EP3485224A1 - Projectile comprenant un dispositif de déploiement d'une voilure ou ailette - Google Patents
Projectile comprenant un dispositif de déploiement d'une voilure ou ailetteInfo
- Publication number
- EP3485224A1 EP3485224A1 EP17749617.1A EP17749617A EP3485224A1 EP 3485224 A1 EP3485224 A1 EP 3485224A1 EP 17749617 A EP17749617 A EP 17749617A EP 3485224 A1 EP3485224 A1 EP 3485224A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- projectile
- wings
- wing
- deployment
- fin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 claims abstract description 4
- 230000008569 process Effects 0.000 claims abstract description 4
- 230000006835 compression Effects 0.000 claims description 18
- 238000007906 compression Methods 0.000 claims description 18
- 230000007246 mechanism Effects 0.000 claims description 11
- 230000006641 stabilisation Effects 0.000 claims description 9
- 238000011105 stabilization Methods 0.000 claims description 9
- 230000004913 activation Effects 0.000 claims description 8
- 230000001360 synchronised effect Effects 0.000 claims description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 238000006073 displacement reaction Methods 0.000 description 4
- 230000001687 destabilization Effects 0.000 description 2
- 241000272525 Anas platyrhynchos Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
Definitions
- Projectile comprising a device for deploying a wing or fin
- the present invention relates to the field of outdoor ballistics and more particularly to the stabilization of projectiles moving in space. More specifically, the invention relates to a projectile and its associated wing or fin deployment device.
- projectiles for this purpose, are provided with mechanisms or devices for deployment of wings or wings for their stabilization.
- the combination of such a mechanism or device with the projectile must not, however, lead to a significant variation in the dimensions of the projectile architecture, at the risk of either aggravating the 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 fin deployment mechanism, the arrangement of which does not reduce the useful volume of the projectile, said deployment mechanism pivots automatically by rotating a fin from a stowed orientation to an extended orientation .
- the deployment mechanism includes a spring that provides a pushing force allowing the fin to move quickly, simply and reliably from the orientation stowed to the deployed orientation.
- the deployment mechanism which is carried out in three steps, 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 associated with a device for deploying a fin secured to the projectile by a hinge located at the rear of the projectile body, said hinge being such that the deployment movement is carried out in two phases: a first phase in which the fin passes from a position of carriage 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 it is in load 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 joint comprises a motor acting as an actuator of the first phase of deployment and locking of the fin assembly, articulation when the fin is in position of carriage.
- the object of the present invention is to overcome one or more disadvantages of the prior art by proposing a projectile architecture comprising an effective and reliable wing or fin deployment device regardless of the trajectory of said projectile.
- a projectile comprising a body having a longitudinal axis and an intermediate portion comprising a wing or fin deployment device comprising a number N, equal to at least three, wings or wings 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.
- the device for deploying the wings or wings is configured so that the rotation of a wing or wing around the axis parallel to the longitudinal axis of the projectile causes a toothing which meshes with a timing gear which meshes with the rotation of each other blade or fin about each axis parallel to the longitudinal axis of the projectile to synchronize the deployment of wings or wings in the second phase.
- the wings or fins are arranged in the median position on the body of the projectile to improve the flight characteristics of the projectile.
- the wings or wings of the projectile deploy from the rear to the front, in the opposite direction of 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 wing or the fin is in position tangential to the body of the projectile.
- the first phase of deployment of all the wings or wings is provided by a single control and latch motor indirectly connected to an expansion system comprising a pressure piston and at least one compression spring, allowing thus lighten the mechanism in the projectile while ensuring good stabilization.
- the pressure piston makes it possible to initiate the rotation movement of the wings in the first deployment phase and comprises guide means for guiding said piston during its translational movement indirectly generated by the control motor. and lock, along the longitudinal axis of the projectile.
