• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    The present invention relates to a projectile comprising a body having a longitudinal axis and an intermediate portion comprising a device for deploying wings or fins comprising at least a number N, at least equal to three, wing or fins capable of being deployed, the process deployment system comprising at least two phases, a first deployment phase where each wing or wing passes from a tangential position to the body of the projectile and parallel to the longitudinal axis to a semi-deployed position, and a second deployment phase with the passing each wing from the semi-deployed position to an extended position where it is perpendicular to the body of the projectile, said wing deployment device is configured to synchronize the deployment of wings or fins in the second phase.
    公开号:FR3054030A1
    申请号:FR1601109
    申请日:2016-07-18
    公开日:2018-01-19
    发明作者:Sylvain PINOTEAU
    申请人:Nexter Munitions；
    IPC主号:
    专利说明:

    TECHNICAL FIELD OF THE INVENTION
    The present invention relates to the field of exterior ballistics and more particularly to the stabilization of projectiles moving in space. More specifically, the invention relates to a projectile and its associated deployment device for wings or fins.
    TECHNOLOGICAL BACKGROUND OF THE INVENTION
    When firing a projectile, several parameters must be taken into account so that said projectile can reach a designated target. During the flight phase, the projectile is subjected to aerodynamic forces which can cause it to deviate from its trajectory. One of the important parameters is therefore the stabilization of said projectile.
    Several projectiles, for this purpose, are provided with mechanisms or devices for deploying wings or fins for their stabilization. The association of such a mechanism or device with the projectile must not, however, lead to a significant variation in the dimensions of the architecture of the projectile, at the risk of either aggravating aerodynamic disturbances or preventing the addition of on-board electronic devices. to improve, for example, the performance of the projectile.
    Document US 6761331 teaches a missile and a deployment mechanism for fins, the arrangement of which does not reduce the useful volume of the projectile, said deployment mechanism automatically pivots by rotating a wing from a stowed orientation to a deployed orientation . The deployment mechanism includes a spring that provides a pushing force allowing the fin to move quickly, simply and reliably from the stowed orientation to the deployed orientation. The deployment mechanism, which is carried out in three stages, also includes one or more cams or the like for guiding the fin from the stowed orientation to the deployed orientation. This mechanism therefore takes up space and its complexity can cause malfunctions or incomplete deployments.
    The document EP0318359 teaches a projectile with which is associated a device for deploying a fin made integral with the projectile by a joint located at the rear of the body of the projectile, said joint being such that the deployment movement takes place in two phases: a first phase in which the fin passes from a carrying position to a semi-deployed position, by rotation in the direction of flow and along a first axis perpendicular to the plane of the fin when the latter is in carrying position then a second phase in which the fin passes from the semi-deployed position to the deployed position, by a rotation along a second axis which is parallel to the plane of the fin. The articulation includes a motor playing the role of actuator of the first deployment phase and locking of the fin assembly, articulation when the fin is in the carrying position.
    The documents cited above have, however, drawbacks which may affect the good stabilization provided by the fins. Indeed, the second deployment phase of the fins depends on the inclination of the projectile, relative to the direction of the aerodynamic flow, in the flight phase. The aerodynamic stresses exerted on a fin depend on the surface that the latter presents opposite the aerodynamic flow. Thus, if during the second deployment phase the projectile is inclined, the fins being each subjected to different aerodynamic forces, it is not certain that the fins are deployed correctly, thereby rendering the mechanisms or devices unreliable. deployment taught in the above documents.
    Document US 6761331 also teaches fins which, during the deployment phase, have a greater surface area facing the aerodynamic flow, which can induce additional constraints for good stabilization of the projectile.
    GENERAL DESCRIPTION OF THE INVENTION
    The present invention aims to overcome one or more drawbacks of the prior art by proposing a projectile architecture comprising an effective and reliable device for deploying wings or fins whatever the trajectory of said projectile.
    This objective is achieved by a projectile comprising a body having a longitudinal axis and an intermediate portion comprising a device for deploying wings or fins comprising a number N, equal to at least three, of wings or fins capable of being deployed, the process of deployment comprising at least two phases, a first deployment phase in which each wing or wing passes from a position tangential to the body of the projectile and parallel to the longitudinal axis to a semi-deployed position, by rotation of the wing or the wing around from an axis perpendicular to the longitudinal axis of the projectile and a second deployment phase with the passage of each wing or fin from the semi-deployed position, in which it is still tangent to the body of the projectile, in a deployed position where it is perpendicular to the body of the projectile, by rotation about an axis parallel to the longitudinal axis of the projectile , said projectile being characterized in that the device for deploying the blades or fins is configured so that the rotation of a blade or a blade about the axis parallel to the longitudinal axis of the projectile causes toothing which meshes with a synchronization toothed wheel which engages by rotation the rotation of each other wing or fin around each axis parallel to the longitudinal axis of the projectile to synchronize the deployment of the wings or fins in the second phase.
