematic view of a projectile part according to this first embodiment during a third deployment phase.
• Fig. 2 represents a cross-sectional view along the plane P of the figure 1a of a projectile according to this first embodiment with the planes in the retracted position.
• Fig. 3 represents a partial cross-sectional view of a projectile according to this first embodiment with a plane in the extended position.
• Fig. 4 represents a partial cross-sectional view of a projectile according to this first embodiment with a plane in the extended and locked position.
• Fig. 5a represents a partial schematic view of a projectile part according to a second embodiment of the invention during a first deployment phase.
• Fig. 5b represents a partial schematic view of a projectile part according to this second embodiment during a second deployment phase.
• Fig. 5c represents a partial schematic view of a projectile part according to this second embodiment during a third deployment phase.

According to figure 1a a projectile 100 comprises an envelope 1 surrounding a part of a body 2 of the projectile 100 and adopting a form of revolution centered on the longitudinal axis can pivot on bearings (not shown) arranged on the body 2. The envelope 1 is placed such that its external surface is located in continuity with the external profile of the projectile 100 so as not to disturb the aerodynamic flow in flight .

According to figure 2 , the projectile 100 comprises housings 4 made in the body 2 and distributed angularly equally.

Each housing houses a sail plan 5 and it opens towards the outside of the projectile body 2.

In this storage position, which corresponds to a position where the planes 5 are contained in the housings 4, the envelope 1 is located opposite the housings 4 and prevents the planes 5 from unfolding. The planes 5 are pushed to unfold under the action of an elastic means not shown and conventionally known to those skilled in the art such as a spring.

In this position the projectile 100 can be fired, in a cannon for example, since the planes 5 are not exposed to the outside of the projectile 100. Always at the figure 2 we note that the envelope 1 includes openings 6 in number equal to that of the housings 4 and the planes 5 and which are distributed angularly identical to the angular distribution of the housings 4.

As visible to figures 1a to 1c , each opening 6 of the envelope 1 comprises two zones Z1 and Z2 each communicating with one another.

A first zone Z1 has a shape substantially corresponding to the shape of the housing 4 at the level where it opens to the outside of the body 2. A second zone Z2 forms a lateral clearance to the first zone Z1, clearance oriented in a direction substantially perpendicular to the longitudinal direction of the first zone Z1. As seen in the figures, the width L of the second zone Z2 is much less than the total length of the first zone Z1. This width L corresponds to the diameter of the foot 5a of the sail plan 5 (which here is a rudder that can pivot to control the projectile).

According to a second phase of operation of the projectile 100 visible to figure 1b And 3 corresponding to the deployment of the planes 5, the envelope 1 pivoted angularly until that, for each opening 6, each first zone 21 is positioned opposite a housing 4. Each plane 5 is no longer retained against the action of the spring by the internal wall of the envelope 1. They can then be deploy outside the projectile 100 by rotation around an axis 8 secured to a foot 5a of the sail plane 5. The axis of rotation 8 is perpendicular to the longitudinal axis X of the projectile 100.

The deployment of each plane 5 takes place up to a nominal position substantially perpendicular radially to the longitudinal axis figure 1b that the communication of the second zone Z2 and the first zone 21 takes place at one end of the first zone 21 which is opposite the foot 5a of the unfolded sail plan 5. The second zone Z2 thus has a width L adapted to the passage of this foot 5a of plane 5.

Thus, according to the figures 1b And 3 , when the envelope 1 continues its pivoting movement around the longitudinal axis X of the projectile 100, the foot 5a of plane 5 is positioned in the second zone Z2.

The pivoting of the envelope 1 continues and at the end of the pivoting of the envelope 1, according to the figures 1c And 4 , the envelope 1 covers the housing 4 and any subsequent folding of the plane 5 towards its housing 4 is prohibited by interference of the plane 5 with the envelope 1. The plane 5 is thus locked in the extended position.

Note that advantageously the housings 4 are closed by the envelope 1 which does not disrupt the flow of air along the projectile. In addition, the entire locking deployment sequence is done with a rotational movement of the envelope in a single angular direction, which simplifies the control which requires only one motor means to open all the housings 4, to release all the planes 5 and to then close all the housings 4. The pivoting of the foot 5a of the sail plane 5 is authorized by the envelope 1. In fact the second zone Z2 surrounds the foot 5a of plane 5 with sufficient functional clearance to authorize such pivoting. The housings 4, however, remain closed by the envelope 1 during the pivoting of the plane 5 of the wing.

THE figures 5a to 5c show a second embodiment of the invention.

In this mode the sail planes 5 (which are also control surfaces) are deployed by a radial translation of each plane 5 in its housing 4.

The operating sequence is identical to that of the first embodiment. A single rotation of envelope 1 will open housings 4, release planes 5 then close housings 4 by locking planes 5.

Those skilled in the art will only ensure that the second zone Z2 is correctly positioned in relation to the foot 5a of the plane 5 so that this second zone Z2 is in front of the foot 5a once the plane 5 is deployed. The second zone Z2 of the opening will thus be located in an intermediate zone between the ends of the first zone Z1.

As an example, it will be noted that on the figures 5a to 5c the foot 5a of the plane 5 is located substantially in the middle of the base of the plane 5. The second zone Z2 is then also positioned substantially in the middle of the first zone 21 considering the longitudinal direction of the opening 6.

Claims (5)

1. - A projectile (100) including at least one pair of airfoil sections (5) that are deployable from housings (4) that are located inside the body (2) and are emerging toward the outside of the projectile (100), the projectile (100) including a casing (1) of revolution surrounding at least part of the body (2) of the projectile and the outer surface of which is in profile continuity with the body (2) of the projectile, the casing (1) being able to pivot, owing to a motor means, around the body (2) along the longitudinal axis (X) thereof and including an opening (6) for each airfoil section (5), the projectile being characterised in that each opening (6) includes two zones (Z1,Z2), namely a first zone (Z1) being intended to be positioned, by pivoting of the casing (1), so as to face a housing (4) in order to allow the section (5) to pass so as to allow it to be deployed, and a second zone (Z2) forming a lateral recess relative to the first zone (Z1), the recess being oriented along a direction substantially perpendicular to the longitudinal direction of the first zone (Z1), the second zone (Z2) having a width (L) allowing passage of a foot (5a) of the airfoil section (5) once deployed, the casing (1) covering the housing (4) by continuation of its pivoting so as to prevent folding of the airfoil section (5).
2. - The projectile (100) according to claim 1, characterised in that each airfoil section (5) is deployed by pivoting around a rotation axis (8) perpendicular to the pivoting axis (X) of the casing.
3. - The projectile (100) according to claim 2, characterised in that for each opening (6), the second zone (Z2) of the opening (6) is located at one end of the first zone (Z1).
4. - The projectile (100) according to claim 1, characterised in that each airfoil section (5) is deployed by radial translation.
5. - The projectile (100) according to claim 4, characterised in that for each opening (6), the second zone (Z2) of the opening (6) is located in an intermediate zone between the ends of the first zone (Z1).

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