- the device comprises a body comprising on its outer part at least one housing for receiving at least one synchronizing means and a part of the wing or 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 wings or fins, the central chamber being between a chamber upstream with respect to the direction of aerodynamic flow and said upper in which is disposed the engine controlling the deployment and the lock of the wings and a downstream chamber with respect to the direction of the aerodynamic flow and said lower, the central chamber and the upper chamber being separated by an upper wall, and the central chamber and the lower chamber by a bottom wall.
- 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 secondary columns located peripherally around the main column and around which are also wound small compression springs, a lock disc having at least the same number N of tenons and at minus an activation gear wheel actuated by the control motor, the activation gear being connected to the lock disc so as to transmit to it the rotational movement to allow the unlocking of the wings or wings.
- the guide means comprise at least one guide disc fixed at the rear of the piston body and at least the same number N of guide rings.
- the pressure piston also comprises at least the same number N of grooves and coming to face the tenons of the latch disc when the latter pivots, the grooves being able to receive said tenons, at least the same number N stops on which are fixed rods, each rod having at its end a guide ring configured to receive a secondary column so that the small spring is located between an inner portion of the body in the vicinity of the bottom wall and the ring, and at least one axial cavity centered on the axis of the projectile and configured to receive the main column and a portion of the central large compression spring.
- the orientation means comprise at least the same number N of split cleats, each cleat having a groove adapted to receive a rod secured to a wing or wing comprising a tenon at its end, and at least the same number N of cams, each cam being secured to a cleat.
- the means for synchronizing the deployment of the wings comprise at least the synchronous 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 wings, each pivot being included in the housing of the outer part of the body of the device and having a cavity adapted to receive the stem of a wing, and a pinion mounted at one of its ends, said pinion coming to mesh with the synchronous gear wheel .
- the device comprises at least one fastening means for preventing the continuous rotation of at least one wing or wing around the axis of rotation of the first deployment phase once the second deployment phase. engaged.
- the pivot is held in the housing of the outer surface of the body of the deployment device by a front flange located at the front end of the pivot towards the upper wall and by a rear flange at the end. rear of the pivot comprising at least one pinion and in the direction of the bottom wall, the flanges being provided with cylindrical profile grooves covering the pivot and guiding the rotational movement of said pivot.
- the housing included in the external surface of the body of the deployment device comprises a profile forming a V-shaped secondary housing, configured to receive a portion of the wing or wing at the end of the deployed phase, said deployed phase of positioning a portion of the wing in said secondary housing.
- FIG. 1 shows a perspective view of the projectile, according to one embodiment
- FIG. 2A; 2B and 2C show 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
- FIG. 3A; 3B, 3C and 3D show a perspective view, according to an embodiment, respectively of the control motor indirectly coupled to the pressure piston by the activation gear and the lock disc, of a section of the body of the empty deployment of its elements, a section of the body of the deployment device with the pressure piston and the compression springs before and after the first deployment phase;
- FIG. 4A and 4B represent a perspective view of the pressure piston, according to one embodiment
- FIGS. 5A and 5D are a perspective view of a section of the deployment device, the wings or wings in half-deployed position according to one embodiment
- Figures 5B and 5E show a perspective view of the deployment device, the wings or fins in deployed position, according to one embodiment
- Figure 5C shows a perspective view of the section of the deployment device before the first deployment phase, according to one embodiment
- FIGS. 6A and 6B show a view from above, according to one embodiment, of the part of the deployment device comprising the pivot axis of the wing or fin, respectively in the half-deployed position and in the deployed position;
- the present invention relates to a projectile (P) and the device (1) [FIG. 1] for deployment of wings or fins associated therewith to ensure its stabilization in the flight phase.
- the projectile (P) comprises a body (PO) having a longitudinal axis (L) and an intermediate portion comprising a device (1) for deployment of wings (2) or fins having a number N, preferably equal to at least three, wings (2) or wings capable of being deployed, said wings being evenly distributed angularly about the axis (L) of the projectile.
