• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an artillery projectile (1) which is intended to have a trajectory comprising a ballistic phase and a piloted phase. This projectile (1) comprises at least one means ensuring its aerodynamic stabilization over all or part of its trajectory and means (9) for providing control during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing having at least two wings (16) which are positioned relative to the axis (26) of the projectile, at least during the piloted phase, with their arrows angles. negative, that is to say with the free ends (16b) of the wings (16) oriented towards the front of the proj ectile (1).
    公开号:FR3041744A1
    申请号:FR1502030
    申请日:2015-09-29
    公开日:2017-03-31
    发明作者:Christian Trouillot；Geoffroy Deschatre
    申请人:Nexter Munitions；
    IPC主号:
    专利说明:

    The technical field of the invention is that of artillery projectiles intended to have a trajectory comprising an initial ballistic phase and a piloted phase.
    Today we are looking for artillery projectiles (or shells) with an extended reach and can be controlled to control their trajectory, search and reach a particular target.
    The control means most often include duck control surfaces which are arranged at a front part of the projectile and which are controlled by geared motors (individually or by planes). The front part of the projectile incorporates an auto director and a computer to guide and control the projectile to a particular target whose signature characteristics have been stored in the calculator. A satellite positioning system can also be implemented in the projectile control chain.
    These projectiles can have a large range at lower cost thanks to the firing by an artillery gun which allows to place a 45 kg shell to more than 10km of altitude in one minute of flight.
    This type of projectile completes the range of shells that can be implemented by the same artillery system. The versatility of a weapon system responds to a recurring operational need of forces.
    In addition, the ballistic fire by a gun makes it possible to obtain a relative precision of positioning of the projectile with respect to a zone (or window of shooting) where are potential targets. At equal accuracy, artillery projectiles have a lower cost than missiles that must be controlled over their entire trajectory and must carry a propellant charge.
    One of the peculiarities of conventional artillery projectiles is that they are stabilized qyroscopically, the rotation being transmitted by the stripes of the tube during the ballistic course. This stabilization mode becomes a disadvantage for artillery projectiles comprising a ballistic phase and a driven phase because they must have a reduced rotational speed so as not to mechanically constrain the sensors and the guiding / driving electronics.
    It is thus known, for example from patent EP905473, to make an artillery shell carrying at its rear part a stabilizer stabilizer deployable.
    A rear shoe keeps the fins of the empennage folded into the tube of the weapon. He wears a slipping belt which allows to communicate to the shell only a reduced speed of rotation, of the order of a few tens of revolutions per second (the usual rotation of a 155 mm shell without a slip-on belt is 300 rpm). At the exit of the tube the shoe is ejected, either by the effect of a borrowing of the propellant gases in the tube, or by the effect of the aerodynamic flow exerted on it at the exit of the tube, the shoe can for example wear longitudinal fragilisations resulting in cutting petals at the exit of the barrel of the weapon and the ejection of the shoe.
    The projectile is thus aerostabilized in the ballistic phase.
    Stabilization in supersonic flight requires a static margin (distance between the aerodynamic focus and the center of gravity) of the order of -1 caliber. The tail empennage also provides complementary rotational braking of the projectile. It can optionally control the residual rotational speed that can be imposed by the type of onboard sensors and control algorithms.
    When the projectile reaches the peak of its trajectory (which may be more than 10 km above sea level for long range fire), it begins its descent to the area where potential targets are located. Generally piloting to the target is provided using duck rudders disposed at a front portion of the projectile, as described by patent EP0905473.
    One of the problems encountered is that stabilization which is ensured by the empennage is not optimal for the piloted flight and decreases the trajectory correction performances which are allowed by the ducks. It is the object of the invention to provide an artillery projectile architecture in which the aerodynamic stabilization ensured by the tailplane in the ballistic phase does not reduce the performance of the controlled phase piloting means.
    According to a particular embodiment, the same tilting wing can also provide aerodynamic stabilization in the ballistic phase by generating a stabilizing longitudinal moment (static margin of the order of -1 cal) and can also ensure maneuverability in the pilot phase (in generating lift with a static margin of the order of -0.25 cal). The invention thus makes it possible to decorrelate the static stability and the lift as a function of the flight regimes. The invention thus makes it possible to optimize the definition of the control module, in particular the dimensions and the choice of components such as the motors, and therefore the cost of the projectile.