    According to another particularity, the airfoils or fins are arranged in the middle position on the body of the projectile in order to improve the flight characteristics of the projectile.
    According to another particularity, in the first deployment phase, the projectile wings or fins deploy from rear to front, in opposite direction to the aerodynamic flow, the pivot axis being mounted upstream of the wing or of the fin, in the direction of the aerodynamic flow when the airfoil or the fin is in position tangential to the body of the projectile.
    According to another particular feature, the first phase of deployment of all the wings or fins is provided by a single control and lock motor indirectly connected to an expansion system comprising a pressure piston and at least one compression spring, allowing thus lightening the mechanism in the projectile while ensuring good stabilization.
    According to another particularity, the pressure piston makes it possible to initiate the rotational movement of the airfoils in the first deployment phase and includes guide means making it possible to guide said piston during its translational movement, indirectly generated by the control motor. and bolt, along the longitudinal axis of the projectile.
    According to another particular feature, the device comprises a body comprising on its external part at least one housing for receiving at least one synchronization means and part of the wing or the fin, a central chamber in which the pressure piston is arranged. and at least one orientation means and at least one means for synchronizing the airfoils or fins, the central chamber being between a chamber upstream with respect to the direction of the aerodynamic flow and called the upper in which the motor controlling the deployment and locking of the airfoils and a chamber downstream relative to the direction of the aerodynamic and so-called lower flow, the central chamber and the upper chamber being separated by an upper wall, and the central chamber and the lower chamber by a lower wall .
    According to another particularity, the central chamber of the body of the deployment device also comprises at least one main column, centered on the axis of the projectile and integral with at least one of the lower or upper walls, around which is wound a large central compression spring, at least the same number N of secondary columns located at the periphery around the main column and around which small compression springs are also wound, a lock disc comprising at least the same number N of studs and at at least one activation toothed wheel actuated by the control motor, the activation toothed wheel being linked to the lock disc so as to transmit the rotational movement thereto to allow the unlocking of the airfoils or fins.
    According to another particular feature, the guide means comprise at least one guide disc fixed to the rear of the piston body and at least the same number N of guide rings.
    According to another particularity, the pressure piston also comprises at least the same number N of grooves and coming to face the tenons of the lock disc when the latter pivots, the grooves being capable of receiving said tenons, at least the same number N of stops on which rods are fixed, each rod having at its end a guide ring configured to receive a secondary column so that the small spring is located between an internal portion of the body in the vicinity of the bottom wall and l ring, and at least one axial cavity centered on the axis of the projectile and configured to receive the main column and part of the large central compression spring.
    According to another particularity, the orientation means comprise at least the same number N of split cleats, each cleat comprising a groove capable of receiving a rod secured to a wing or fin comprising a tenon at its end, and at least the same number N of cams, each cam being integral with a cleat.
    According to another particular feature, the means for synchronizing the deployment of the airfoils comprise at least the synchronization toothed wheel disposed in a circular groove coaxial with the central chamber, and at least the same number N of pivots equal to the number of airfoils, each pivot being included in the housing of the external part of the body of the device and comprising a cavity capable of receiving the rod of an airfoil, and a pinion mounted at one of its ends, said pinion coming to mesh on the synchronization toothed wheel .
    According to another particularity, the device comprises at least one fixing means making it possible to prevent the continuous rotation of at least one wing or fin around the axis of rotation of the first deployment phase once the second deployment phase engaged.
    According to another particularity, the pivot is held in the housing of the external surface of the body of the deployment device by a front flange located at the front end of the pivot in the direction of the upper wall and by a rear flange located at the end rear of the pivot comprising at least one pinion and in the direction of the lower wall, the flanges being provided with grooves of cylindrical profile covering the pivot and guiding the rotational movement of said pivot.
    According to another particular feature, the housing included in the external surface of the body of the deployment device comprises a profile forming a secondary V-shaped housing, configured to receive a part of the airfoil or fin at the end of the deployed phase, said deployed phase consisting in positioning part of the airfoil in said secondary housing.
    DESCRIPTION OF ILLUSTRATIVE FIGURES
    Other particularities and advantages of the present invention will appear more clearly on reading the description below, made with reference to the appended drawings, in which:
    - Figure 1 shows a perspective view of the projectile, according to one embodiment;
    - Figures 2A; 2B and 2C represent a perspective view, respectively of the deployment device before the first deployment phase, after the first deployment phase and after the second deployment phase, according to one embodiment;
    - Figure 3A; 3B, 3C and 3D show a perspective view, according to one embodiment, of the control motor respectively coupled indirectly to the pressure piston by the activation toothed wheel and the lock disc, of a section of the body of the device. empty deployment of its elements, of a section of the body of the deployment device with the pressure piston and the compression springs before and after the first deployment phase;
    - Figures 4A and 4B; represent a perspective view of the pressure piston, according to one embodiment;
    - Figures 5A and 5D; represent a perspective view of a section of the deployment device, the airfoils or fins in the semi-deployed position according to one embodiment, FIGS. 5B and 5E represent a perspective view of the deployment device, the airfoils or fins in the deployed position, according to one embodiment and FIG. 5C represents a perspective view of the section of the deployment device before the first deployment phase, according to one embodiment;
    - Figures 6A and 6B show a top view, according to one embodiment, of the part of the deployment device comprising the pivot axis of the airfoil or the fin, respectively in the semi-deployed position and in the deployed position;
    DESCRIPTION OF THE PREFERRED EMBODIMENTS OF THE INVENTION
    The present invention relates to a projectile (P) and the device (1) [Figure 1] for deploying wings or fins associated therewith to ensure its stabilization in flight phase.