- the deployment process comprises at least two phases, a first deployment phase where a wing (2) or fin passes from a position tangential to the body (PO) of the projectile and parallel to the longitudinal axis (L) ( Figure 2A).
- said projectile (P) is characterized in that the device (1) for deploying the wings (2) or wings is configured so that the rotation of a wing (2) or a fin about the axis ( XX ') parallel to the longitudinal axis (L) of the projectile (P) causes a toothing which meshes with a synchronous tooth gear (14B) which meshes with the rotation of each other wing (2) or wing around each axis. (XX ') parallel to the longitudinal axis (L) of the projectile (P) to synchronize the deployment of wings or fins in the second phase.
- 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, whose body (PO) may comprise 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 fins (P2) of piloting (or duck wing) fixed on the front tip of the body (PO) of the projectile (P), as can be observed for example on the Figure 1, and reduced in size compared to the dimensions of the fins (P1) attached to 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 tip of said projectile (P).
- the device is fixed to the body (PO) of the projectile so that the wings (2) or wings of the device are arranged in a median position on the body of the projectile (P) to improve the lift characteristics which are provided by the wings (2), such as the wings of an airplane.
- the wings (2) are deployed near the apogee of the ballistic trajectory of the projectile and their lift increases the range of the latter.
- the wings (2) or wings of the projectile (P) are preferably deployed from the rear to the front, in the opposite direction of the aerodynamic flow, the pivot axis being mounted upstream of the wing (2) or the fin, in the direction of the aerodynamic flow, when the wing (2) or the fin is in position tangential to the body (PO) of the projectile ( figure 1 ).
- the first phase of deployment of all the wings (2) or wings is provided by a single motor (M) control and latch 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 Figures 3A, 3C and 3D, thereby lightening the mechanism in the projectile (P) while ensuring good stabilization .
- the aerodynamic constraints act as a brake and thus reduce the risks that the first phase of deployment is sudden and damage the deployment device, which can lead to a destabilization of the projectile along its trajectory .
- the pressure piston (12) initiates the rotational movement of the wings (2) in the first deployment phase and comprises means (121, 1221) for guiding said piston (12). ) during its displacement in translation, indirectly generated by the motor (M) control and lock, along the longitudinal axis (L) of the projectile (P).
- the device (1) comprises a body (10) (FIGS. 3B, 3C and 3D) comprising on its outer part at least one housing (103) (FIG. 3B) for receiving at least one means (1 1 ) [ Figure 5B] synchronization and a portion of the wing (2) or fin.
- the body (10) delimits a central chamber (CC) in which the pressure piston (12) and at least one orientation means (17, 18) (FIG. 5A) and at least one synchronization means (14B) are arranged.
- the central chamber (CC) [ Figure 3C] being between a chamber upstream with respect to the direction of the aerodynamic flow and said upper (CS) in which is arranged the motor (M) controlling the deployment and locking of the wings (2) and a downstream chamber with respect to the direction of the aerodynamic flow and said lower (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 (C1) by a bottom wall (PI) (see Figure 3C).
- the motor (M) controlling the deployment and locking of the wings (2) and a downstream chamber with respect to the direction of the aerodynamic flow and said lower (Cl)
- the central chamber (CC) and the upper chamber (CS) being separated by an upper wall (PS)
- the central chamber (CC) and the lower chamber (C1) by a bottom wall (PI) (see Figure 3C).
- 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 integral here with the lower wall (PI) and positioned in a bore of the upper wall (PS), around which is wound a large spring (16A) of central compression.
- the central column could be secured to the upper wall and positioned in a bore of the bottom wall.
- a number N of secondary columns (15B), N being equal to the number of wings (for example five, as shown in Figures 2B), located around the main column (15A), regularly distributed angularly, and around which are , also, wound with small compression springs (16B), a latch disk (13) (FIG.