    Thus, the subject of the invention is an artillery projectile intended to have a trajectory comprising a ballistic phase and a piloted, projectile phase comprising at least one means ensuring its aerodynamic stabilization over all or part of its trajectory and means intended to ensure a control during the piloted phase, projectile characterized in that the aerodynamic stabilization means comprises a wing having at least two wings which are positioned relative to the axis of the projectile, at least during the piloted phase, with their negative arrow angles , ie with the free ends of the wings oriented towards the front of the projectile.
    According to a first embodiment, the wings of the wing can be deployed during a first portion of the ballistic trajectory so as to have positive angles of deflection, maneuver means being provided for modifying the angle of deflection wings and give it negative values during a second part of the ballistic trajectory.
    Each wing can be linked to a casing relative to which it will be mounted swinging through a wing support, the wing being connected to the support by a rod having means allowing it to pivot relative to the support of wing during the tilting movement of the support relative to the housing, the wing thus passing from a folded position, in which it is positioned along the projectile with the plane of the wing applied along an outer wall of the projectile at an extended position in which the plane of the wing is oriented radially relative to the projectile, each casing being moreover pivotally mounted relative to the body of the projectile and the actuating means making it possible to pivot all the casings carrying the wings of to simultaneously change the angle of deflection of all wings.
    The maneuvering means may comprise a piston having the same axis as the projectile axis, which piston will comprise a rear face which will bear against a lower face of the housings, the piston being able to translate by the action of a motor means, the translation of the piston causing the simultaneous pivoting of all the housings.
    Advantageously, the piston may adopt a final position at the end of translation in which it will ensure a locking of all the housings in the negative angle of arrow position.
    The wing housings and the operating means may be housed in a rear base integral with the proj ectile body.
    The projectile may include a shoe surrounding the base and covering the wings in their folded position, shoe wearing a slipping belt and ejected after firing.
    Each wing may be engaged in a notch of the projectile body when it is in its final position with negative arrow angle.
    According to another embodiment of the invention, the aerodynamic stabilization means may also comprise an unfolding stabilizer which will be disposed at a rear part of the projectile, which empennage. will deploy during the ballistic phase.
    According to a particular embodiment, the empennage may be attached to the projectile by a releasable connection means, the empennage being ejected before opening the wing with negative arrow angles. The invention will be better understood on reading the following description of various embodiments, description made with reference to the accompanying drawings and in which: - Figure 1 is an external view of a projectile according to a first embodiment of the invention, projectile shown before firing; - Figure 2 is a schematic longitudinal sectional view of the projectile according to this first embodiment of the invention; FIG. 3 is an external perspective view of the projectile according to the first embodiment during its ballistic phase; FIG. 4 is an external perspective view of the projectile according to the first embodiment during its piloted phase; - Figure 5a is a partial sectional view of the rear portion of this first embodiment, projectile shown before opening the wings of the wing; - Figure 5b is a partial sectional view of the rear portion of this first embodiment, projectile shown with the wings in the position they occupy during the ballistic phase, so with the positive arrow angles; - Figure 5c is a partial sectional view of the rear portion of this first embodiment, projectile shown during the beginning of the movement of the operating means; - Figure 5d is a partial sectional view of the rear part of this first embodiment, projectile shown during a first intermediate phase of the movement of the operating means; - Figure 5e is a partial sectional view of the rear part of this first embodiment, projectile shown during a second intermediate phase of the movement of the operating means; - Figure 5f is a partial sectional view of the rear part of this first embodiment, projectile shown with the wings in the locked position they occupy during the piloted phase, so with the negative arrow angles; FIGS. 6a and 6b show a wing and its case in partial perspective and in an isolated manner, FIG. 6a showing the wing in its folded position and FIG. 6b showing the wing at the beginning of its opening movement; FIGS. 7a, 7b, 7c, 7d, 7e and 7f show a partial rear perspective of the projectile, FIG. 7a showing the wings in the folded position and FIG. 7f the wings in the ballistic position, so with the positive deflection angles, the other figures showing intermediate phases of the wing opening movement; FIG. 8 is an external view of a projectile according to a second embodiment of the invention, projectile represented before firing; FIG. 9 is an external perspective view of this projectile during its ballistic phase; FIG. 10 is an external perspective view of this projectile during its piloted phase; FIG. 11 is an external view of a projectile according to a third embodiment during its piloted phase.