    In certain embodiments, the projectile (P) comprises a body (PO) having a longitudinal axis (L) and an intermediate portion comprising a device (1) for deploying airfoils (2) or fins comprising a number N, preferably equal to at least three, airfoils (2) or fins capable of being deployed, said airfoils being regularly distributed angularly around the axis (L) of the projectile. The deployment process includes at least two phases, a first deployment phase where an airfoil (2) or a wing passes from a position tangential to the body (PO) of the projectile and parallel to the longitudinal axis (L) (Figure 2A ) in a semi-deployed position (FIG. 2B), by rotation of the airfoil (2) or of the fin about an axis (ZZ ') perpendicular to the longitudinal axis (L) of the projectile (P) and a second deployment phase with the passage of the airfoil (2) or the fin from the semi-deployed position (FIG. 2B), in which it is still tangent to the body of the projectile, to a deployed position where it is perpendicular to the body of the body projectile (Figure 2C), by rotation about an axis (XX ') parallel to the longitudinal axis (L) of the projectile (P). Said projectile (P) is characterized in that the device (1) for deploying the wings (2) or fins is configured so that the rotation of a wing (2) or of a wing around the axis (XX ') parallel to the longitudinal axis (L) of the projectile (P) causes a toothing which meshes with a toothed wheel (14B) of synchronization which entails by meshing the rotation of each other wing (2) or fin around each axis (XX ') parallel to the longitudinal axis (L) of the projectile (P) to synchronize the deployment of the airfoils or fins in the second phase.
    In the following description, a certain number of parts or parts will be in a number N which is equal to the number of wings (2) or fins.
    The projectile (P) is, for example and without limitation, a missile, a shell or a rocket, the body (PO) of which can include at least three stabilizing fins (P1) fixed at the level of the tail of the body ( PO) of said projectile (P) and / or at least three pilot fins (P2) (or duck fin) fixed on the front point of the body (PO) of the projectile (P), as can be observed for example on the Figure 1, and reduced dimensions compared to the dimensions of the fins (P1) fixed at the tail of the body (PO) of the projectile.
    The deployment device (1) can be fixed on the body (PO) of the projectile (P) between the tail and the front point of said projectile (P). Preferably the device is fixed to the body (PO) of the projectile so that the airfoils (2) or fins of the device are arranged in the middle position on the body of the projectile (P) in order to improve the bearing characteristics which are provided by the wings (2), such as for example the wings of an airplane.
    The airfoils (2) are deployed in the vicinity of the apogee of the ballistic trajectory of the projectile and their lift makes it possible to increase the range of the latter.
    In certain embodiments, in the first deployment phase, the airfoils (2) or fins of the projectile (P) deploy, preferably, from the rear to the front, in the opposite direction to the aerodynamic flow, the pivot axis being mounted upstream of the airfoil (2) or the fin, in the direction of the aerodynamic flow, when the airfoil (2) or the airfoil is in position tangential to the body (PO) of the projectile ( figure 1).
    In certain embodiments, the first phase of deployment of all of the airfoils (2) or fins is ensured by a single control and lock motor (M) indirectly connected to an expansion system comprising a piston (12) of pressure and at least one compression spring (16A, 16B), as can be seen for example in FIGS. 3A, 3C and 3D, thus making it possible to lighten the mechanism in the projectile (P) while ensuring good stabilization .
    In the case where the canopies or fins of the device (1) deploy in the opposite direction to the aerodynamic flow, it is necessary to provide an effort to counter aerodynamic constraints. The pressure piston (12) and the compression springs (16A, 16B) provide this effort necessary to carry out the first deployment phase. In this arrangement of the wings or fins, the aerodynamic constraints act as a brake and thus reduce the risks that the first deployment phase is abrupt and damages the deployment device, which can thus lead to destabilization of the projectile along its trajectory. .
    In certain embodiments, the pressure piston (12) makes it possible to initiate the rotational movement of the airfoils (2) in the first deployment phase and includes guide means (121, 1221) for guiding said piston (12 ) during its translational movement, indirectly generated by the control and latch motor (M), along the longitudinal axis (L) of the projectile (P).