- 3A comprising at least the same number N of tenons (130) as of wings and at least one activation gear (14A) actuated by the control motor (M), the activation gear being connected to the lock disc (13) so as to transmit to it the rotational movement to enable the unlocking of wings (2) or fins.
- a part of the motor (M) located in the central chamber (CC), comprises a pinion (M1) meshing with the activation gear (14A), which, fixed to the latch disk (13), will cause the rotation of the last.
- the other part (MO) of the engine (M) is in the upper chamber (CS), the axis of the engine (M) is parallel and peripheral to the longitudinal axis (L) of the projectile (P).
- the guide means (121, 1221) preferably comprise at least one guide disk (121) attached to the rear of the piston body (120) (FIGS. 4A, 4B) and at least one 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.
- the pressure piston (12) (FIGS. 4A, 4B) also comprises at least the same number N of grooves (1201) intended to face the lugs (130) of the disk (13) of latch, when the latter rotates, the grooves (1201) being adapted to receive said tenons (130).
- the piston (12) comprises the same number N of stops (122) on which rods (1220) are fixed.
- the grooves (1201) comprise slots (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 situated between an inner portion of the body (10) in the vicinity of the lower wall (PI) and the ring (1221), as represented for example in FIGS. 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 a portion of the large central compression spring (16A) ( Figure 3C).
- the large spring (16A) is disposed between and the lower wall (PI) and the front wall (1203) of the piston ( Figures 4A and 5B) adjacent the outlet of the grooves (1201) (see Figure 3D).
- the large spring (16A) pushes the piston (12) abutting against the pins (130).
- the latch disk (13) is rotated.
- the pins (130) are then positioned opposite the grooves (1201). This positioning of the tenons (130) allows to unlock the piston (12) pressure whose body (120) slides along the main column and the guide rings (1221) along the secondary columns (15B) of the wall lower (PI) to the upper wall (PS) of the device (1), under the action of the compression springs.
- the translational movement 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 latch disk (13) are then abutting 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) oscillating about 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 a non-deployment or a partial deployment of the wing 2, thus causing a destabilization of the projectile (P).
- the orientation means (17, 18) (FIGS. 5A, 5B, 5C and 5D) preferably comprise at least the same number N of slit cleats (18).
- Each cleat (18) has a groove (180) adapted to receive a pin (21) located at the end of a rod (20) integral with 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 Figures 3D and 5A, for example], an enlarged head of the cleat (18) is positioning against a countersink of this bore (104).
- the tongue (21) of the wing or fin rod (20) is configured to fit into the groove (180) of the cleat (18) so that the movement of the cleat (18) causes the cleat (18) to move. rod (20) and therefore the wing (2) or fin during the first phase of deployment.
- the wing deployment synchronization means (14B, 1 1) preferably comprise at least one synchronous gear (14B) (FIGS. 5B, 5E) arranged in a circular groove ( 105) coaxial with the central chamber (CC) and closed by the lower wall (PI) (see Figure 3B), and the same number N of pivots (1 1), equal to the number of wings (2) ( Figure 5B).
- Each pivot (1 1) is included in the housing (103) of the external part of the body (10) of the device (1) and comprises a cavity (1 1 1) adapted to receive the stem (20) of a wing ( 2), and a pinion (1 10) mounted at one of its ends, said pinion coming to mesh with the timing gear (14B) (FIG. 5B).
- the first deployment phase results from the displacement in translation of the piston (12) of pressure 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) about the axes ( ⁇ ') perpendicular to the longitudinal axis (L) of the projectile (P). ).
- the translational movement of the piston (12) is triggered by the start of the motor (M) control and latch which rotates the latch (13) and positions the tenons (130) facing 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) move from a compressed state to a relaxed state thereby causing the piston (12) to move towards the upper wall (PS).
- the piston (12) has N stops (122), each coming in point support connection with a cam (17) [see Figures 5A, 5C and 5D].