    Referring to FIGS. 1 and 2, an artillery projectile 1 according to a first embodiment of the invention comprises a body 2 carrying a fuse 3 provided with target sensors 4 regularly distributed angularly (for example infrared sensors). One could also provide a single axial sensor having a sufficient field to detect and track a target. The projectile may be for example of 155 mm caliber.
    The body 2 comprises a front portion 2a and a rear portion 2b.
    The rear part 2b contains an explosive charge 8 and its priming relay 10.
    The front portion 2a contains an electronic 5 guide / control (which may include a satellite positioning device or GPS), a safety device and arming 6 for the explosive charge 8 and a control means 7 of the projectile. The control means 7 is constituted by four duck control surfaces 9 which are deployable on trajectory. The control surfaces 9 will be deployed using a mechanism (not shown) of known type, for example that described by the patent FR2949848. The deployment of the control surfaces 9 will be controlled at a given moment on trajectory by the guiding / driving electronics. Gearmotors will control the pivoting of the duck rudders (or duck control plane) after deployment to allow steering.
    The rear part 2b of the projectile is covered by a shoe 11 which is a metal or composite part comprising a tubular portion 11a closed by a bottom 11b. The shoe 11 has at its rear part a slipping belt 12 which is intended to seal the propellant when firing the projectile into an artillery tube. In a conventional manner and described in patent EP905473, the slipping belt makes it possible to communicate to the projectile only part of the rotation induced by the scratches of the barrel of the weapon. The rotational speed of the projectile at the exit of the barrel of the weapon is thus of the order of a few tens of revolutions per second (the usual rotation of a 155 mm shell without a slip belt is of the order of 300 revolutions / second).
    As seen more particularly in Figure 2, the projectile 1 carries at its rear end a rear base 13 which carries housings 14 each connected to a wing 16 and a means 15 for maneuvering these casings 14 wing.
    The projectile also carries a means of aerodynamic stabilization which according to this first embodiment is constituted by a wing comprising at least two wings 16. Here the projectile 1 comprises six wings 16 regularly distributed angularly.
    According to the ballistic phase configuration shown in Figure 2, the wings 16 are folded along the projectile 1 with the plane of each wing 16 applied along an outer wall of the projectile 1, at the rear portion 2b.
    The shoe 11 thus also covers the wings 16 during the internal ballistic phase (in the barrel of the weapon) and ensures their protection against the effect of propellant gases and the aggressions of the tube as a function of the jolt of the proj ectile.
    Figure 5a shows more accurately the rear base 13, the shoe 11 being removed. In this figure the wings 16 are in the position they occupy before opening. Each wing 16 is applied against an outer wall 17 of the projectile 1. The wall will have a plane profile or will have a profile corresponding to that of the aerodynamic profile of the wing, thus allowing to receive the wing 16.
    In this figure 5a two wings 16 are visible.
    Each wing 16 is connected to a housing 14 with respect to which it is pivotally mounted by means of a wing support 18.
    An axis 19 allows tilting of the support 18 of the wing 16 relative to the casing 14. The wing is also connected to the support 18 by a rod 20 having means enabling it to pivot relative to the wing support 18 when the tilting movement of the support 18 relative to the housing 14.
    Such an architecture allowing a pivoting of the wing around its rod 20 during the opening of the wing is described in detail by the patent EP1524488 which can be referred to for more details.
    Referring more particularly to Figures 6a and 6b, we see a wing 16 insulated and fixed to its housing 14 by the support 18. Note that the housing 14 has lateral trunnions 14a and 14b which allow pivotal mounting of the housing 14 relative to the rear base 13. These journals will be housed in bearings of the base (not shown).