    In certain embodiments, the device (1) comprises a body (10) (FIGS. 3B, 3C and 3D) comprising on its external part at least one housing (103) (FIG. 3B) for receiving at least one means (11) [Figure 5B] synchronization and part of the wing (2) or the fin. The body (10) defines a central chamber (CC) in which are arranged the pressure piston (12) and at least one orientation means (17,18) (Figure 5A) and at least one synchronization means (14B) wings (2) or fins, the central chamber (CC) [Figure 3C] being between a chamber upstream with respect to the direction of aerodynamic flow and called upper (CS) in which is arranged the motor (M) controlling the deployment and the locking of the airfoils (2) and a chamber downstream relative to the direction of the aerodynamic and so-called lower flow (Cl), the central chamber (CC) and the upper chamber (CS) being separated by an upper wall (PS), and the central chamber (CC) and the lower chamber (Cl) by a lower wall (PI) (see FIG. 3C).
    In certain embodiments, the central chamber (CC) of the body (10) of the deployment device (1) also comprises at least one main column (15A), which is centered on the axis (L) of the projectile and here integral with the lower wall (PI) and positioned in a bore in the upper wall (PS), around which is wound a large spring (16A) of central compression. Conversely, the central column could be integral with the upper wall and positioned in a bore in the lower wall. A number N of secondary columns (15B), N being equal to the number of airfoils (for example five, as shown in FIGS. 2B), located on the periphery around the main column (15A), regularly distributed angularly, and around which are , also, wound with small compression springs (16B), a lock disc (13) (FIG. 3A) comprising at least the same number N of studs (130) as airfoils and at least one toothed wheel (14A) of activation activated by the control motor (M), the activation toothed wheel being linked to the lock disc (13) so as to transmit the rotational movement to it to allow the unlocking of the airfoils (2) or fins. A part of the motor (M), located in the central chamber (CC), includes a pinion (M1) meshing with the toothed activation wheel (14A), which, fixed to the lock disc (13), will cause rotation of the last. The other part (MO) of the motor (M) is located in the upper chamber (CS), the axis of the motor (M) is parallel and on the periphery of the longitudinal axis (L) of the projectile (P).
    It should be noted that for the clarity of the figures in partial section, some of the elements are not always shown. In particular, it can be seen in FIG. 3A, representing the pressure piston (12), that the rods (1220) fixed to the stops (122) are not all shown. It is the same for these elements in Figures 3C, 3D, 5C, 5D and 5E.
    In certain embodiments, the guide means (121, 1221) preferably comprise at least one guide disc (121) fixed to the rear of the body (120) of the piston (FIGS. 4A, 4B) and at least the same number N of guide rings (1221). The disc (121) slides in a bore of the body (10) [see Figures 3C and 3D]. The rings (1221) slide along the secondary columns (15B), fixed to the body (10), for example by screwing.
    In certain embodiments, the pressure piston (12) (FIGS. 4A, 4B) also comprises at least the same number N of grooves (1201) intended to come into contact with the pins (130) of the disc (13) of latch, when the latter pivots, the grooves (1201) being able to receive said pins (130). The piston (12) comprises the same number N of stops (122) on which rods (1220) are fixed. As can be seen in FIG. 4A, the grooves (1201) comprise lights (1202) because, they open into the cavity (1200) beyond a front wall (1203) receiving the support of the large spring (16A ).
    Each rod (1220) carries at its end a guide ring (1221) which is configured to receive a secondary column (15B). Each secondary column (15B) receives a small spring (16B) which is located between an internal portion of the body (10) in the vicinity of the bottom wall (PI) and the ring (1221), as shown for example in Figures 3C and 3D. The piston (12) has an axial cavity (1200) centered on the axis (L) of the projectile and configured to receive the main column (15A) and part of the large spring (16A) of central compression (Figure 3C). The large spring (16A) is disposed between and the bottom wall (PI) and the front wall (1203) of the piston (FIGS. 4A and 5B) near the outlet of the grooves (1201) (see FIG. 3D).
    In the locked state, the large spring (16A) pushes the piston (12) into abutment against the studs (130). When the control motor (M) is activated during flight, the lock disc (13) is rotated. The pins (130) are then positioned opposite the grooves (1201). This positioning of the studs (130) makes it possible to unlock the pressure piston (12) whose body (120) slides along the main column and the guide rings (1221) along the secondary columns (15B), from the wall lower (PI) towards the upper wall (PS) of the device (1), under the action of the compression springs. The displacement in translation of the piston (12) is stopped when the end of the body of said piston (12) abuts on the upper wall (PS) of the device (1). The lugs (130) of the lock disc (13) are then in abutment on surfaces included in the grooves of the piston (12).
    The guide means (121, 1221) make it possible to prevent the longitudinal axis of the piston (12) from oscillating around the longitudinal axis (L) of the projectile during the translational movement of said piston (12), in which case an offset angular could occur and the cams (17) would no longer be in front of the stops (122) of the piston. This would lead to non-deployment or partial deployment of the airfoil 2, thus causing destabilization of the projectile (P).