- the displacement of the piston (12) thus 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 (P0) of the projectile (P) and parallel to the longitudinal axis (L) at a semi-extended position and tangent to the body (P0) of the projectile (P).
- 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).
- the stop (122) of the piston (12) of pressure in contact with the cam then generates the rotation thereof around an axis ( ⁇ ') perpendicular to the longitudinal axis (L) of the projectile (P).
- the device comprises at least one fastening means for preventing the continuous rotation of at least one wing (2) or wing around the axis of rotation ( ⁇ ') of the first phase of deployment once the second deployment phase is engaged.
- each cam (17) abuts on a tenon (130) of the latch disk (13) and thus lies between a stop (122) of the pressure piston (12) and a pin (130) of the latch disk (13). This pinching thus prevents rotation of the cam (17) and the cleat (18) about the axis ( ⁇ ') perpendicular to the longitudinal axis (L) of the projectile (P).
- the stem (20) of the wing (2) can not rotate around the axis ( ⁇ ' ) perpendicular to the longitudinal axis (L) of the projectile (P) when the wing is in a semi-extended position.
- the second deployment phase is ensured by the rotational movement, about an axis (XX ') parallel to the longitudinal axis (L) of the projectile (P), of at least one pivot ( 1 1) included in at least one housing (103) of the outer surface of the body (10) of the deployment device (1).
- At least one groove (106) [FIG. 6B], machined in the body (10) of the device (1), can receive the tenon (21) of the rod (20) when the rod (20) comes out of the groove ( 180) of the cleat (18) during the second deployment phase of the sails.
- Such an arrangement prevents the shank (20) of the wing (2) or fin from rotating about the axis ( ⁇ ') perpendicular to the longitudinal axis (L) of the projectile (P) during the second deployment phase.
- the pivot (1 1) is preferably held in the housing (103) of the outer surface of the body (10) of the deployment device (1) by a front flange (102A) front end of the pivot (1 1) in the direction of the upper wall (PS) and by a rear flange (102B) (FIG. 5B) located at the rear end of the pivot (1 1) which comprises at least one pinion (1 10) and towards the lower wall (PI).
- the flanges (102A, 102B) are provided with grooves cylindrical profile which cap the pivot (1 1) and guide the rotational movement of the pivot (1 1).
- the rotation of the pivot (1 1) causes the rotation of a pinion (1 10) or gear teeth of the timing gear (14B).
- the pinion (1 10) attached to one end of the pivot (1 1) also rotates at the same speed as the latter.
- the pinion (1 10 being connected to the timing gear (14B), will cause its rotation.
- the synchronous toothed wheel (14B) by its rotation, simultaneously induces the rotation of each of the other pinions (1 10) with which it is connected.
- the rotation of each other pinion causes the rotation of the pivot (1 1) to which it is associated and the rotation of each other pivot allows the rotation of the blade to which it is connected, thus allowing a synchronized deployment of all the wings or wings.
- the housing (103) included in the outer surface of the body (10) of the deployment device (1) comprises a profile forming a secondary housing (1030) in the form of a V.
- This secondary housing (1030) is configured to receive a portion of the wing (2) or winglet at the end of the deployed phase, when a portion of the wing (2) is positioned in said secondary housing (1030).
- the wing (2) or fin When it rotates about the axis (XX ') parallel to the longitudinal axis (L) of the projectile (P) in the second deployment phase, the wing (2) or fin passes from a tangential position to the body (P0) of the projectile (P) at a position perpendicular to the body (P0) of the projectile (P). A part of the wing (2) or the fin then comes into abutment against the wall of the V-shaped secondary housing (1030), so as to hold the position of the wing (2) or the fin in fixed position. deployed phase (FIG. 6B).
- the movement in the second deployment phase is activated by the resultant aerodynamic forces exerted on the wings (2) in the half-deployed position.