    The means for pivoting the rod 20 relative to the support 18 comprise in particular a lateral arm 21 integral with the end of the rod 20 (arm visible in Figures 6a and 6b and also Figure 5b). Arm which cooperates with a cam profile 22 carried by the housing 14 (Figure 5a and 6a).
    Thus during the opening of the wing 16 by the effect of aerodynamic forces received and the offset between the point of application of the aerodynamic force and the axis of rotation 19, the support 18 tilts relative to the housing 14 on its axis 19 (the geometric axis of the axis 19 is marked in Figures 6a and 6b). During this tilting the arm 21 will be driven by the cam profile 22 and will cause the pivoting of the wing 16 relative to its support 18. The plane of the wing 16 will rotate 90 ° and position itself in the direction of aerodynamic flow (Figure 5b).
    FIGS. 7a to 7f show different stages of the pivoting of the wing 16. FIG. 7a shows (just like FIG. 5a) the different wings positioned along the outer wall 17 of the projectile.
    FIG. 7b shows the beginning of the opening of the wings 16. The pivoting of the supports 18 comes to apply the arms 21 of each wing against the cam profile 22.
    Each wing then pivots relative to its support 18 along the axis of its rod 20. Figures 7c and 7d show two stages of this pivoting of the wing.
    The figure shows the wing after its pivoting. It then has its plane in the direction of the aerodynamic flow, and the trailing edge of the wing 16 is directed facing a radial slot 24 carried by the base 13.
    When the wing 16 has pivoted, it is locked with respect to its support 18, for example by buttressing a leaf spring (not shown), perpendicular to the plane of the wing 16, and secured to the casing 14 ( such a solution is described by the patent EP1798513).
    Figures 5b and 7f show the rear part of the projectile when the wings 16 are in the position they occupy during the ballistic phase. We see that in this position the wings 16 are in abutment against a rear bearing surface 23 of the base 13. Each wing is housed in a radial slot 24 of the rear base 13. Figures 3 and 4 show the rear base 13 with its slots radial 24.
    The different casings 14 carrying the flanges 16 are also themselves pivotally mounted relative to the rear base 13 thanks to the journals 14a, 14b.
    As can be seen in FIG. 5a, the rear base 13 encloses an operating means 15 that makes it possible to rotate all the housings 14 carrying the wings 16 so as to simultaneously modify the angle of deflection of all the wings 16.
    The operating means 15 comprises a piston 25 having the same axis as the axis 26 of the projectile. This piston 25 has a rear face which bears against a lower face 14a of the housings 14. The operating means 15 also comprises a motor means 27 which can translate the piston 25 via a rod 28 (for example by a worm link).
    The piston 25 being in simultaneous contact with all the housings 14, the translation of the piston 25 causes the simultaneous pivoting of all the housings 14, therefore of all the wings 16.
    Thus, FIG. 5b shows the rear part of the projectile 1 when the wings 16 are in their deployed position with a positive arrow angle. The angle of deflection is the angle between the leading edge 16a of the wing 16 and a plane 29 perpendicular to the axis 26 of the projectile. The positive arrow angle is of the order of 60 °. Figure 3 shows the projectile 1 in this flight configuration which is the one corresponding to the ballistic phase.
    When controlling the motor means 27, the piston 25 causes the simultaneous pivoting of all the housings 14. FIG. 5c thus shows the beginning of the translational movement of the piston 25, thus the pivoting of the housings 14 and the associated wings 16.
    Figure 5d shows a first intermediate phase of the translational movement of the piston 25, phase during which the arrow angles of the wings 16 are damaged (wings 16 perpendicular to the axis 26 of the projectile.
    FIG. 5e shows a second intermediate phase of the translational movement of the piston 25. This phase corresponds to a positioning of the flanges 16 with an arrow angle β which is negative, that is to say with the free ends 16b (see FIG. 4) wings 16 all oriented towards the front of the projectile 1.
    Each wing 16 is then engaged in a notch 30 of the projectile body 1. The notches 30 allow to block the root of each wing 16. The value of the arrow β is of the order of -30 °.