    In certain embodiments, the orientation means (17, 18) (FIGS. 5A, 5B, 5C and 5D) preferably comprise at least the same number N of split lugs (18). Each cleat (18) has a groove (180) capable of receiving a stud (21) located at the end of a rod (20) secured to a wing (2) or fin. Each cleat (18), integral with a cam (17), is housed in a radial bore (104) of the body (10) [see FIGS. 3D and 5A, for example], an enlarged head of the cleat (18) positioned against a counterbore in this bore (104).
    The post (21) of the rod (20) of the wing or of the fin is configured to be inserted in the groove (180) of the cleat (18) so that the movement of the cleat (18) causes that the rod (20) and therefore of the airfoil (2) or fin during the first deployment phase.
    In certain embodiments, the means (14B, 11) for synchronizing the deployment of the airfoils (2) preferably comprise at least one synchronous toothed wheel (14B) (FIGS. 5B,
    5E) arranged in a circular groove (105) coaxial with the central chamber (CC) and closed by the bottom wall (PI) (see FIG. 3B), and the same number N of pivots (11), equal to the number of canopies ( 2) (Figure 5B). Each pivot (11) is included in the housing (103) of the external part of the body (10) of the device (1) and has a cavity (111) capable of receiving the rod (20) d 'a wing (2), and a pinion (110) mounted at one of its ends, said pinion meshing with the toothed wheel (14B) synchronization (Figure 5B).
    According to the invention, the first deployment phase results from the translational displacement of the pressure piston (12) along the longitudinal axis (L) of the projectile (P) in the direction of the upper wall (PS) separating the chambers central (CC) and upper (CS) of the body (10) of the device (1), this displacement causing the rotation of the cams (17) around the axes (ZZ ') perpendicular to the longitudinal axis (L) of the projectile (P ).
    The translational movement of the piston (12) is triggered by the starting of the control and lock motor (M) which turns the lock (13) and positions the pins (130) opposite the grooves (1201) of the piston , which releases the piston (12) which can move pushed by the springs (16A) and (16B). The central compression spring (16A) and small springs (16B) change from a compressed state to a relaxed state, thus causing the pressure piston (12) to move towards the upper wall (PS).
    As shown in Figure (4B), the piston (12) has N 15 stops (122), each coming in punctual support connection with a cam (17) [see Figures 5A, 5C and 5D], The displacement of the piston (12) therefore actuates the rotation of the cams (17) (see FIG. 5D) so as to allow the passage of each wing (2) from a position tangential to the body (PO) of the projectile (P) and parallel to the longitudinal axis (L) at a semi-deployed position and tangent to the body (PO) of the projectile (P).
    In the locked position, the compression springs (16B) are compressed, as shown in FIG. 3C for example, at least one stop (122) of the pressure piston (12) being in contact with a cam (17).
    Starting the engine (M) unlocks the piston 25 (12) and compression springs (16A, 16B) which extend along the main and secondary columns (15A, 15B), allowing the piston (12 ) to move along the main column.
    The stop (122) of the pressure piston (12) in contact with the cam generates, then, the rotation of the latter about an axis (ZZ ') perpendicular to the longitudinal axis (L) of the projectile (P) . The cleat (18), linked to the cam (17) and comprising the end of the rod (20) of the airfoil (2) or of the fin, in turn causes the rotation of said airfoil or fin, making it pass from a position tangential to the body (PO) of the projectile (P) and parallel to the longitudinal axis (L) to a semi-deployed position and tangent to the body (PO) of the projectile (P) (Figure 5D).
    In certain embodiments, the device comprises at least one fixing means making it possible to prevent the continuous rotation of at least one wing (2) or fin around the axis of rotation (ZZ ') of the first phase of deployment once the second deployment phase has started.
    Thus, when the airfoils (2) or fins are in the semi-deployed position (FIG. 5A), each cam (17) abuts on a lug (130) of the lock disc (13) and is thus located between a stop (122 ) of the pressure piston (12) and a lug (130) of the disc (13). This pinching thus prevents rotation of the cam (17) as well as the cleat (18) around the axis (ZZ ’) perpendicular to the longitudinal axis (L) of the projectile (P). The tenon (21) integral with the rod (20) being engaged in the groove (180) of the cleat (18), the rod (20) of the airfoil (2) cannot therefore rotate around the axis (ZZ ' ) perpendicular to the longitudinal axis (L) of the projectile (P) when the airfoil is in the semi-deployed position.
    In certain embodiments, the second deployment phase is ensured by the rotational movement, around an axis (XX ') parallel to the longitudinal axis (L) of the projectile (P), of at least one pivot ( 11) included in at least one housing (103) of the external surface of the body (10) of the deployment device (1). During the rotation of the airfoil (2) or the fin about the axis (XX ') parallel to the longitudinal axis (L) of the projectile (P), the tenon (21) of the rod (20) of said airfoil (2) or fin leaves the groove (180) of the cleat (18), as can be seen for example in FIG. 5E, to allow the airfoil to rotate around the axis (XX ') parallel to the longitudinal axis (L) of the projectile (L).