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Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1601109A FR3054030B1 (fr) | 2016-07-18 | 2016-07-18 | Projectile comprenant un dispositif de deploiement d'une voilure ou ailette |
PCT/EP2017/068092 WO2018015367A1 (fr) | 2016-07-18 | 2017-07-18 | Projectile comprenant un dispositif de déploiement d`une voilure ou ailette |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3485224A1 true EP3485224A1 (fr) | 2019-05-22 |
EP3485224B1 EP3485224B1 (fr) | 2020-06-10 |
Family
ID=57906654
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17749617.1A Active EP3485224B1 (fr) | 2016-07-18 | 2017-07-18 | Projectile comprenant un dispositif de déploiement d'une voilure ou ailette |
Country Status (4)
Country | Link |
---|---|
US (1) | US11079206B2 (fr) |
EP (1) | EP3485224B1 (fr) |
FR (1) | FR3054030B1 (fr) |
WO (1) | WO2018015367A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3080912B1 (fr) | 2018-05-02 | 2020-04-03 | Nexter Munitions | Projectile propulse par statoreacteur |
US11255648B2 (en) * | 2018-11-08 | 2022-02-22 | Mbda Incorporated | Projectile with a range extending wing assembly |
SE544263C2 (en) * | 2020-07-03 | 2022-03-22 | Saab Ab | A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly |
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FR2623898B1 (fr) * | 1987-11-26 | 1990-03-23 | France Etat Armement | Dispositif de deploiement d'une ailette de projectile |
DE3827590A1 (de) * | 1988-08-13 | 1990-02-22 | Messerschmitt Boelkow Blohm | Flugkoerper |
US4869442A (en) * | 1988-09-02 | 1989-09-26 | Aerojet-General Corporation | Self-deploying airfoil |
US5125131A (en) * | 1991-01-14 | 1992-06-30 | Hughes Aircraft Company | Hinge locking mechanism with disengage action |
US5829715A (en) * | 1996-04-19 | 1998-11-03 | Lockheed Martin Vought Systems Corp. | Multi-axis unfolding mechanism with rate controlled synchronized movement |
SE521445C2 (sv) * | 2001-03-20 | 2003-11-04 | Bofors Defence Ab | Sätt att synkronisera fenutfällningen vid en fenstabiliserad artillerigranat samt en i enlighet därmed utformad artillerigranat |
US6761331B2 (en) * | 2002-03-19 | 2004-07-13 | Raytheon Company | Missile having deployment mechanism for stowable fins |
FR2955653A1 (fr) * | 2010-01-28 | 2011-07-29 | Nexter Munitions | Dispositif de deploiement simultane de gouvernes d'un projectile |
US8530809B2 (en) * | 2011-08-03 | 2013-09-10 | Raytheon Company | Ring gear control actuation system for air-breathing rocket motors |
FR2986319B1 (fr) * | 2012-01-27 | 2014-03-14 | Tda Armements Sas | Troncon de pilotage pour munition guidee |
US8921749B1 (en) * | 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 |
US9555873B1 (en) * | 2015-11-11 | 2017-01-31 | Area-I Inc. | Aerial vehicle with deployable components |
-
2016
- 2016-07-18 FR FR1601109A patent/FR3054030B1/fr not_active Expired - Fee Related
-
2017
- 2017-07-18 EP EP17749617.1A patent/EP3485224B1/fr active Active
- 2017-07-18 WO PCT/EP2017/068092 patent/WO2018015367A1/fr unknown
- 2017-07-18 US US16/318,600 patent/US11079206B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US11079206B2 (en) | 2021-08-03 |
US20190219373A1 (en) | 2019-07-18 |
FR3054030B1 (fr) | 2018-08-24 |
WO2018015367A1 (fr) | 2018-01-25 |
EP3485224B1 (fr) | 2020-06-10 |
FR3054030A1 (fr) | 2018-01-19 |
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