    FIG. 5f finally shows the final position of the piston 25. The arrow of the wings 16 has not been modified between FIG. 5e and FIG. 5f, but the piston 25 has continued its travel and is in a final position at the end of translation. in which it ensures a locking of all the housings 14 in the position at negative arrow angle β.
    To ensure this locking the cylindrical peripheral edge of the piston 25 cooperates with the lower face 14a of each housing 14. The piston 25 is in the final position disposed at a distance D from the pivot axis of each housing 14 and prohibits any return of wings in a positive arrow position.
    The rigidity of the final position is ensured, each fin being engaged in a notch 30 and blocked by the piston 25.
    The operation of the projectile according to the invention is as follows.
    When firing the projectile, the slipping belt 12 makes it possible to limit the rotational speed of the projectile to a few tens of revolutions per second (whereas the rotational speed of a projectile of 155 mm is more than 300 revolutions per second for long range shots).
    The shoe 11 which ensures both the speed of the projectile 1 and the tightness of the propellant gas separates from the projectile 1 naturally at the exit of the tube of the weapon, by the action of aerodynamic forces. Alternatively, a separation aid could be achieved for example by a borrowing propellant or a spring mechanism placed between the base 13 and the shoe 11. The patent EP905473 describes such separation modes by borrowing gas.
    Once the shoe 11 ejected, the wings 16 unfold naturally under the action of the centrifugation of the wings and the dynamics of the projectile at the exit of the tube.
    When each wing 16 is raised against the flow by an aerodynamic effect, it pivots immediately relative to its casing 14 with its wing support 18 limiting the tilting speed of the wing and therefore the shock at the end of opening . A heavy wing limits the intensity of the shock by inertia effect. The mechanism formed by the rod 20 and its arm 21 cooperating with the profiles 22 provided on the housing 14 causes the pivoting of the wing 16 and its positioning in the wind bed, plane of the radial flange 16 relative to the projectile and passing through the axis 26 of the proj ectile.
    The wings all adopt the position shown in Figures 3 and 5b, in which position they are in rear abutment against the rear surfaces 23 of the radial slots 24. Each wing 16 is also locked relative to its housing 14 by a locking device suitable, for example that described by EP1798513 (blocking by buttressing a leaf spring). The positive angle of deflection of about 60 ° minimizes the drag in supersonic flight while ensuring a sufficient static margin (of the order of -1 caliber), thus guaranteeing the stability of the projectile at the exit of tube, during the most critical phase of flight (supersonic flight at high Mach). As the speed decreases, the static margin increases.
    Once the wings 16 deployed, the projectile 1 is in its phase of ballistic flight. It can climb to over 10000m altitude at high propulsive loads with minimal aerodynamic drag configuration. The wings 16 also reduce the rotational speed of the projectile 1. At the end of a duration which will be programmed for example at a computer of the guide electronics 5, or programmed in a specific electronic module housed in the base, the operating means 15 is controlled to modify the angle of deflection of the wings 16. This control preferably occurs at the apogee of the trajectory at the moment when the projectile begins its descent to reach the largest ranges.
    The maneuvering means 15 makes it possible to tilt the wings 16 toward the front of the projectile 1. The angular amplitude of the tilting is of the order of 90 ° (passage of the wings from + 60 ° to -30 °).
    The motor means 27 of the operating means 15 may be electric or pyrotechnic (retractor, latch, jack ...). The switchover can be done in a few seconds knowing that the stability of the projectile during this transitional phase will always be assured (subsonic flight).
    In addition, the energy required for this maneuver is reduced because of the low density of the air and the minimal drag of the wings.
    When the wings 16 have their free end 16b oriented towards the front of the projectile (negative angle of deflection), the duck control surfaces 9 are also deployed and operational (FIG. 4). The modification of the angle of the wings 16 has been controlled near the apogee of the trajectory of the projectile 1.
    Due to the negative deflection of the wings, the aerodynamic stability of the projectile 1 is reduced (static margin less than -0.5 gauge.
    The optimal value to choose for the static margin depends on the performance of the flight deck and the objectives of the flight.