    Furthermore, at least one groove (106) [FIG. 6B], machined in the body (10) of the device (1), can receive the pin (21) of the rod (20) when the latter comes out of the groove ( 180) of the cleat (18) during the second deployment phase of the airfoil. Such an arrangement prevents the rod (20) of the airfoil (2) or fin from rotating around the axis (ZZ ') perpendicular to the longitudinal axis (L) of the projectile (P) during the second phase of deployment.
    In certain embodiments, the pivot (11) is preferably held in the housing (103) of the external surface of the body (10) of the deployment device (1) by a front flange (102A) located at the front end of the pivot (11) towards the upper wall (PS) and by a rear flange (102B) (FIG. 5B) situated at the rear end of the pivot (11) which comprises at least one pinion (110) and in direction of the lower wall (PI). The flanges (102A, 102B) are provided with cylindrical profile grooves which cover the pivot (11) and guide the rotational movement of the pivot (11).
    The rotation of the pivot (11) causes the rotation of a pinion (110) or toothed drive of the synchronous gear (14B). When the pivot (11) rotates, causing the blade (2) or fin to rotate, the pinion (110) fixed to one end of the pivot (11) also rotates at the same speed as the latter. The pinion (110), being linked to the synchronizing gear (14B), will cause its rotation. The synchronization toothed wheel (14B), by its rotation, simultaneously induces the rotation of each of the other pinions (110) with which it is connected. The rotation of each other pinion causes the rotation of the pivot (11) with which it is associated and the rotation of each other pivot allows the rotation of the airfoil to which it is connected, thus allowing a synchronized deployment of all the airfoils or fins.
    In certain embodiments, as shown in FIGS. 3B and 6A, the housing (103) included in the external surface of the body (10) of the deployment device (1) comprises a profile forming a secondary housing (1030) in the form of V. This secondary housing (1030) is configured to receive part of the airfoil (2) or fin at the end of the deployed phase, when part of the airfoil (2) is positioned in said secondary housing (1030 ).
    îo When it rotates around the axis (XX ') parallel to the longitudinal axis (L) of the projectile (P) in the second deployment phase, the airfoil (2) or fin therefore passes from a tangential position to the body (PO) of the projectile (P) at a position perpendicular to the body (PO) of the projectile (P). Part of the airfoil (2) or the fin then comes into abutment against the wall of the secondary housing (1030) in a V shape, so as to keep the position of the airfoil (2) or the airfoil fixed. deployed phase (Figure 6B).
    In certain embodiments, the movement in the second deployment phase is activated by the result of the aerodynamic forces exerted on the airfoils (2) in the semi-deployed position.
    The present application describes various technical characteristics and advantages with reference to the figures and / or to various embodiments. Those skilled in the art will understand that the technical characteristics of a given embodiment can in fact be combined with characteristics of another embodiment unless the reverse is explicitly mentioned or it is obvious that these characteristics are incompatible or that the combination does not provide a solution to at least one of the technical problems mentioned in the present application. In addition, the technical characteristics described in a given embodiment can be isolated from the other characteristics of this mode unless the reverse is explicitly mentioned.
    It should be obvious to those skilled in the art that the present invention allows embodiments in many other specific forms without departing from the scope of the invention as claimed. Therefore, the present embodiments should be considered by way of illustration, but may be modified in the field defined by the scope of the appended claims, and the invention should not be limited to the details given above.
    权利要求:
    Claims (14)
    [1" id="c-fr-0001]
    1. Projectile (P) comprising a body (PO) having a longitudinal axis (L) and an intermediate portion comprising a device (1) for deploying airfoils or fins comprising a number N, equal to at least 3, airfoils (2 ) or fins capable of being deployed, the deployment process comprising at least two phases, a first deployment phase in which each wing (2) or wing passes from a position tangential to the body (PO) of the projectile and parallel to the axis longitudinal (L) to a semi-deployed position, by rotation of the airfoil (2) or of the wing about an axis (ZZ ') perpendicular to the longitudinal axis (L) of the projectile (P) and a second deployment phase with the passage of each wing (2) or fin from the semi-deployed position, in which it is still tangent to the body of the projectile, to a deployed position where it is perpendicular to the body of the projectile, by rotation about an axis (XX ') parallel to l longitudinal axis (L) of the projectile (P), said projectile (P) being characterized in that the device (1) for deploying the airfoils (2) or fins is configured so that the rotation of an airfoil ( 2) or of a fin about the axis (XX ') parallel to the longitudinal axis (L) of the projectile (P) causes a toothing which meshes with a toothed wheel (14B) of synchronization which entails by meshing the rotation of each other wing (2) or fin around each axis (XX ') parallel to the longitudinal axis (L) to synchronize the deployment of the wings or fins in the second phase.
    [2" id="c-fr-0002]
    2. Projectile (P) according to claim 1, characterized in that the airfoils (2) or fins are arranged in the middle position on the body of the projectile (P) in order to improve the flight characteristics of the projectile (P).
    [3" id="c-fr-0003]
    3. Projectile (P) according to one of claims 1 or 2, characterized in that, in the first deployment phase, the airfoils (2) or fins of the projectile (P) deploy from rear to front, in contraflow of the aerodynamic flow, the pivot axis being mounted upstream of the airfoil (2) or the fin in the direction of the aerodynamic flow, when the airfoil (2) or the airfoil is in tangential position to the body (PO) of the projectile.
    [4" id="c-fr-0004]
    4. Projectile (P) according to one of claims 1 to 3, characterized in that the first phase of deployment of all the wings (2) or fins is provided by a single motor (M) control and lock, indirectly connected to an expansion system comprising a pressure piston (12) and at least one compression spring (16A, 16B), thus making it possible to lighten the mechanism in the projectile (P) while ensuring good stabilization.
    [5" id="c-fr-0005]
    5. Projectile (P) according to claim 4, characterized in that the pressure piston (12) makes it possible to initiate the rotational movement of the airfoils (2) in the first deployment phase and comprises means (121, 1221) guide for guiding said piston (12) during its translational movement, indirectly generated by the motor (M) control and lock, along the longitudinal axis (L) of the projectile (P).
    [6" id="c-fr-0006]
    6. Projectile (P) according to claims 4 to 5, characterized in that the device (1) comprises a body (10) comprising on its external part at least one housing (103) for receiving at least one means (11) of synchronization and part of the airfoil (2) or of the fin, a central chamber (CC) in which the pressure piston (12) are arranged and at least one orientation means (17,18) and one means of synchronization (14B) of the airfoils (2) or fins, the central chamber (CC) being between a chamber upstream with respect to the direction of the aerodynamic flow and called upper (CS) in which is placed the motor (M) controlling the deployment and the locking of the airfoils (2) and a chamber downstream relative to the direction of the aerodynamic and so-called lower flow (Cl), the central chamber (CC) and the upper chamber (CS) being separated by an upper wall (PS), and the central chamber (CC) and the lower chamber (Cl) by a p lower aroi (PI).
    [7" id="c-fr-0007]
    7. Projectile (P) according to claim 6, characterized in that the central chamber (CC) of the body (10) of the device (1) for deployment also comprises at least one main column (15A), centered on the axis (L) of the projectile and integral with at least one of the lower (PI) or upper (PS) walls, around which a large central compression spring (16A) is wound, at least the same number N of secondary columns ( 15B) located at the periphery around the main column (15A) and around which are also wound small compression springs (16B), a lock disc (13) comprising at least the same number N of studs (130) and at least an activating toothed wheel (14A) actuated by the control motor (M), the activating toothed wheel being linked to the lock disc (13) so as to transmit the rotational movement to it to allow the unlocking of the airfoils ( 2).
    [8" id="c-fr-0008]
    8. Projectile (P) according to claim 5, characterized in that the guide means (121,1221) comprise at least one guide disc (121) fixed to the rear of the body (120) of the piston (12) and at least the same number N of guide rings (1221).
    [9" id="c-fr-0009]
    9. Projectile (P) according to the combination of claims 4 to 8, characterized in that the pressure piston (12) also comprises at least the same number N of grooves (1201) coming to face the tenons (130) of the lock disc (13) when the latter pivots, the grooves (1201) being capable of receiving said tenons (130), at least the same number N of stops (122) on which rods (1220) are fixed, each rod ( 1220) having at its end a guide ring (1221) configured to receive a secondary column (15B) so that the small spring (16B) is located between an internal portion of the body (10) in the vicinity of the bottom wall (PI) and the ring (1221), and at least one axial cavity (1200) centered on the axis (L) of the projectile and configured to receive the main column (15A) and a
    5 part of the large central compression spring (16A).
    [10" id="c-fr-0010]
    10. Projectile (P) according to claim 6, characterized in that the means (17,18) for orientation comprise at least the same number N of cleats (18) split, each cleat comprising a groove (180) capable of receiving a rod (20) integral with a wing (2) or fin îo comprising a lug (21) at its end, and at least the same number of cams (17), each cam (17) being integral with a cleat ( 18).
    [11" id="c-fr-0011]
    11. Projectile (P) according to one of claims 6 to 10, characterized in that the means (14B, 11) for synchronizing the deployment of the airfoils (2) comprise the toothed wheel (14B) for synchronization
    15 disposed in a circular groove (105) coaxial with the central chamber (CC), and the same number N of pivots (11) equal to the number of wings (2), each pivot (11) being included in the housing (103) of the external part of the body (10) of the device (1) and comprising a cavity (111) capable of receiving the rod (20) of a wing (2), and a pinion (110)
    20 mounted at one of its ends, said pinion coming to mesh on the synchronous gear (14B).