    It is possible with the invention to adjust the static margin to the profile of the proposed mission. For a very long-range shot, end-stage maneuverability will be preferred. For a short-range shot it will be possible to maintain the wings in ballistic position (positive arrow position), and not to control their passage in the forward position (negative arrow). Maneuverability will then be reduced with a projectile that is very statically stable, but this may be acceptable for short-range shooting.
    The static margin in the negative arrow position is chosen just enough to ensure aerostabilization of the projectile, whether the ducks 9 are deployed or not.
    The control duck 9 will control the projectile by changing its incidence. The wings 16 negative arrow provide high lift and allow strong maneuverability through their good aerodynamic lift characteristics.
    The projectile according to the invention thus makes it possible at the same time to ensure the stability in supersonic ballistic flight and the strong maneuvering capacities in terminal piloting phase in subsonic regime.
    Figures 8 to 10 show a projectile according to a second embodiment of the invention.
    This embodiment is shown here very schematically.
    As in the previous mode, the projectile 1 comprises a body 2 carrying a fuse 3 provided with target sensors 4 regularly distributed angularly (for example infrared sensors), or comprising a single axial sensor having a field sufficient to detect and continue a target. The guidance / control electronics may also include a satellite positioning device or GPS. The body 2 comprises a front portion 2a and a rear portion 2b.
    The rear part 2b contains an explosive charge and its priming relay (not visible in the figures) and the front part 2a contains a guiding / driving electronics, a security and arming device for the explosive charge and a means of piloting 7 of the projectile.
    The control means 7 is constituted by four duck control surfaces 9 which are deployable on trajectory.
    The rear part 2b of the projectile is partially covered by a shoe 11 which is a metal or composite part comprising a tubular portion 11a closed by a bottom 11b. The shoe 11 has at its rear part a slipping belt 12 which is intended to seal the propellant when firing the projectile into an artillery tube.
    This projectile 1 differs from that described above in that the aerodynamic stabilization means comprises: - on the one hand a wing formed of wings 16 which are during the ballistic phase in the folded position arranged with the plane of each wing 16 applied along an outer wall of the projectile 1, at the rear portion 2b; - On the other hand a deploying tail 31 which is disposed at a base 34 integral with the rear part 2b of the projectile, behind the wing 16. The empennage 31 is constituted by fins 32 constituted by plates steel which are for example recessed or hinged to their root on the base 34 and lockable in the deployed position. These fins 32 are initially wound elastically on a cylindrical portion 33 of the cap 34 and held in position by the shoe 11.
    The shoe 11 may be ejected after firing, either by the effect of a borrowing of the propellant gases in the tube, or by the effect of the aerodynamic flow exerted on it at the exit of the tube. The shoe may for example wear longitudinal embrittlement resulting in cutting petals at the exit of the barrel of the weapon and the ejection of the shoe. The ejection of the shoe 11 at the exit of the barrel of the weapon causes the deployment of the fins 32 which ensure the stabilization of the projectile throughout its ballistic phase and its rotational braking.
    Unlike the previous embodiment, during this ballistic phase the wings 16 of the wing remain in the folded position (Figure 9).
    The wings 16 are held in the folded position, for example by locks 35 which are integral with the body 2 of the projectile and which engage in holes in the ends of the wings 16.
    Moreover, the base 34 is secured to the rear part 2b of the projectile body by a pyrotechnic bolt 36.
    In the vicinity of the apogee of the trajectory, at the end of a duration which will for example be programmed at a computer of the guiding electronics, the pyrotechnic bolt 36 is controlled to cause separation of the cap 34 and body 2 of the projectile. In addition, the latches 35 which release the wings 16 are controlled.
    Each wing 16 is connected to the body 2 of the projectile by a connection of the type described above with reference to Figure 5a and which is also described by the patent EP1524488.
    This link is not drawn in detail. It comprises as previously described a housing secured to the body 2 and relative to which pivots a wing support receiving a rod integral with the wing, which can itself rotate relative to the support and carrying a lateral arm cooperating with a cam profile of the case.
    This connection allows a pivoting of the wing around its rod during the opening of the wing, which allows the passage of a position where the plane of the wing is in abutment against the projectile body (Figure 9 ) at a position in which the plane of the wing 16 has rotated 90 ° and is positioned in the direction of the aerodynamic flow (Figure 10), the wing 16 having its leading edge 16a in the flow aerodynamic.
    The cam profiles of the casing will be dimensioned by the skilled person to ensure a pivoting of the wing with a final position as shown in Figure 10, with a negative deflection angle β, ie with the free ends 16b of the wings oriented towards the front of the projectile. A backgauge will be positioned to maintain the wings with this negative arrow.
    At the same time the duck control surfaces 9 are deployed and operational.
    Due to the negative deflection of the wings 16, the aerodynamic stability of the projectile 1 is reduced (static margin less than -0.5 gauge). This margin is chosen just enough to ensure the aerostabilization of the projectile that the ducks 9 are raised or not.
    This embodiment makes it possible to eliminate the transition phase of the wings 16 from a positive arrow to a negative arrow.
    The means ensuring the stabilization in the ballistic phase and piloted phase are then distinct and the deployment movement of the wings 16 is also smaller in amplitude.
    Various variants of this mode are possible.
    For example, the fins 32 may be bonded to the base 34 by longitudinal grooves which will open at the rear of the base. Each fin 32 will then be designed to slide axially in its groove.
    A stop will be provided at the rear portion of the cap 34. The deletion of the stop will allow the axial ejection of the fins 32 by sliding in their groove under the effect of the aerodynamic resistance.
    This ejection fins can then intervene without the need to eject all the cap 34. Such a variant allows to keep substantially the same length to the projectile 1 during the ballistic and piloted phases. As a variant, it will be possible to implement, in this latter embodiment, wings 16 whose plane remains positioned radially to the projectile and which each pivot about an axis perpendicular to the axis 26 of the projectile. This embodiment, however, requires having radial grooves in the body 2 of the projectile 1 and wings 16 which are then intrusive in the body 2. The carrying capacity of the projectile explosive will be reduced.
    FIG. 11 shows another embodiment of the projectile according to the invention which differs from the preceding one only in that the empennage 31 is not ejected in the vicinity of the apogee of the trajectory.
    FIG. 11 shows the projectile during its piloted flight phase. The duck control surfaces 9 are deployed as well as the wings 16 which have a negative arrow. The rear fins 32 are always constituted by steel plates recessed or hinged on the base 34. They remain attached to the projectile during this pilot phase. This embodiment increases somewhat the aerodynamic drag of the projectile but may be satisfactory in some configurations.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    An artillery projectile (1) intended to have a trajectory comprising a ballistic phase and a piloted phase, a projectile comprising at least one means ensuring its aerodynamic stabilization over all or part of its trajectory and means for ensuring steering during the piloted, projectile phase characterized in that the aerodynamic stabilization means comprises a wing having at least two wings (16) which are positioned relative to the axis (26) of the projectile, at least during the piloted phase, with their angles arrows (β) negative, that is to say with the free ends (16b) of the wings (16) facing the front of the projectile (1).
    [2" id="c-fr-0002]
    2- artillery projectile according to claim 1, characterized in that the wings (16) of the wing are deployed during a first portion of the ballistic trajectory so as to have positive arrow angles (a), a means for maneuvering (15) being provided which makes it possible to modify the angle of deflection of the wings (16) and to give it negative values during a second part of the ballistic trajectory.
    [3" id="c-fr-0003]
    3- artillery projectile according to claim 2, characterized in that each wing (16) is connected to a housing (14) relative to which it is pivotally mounted by means of a support (18) wing, the wing being connected to the support (18) by a rod (20) having means (21) allowing it to pivot relative to the wing support (18) during the tilting movement of the support (18) relative to the housing (14), the wing (16) thus passing from a folded position, in which it is positioned along the projectile (1) with the plane of the wing applied along an outer wall (17) of the projectile at an extended position in which the plane of the wing (16) is oriented radially relative to the projectile, each casing (14) being moreover pivotally mounted relative to the body of the projectile (1) and the maneuvering means (15). ) for rotating all the housings (14) carrying the wings (16) so as to simultaneously change the angle of èche of all the wings.