    [12" id="c-fr-0012]
    12. Projectile (P) according to one of claims 1 to 11, characterized in that it comprises at least one fixing means making it possible to prevent the continuous rotation of at least one wing (2) or fin around
    25 the axis of rotation (ZZ ’) of the first deployment phase once the second deployment phase has started.
    [13" id="c-fr-0013]
    13. Projectile (P) according to one of claims 6 to 12, characterized in that the pivot (11) is held in the housing (103) of the external surface of the body (10) of the device (1) for deployment by a flange (102A) front located at the front end of the pivot (11) towards the upper wall (PS) and by a rear flange (102B) located at the rear end of the pivot (11) comprising at least one pinion (110 ) and in
    5 direction of the lower wall (PI), the flanges (102A, 102B) being provided with cylindrical profile grooves covering the pivot (11) and guiding the rotational movement of said pivot (11).
    [14" id="c-fr-0014]
    14. Projectile (P) according to one of claims 6 to 13, characterized in that the housing (103) included in the external surface of the body (10) îo of the deployment device (1) comprises a profile forming a secondary housing (1030 ) V-shaped, configured to receive part of the airfoil (2) or fin at the end of the deployed phase, said deployed phase consisting in positioning a part of the airfoil (2) in said secondary housing (1030 ).
    30 5403 ° gÿguxe ^
    305 ^ °
    2 | Λ0 (P /
    4/10
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    同族专利:
    公开号 | 公开日
    WO2018015367A1|2018-01-25|
    FR3054030B1|2018-08-24|
    US20190219373A1|2019-07-18|
    EP3485224A1|2019-05-22|
    EP3485224B1|2020-06-10|
    US11079206B2|2021-08-03|
    引用文献:
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    EP0318359A1|1987-11-26|1989-05-31|GIAT Industries|Device for spreading projectile wings|
    WO2002079716A1|2001-03-20|2002-10-10|Bofors Defence Ab|Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith|
    EP2354755A1|2010-01-28|2011-08-10|Nexter Munitions|Device for simultaneously deploying control surfaces of a projectile|
    US20130032659A1|2011-08-03|2013-02-07|Raytheon Company|Ring gear control actuation system for air-breathing rocket motors|
    EP2620738A1|2012-01-27|2013-07-31|Tda Armements S.A.S.|Steering section for guided munition|
    US8921749B1|2013-07-10|2014-12-30|The United States Of America As Represented By The Secretary Of The Navy|Perpendicular drive mechanism for a missile control actuation system|WO2019211716A1|2018-05-02|2019-11-07|Nexter Munitions|Ramjet-propelled projectile|US3102437A|1960-11-23|1963-09-03|Gen Motors Corp|Electromechanical actuator|
    US4664339A|1984-10-11|1987-05-12|The Boeing Company|Missile appendage deployment mechanism|
    DE3827590C2|1988-08-13|1992-01-23|Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De|
    US4869442A|1988-09-02|1989-09-26|Aerojet-General Corporation|Self-deploying airfoil|
    US5125131A|1991-01-14|1992-06-30|Hughes Aircraft Company|Hinge locking mechanism with disengage action|
    US5829715A|1996-04-19|1998-11-03|Lockheed Martin Vought Systems Corp.|Multi-axis unfolding mechanism with rate controlled synchronized movement|
    US6761331B2|2002-03-19|2004-07-13|Raytheon Company|Missile having deployment mechanism for stowable fins|
    US9545991B1|2015-11-11|2017-01-17|Area-I Inc.|Aerial vehicle with deployable components|US11255648B2|2018-11-08|2022-02-22|Mbda Incorporated|Projectile with a range extending wing assembly|
    SE2000115A1|2020-07-03|2022-01-04|Saab Ab|A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly|
    法律状态:
    2017-06-20| PLFP| Fee payment|Year of fee payment: 2 |
    2018-01-19| PLSC| Search report ready|Effective date: 20180119 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1601109|2016-07-18|
    FR1601109A|FR3054030B1|2016-07-18|2016-07-18|PROJECTILE COMPRISING A DEVICE FOR DEPLOYING A VESSEL OR AILT|FR1601109A| FR3054030B1|2016-07-18|2016-07-18|PROJECTILE COMPRISING A DEVICE FOR DEPLOYING A VESSEL OR AILT|
    US16/318,600| US11079206B2|2016-07-18|2017-07-18|Projectile comprising a device for deploying a wing or fin|
    EP17749617.1A| EP3485224B1|2016-07-18|2017-07-18|Projectile comprising a device for deploying a wing or fin|
    PCT/EP2017/068092| WO2018015367A1|2016-07-18|2017-07-18|Projectile comprising a device for deploying a wing or fin|
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