    [4" id="c-fr-0004]
    4- artillery projectile according to claim 3, characterized in that the operating means (15) comprises a piston (25) having the same axis as the axis (26) of the projectile piston having a rear face which is in bearing against a lower face (14a) of the housings (14), the piston (25) being translatable by the action of a motor means (27), the translation of the piston (25) causing the simultaneous pivoting of all the housings (14).
    [5" id="c-fr-0005]
    5- artillery projectile according to claim 4, characterized in that the piston (25) adopts a final position at the end of translation in which it ensures a locking of all the housings (14) in the negative arrow angle position.
    [6" id="c-fr-0006]
    6- Artillery projectile according to one of claims 2 to 5, characterized in that the casings (14) of wings and the operating means (15) are housed in a rear base (13) integral with the projectile body.
    [7" id="c-fr-0007]
    7- artillery projectile according to claim 6, characterized in that it comprises a shoe (11) surrounding the base (13) and covering the wings (16) in their folded position, shoe (11) carrying a slipping belt ( 12) and ejected after firing.
    [8" id="c-fr-0008]
    8- Artillery projectile according to one of claims 2 to 7, characterized in that each wing (16) is engaged in a notch (30) of the projectile body when it is in its final position at negative arrow angle .
    [9" id="c-fr-0009]
    9- artillery projectile according to claim 1, characterized in that the aerodynamic stabilization means also comprises an unfolding tail (31) which is disposed at a rear portion of the projectile, empennage which unfolds during the phase ballistic.
    [10" id="c-fr-0010]
    10- artillery projectile according to claim 9, characterized in that the empennage (31) is fixed to the projectile by a releasable connection means (36), the empennage being ejected before opening the blade (16) at angles negative arrows.
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    同族专利:
    公开号 | 公开日
    US20170299355A1|2017-10-19|
    ES2689074T3|2018-11-08|
    US10401134B2|2019-09-03|
    FR3041744B1|2018-08-17|
    EP3150957B1|2018-08-01|
    US10788297B2|2020-09-29|
    EP3150957A1|2017-04-05|
    PL3150957T3|2018-12-31|
    DK3150957T3|2018-11-05|
    TR201816346T4|2018-11-21|
    US20190368846A1|2019-12-05|
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    US10345087B2|2017-08-01|2019-07-09|BAE Systems Informaticn and Electronic Systems Integration Inc.|Mid body seeker payload|
    FR3080912B1|2018-05-02|2020-04-03|Nexter Munitions|PROJECTILE POWERED BY STATOREACTOR|
    US10996037B2|2018-09-04|2021-05-04|The United States Of America As Represented By The Secretary Of The Army|Obturator for robust and uniform discard|
    US11255648B2|2018-11-08|2022-02-22|Mbda Incorporated|Projectile with a range extending wing assembly|
    US11187505B1|2019-07-03|2021-11-30|Gerhard W. Thielman|Concatenated annular swing-wing tandem lift enhancer|
    法律状态:
    2016-07-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-03-31| PLSC| Search report ready|Effective date: 20170331 |
    2017-08-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-16| ST| Notification of lapse|Effective date: 20200906 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1502030|2015-09-29|
    FR1502030A|FR3041744B1|2015-09-29|2015-09-29|ARTILLERY PROJECTILE HAVING A PILOTED PHASE.|FR1502030A| FR3041744B1|2015-09-29|2015-09-29|ARTILLERY PROJECTILE HAVING A PILOTED PHASE.|
    PL16190582T| PL3150957T3|2015-09-29|2016-09-26|Artillery projectile having a piloted phase|
    TR2018/16346T| TR201816346T4|2015-09-29|2016-09-26|Heavy weapon projectile with managed phase.|
    DK16190582.3T| DK3150957T3|2015-09-29|2016-09-26|Artillery projectile with a controlled phase|
    EP16190582.3A| EP3150957B1|2015-09-29|2016-09-26|Artillery projectile having a piloted phase|
    ES16190582.3T| ES2689074T3|2015-09-29|2016-09-26|Artillery projectile with a piloted phase|
    US15/278,653| US10401134B2|2015-09-29|2016-09-28|Artillery projectile with a piloted phase|
    US16/516,302| US10788297B2|2015-09-29|2019-07-19|Artillery projectile with a piloted phase|
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