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
  • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
  • F42B10/16—Wrap-around fins

Definitions

• Projectiles often comprise wings for enhancing flight characteristics.
• the projectiles are often accommodated in narrow compartments, such as canisters and launch tubes.
• the wings are folded. After a projectile have been launched, the wings of the projectile have to be rapidly unfolded and fixed, so that a steady flight may be achieved.
• deployment actuators of various configurations.
• An object of the present invention is to achieve an advantageous wing arrangement for a projectile.
• Another object of the invention is to achieve a compact wing arrangement.
• a further object of the invention is to improve the aerodynamic properties.
• a method for deploying a wing blade for a projectile by using a wing arrangement comprising: an elongated wing base configured to be arranged at a circumferential wall of the projectile, the wing base extending longitudinally between a first end and a second end; a wing blade configured to be attached to the wing base along a pivot axis extending along the longitudinal extension of the wing base, the wing blade being folded towards the circumferential wall of the projectile in the folded state and extending away from the circumferential wall in the deployed state; a deployment arrangement configured to control a pivotal movement of the wing blade around the pivot axis from the folded state to the deployed state.
• a use of a wing arrangement as disclosed herein for deployment of a wing blade during launch of a projectile is provided.
• a projectile comprising at least one wing arrangement as disclosed herein is provided.
• Previously known solutions for deployment of wings are often relatively space consuming. In order to manage the heavy air flows that the wing arrangement may be exposed to at launch and after launch, prior art solutions may often be relatively bulky and take up valuable space inside the projectile. Alternatively, existing solutions may be arranged in the wing blade and/or on the outside of the projectile body where the wing blade and the projectile body intersects. Such configurations may affect the aerodynamic properties of the projectile negatively and significantly increase drag. Consequently, such known solutions may not be a pertinent option for projectiles comprising thin wings.
• the wing arrangement may essentially be arranged in association with the circumferential wall of the projectile body.
• a compact wing arrangement is achieved, which saves valuable space within the projectile.
• a compact wing arrangement arranged essentially in association with the circumferential wall of the projectile may also facilitate thinner wing blades, which may improve the aerodynamic properties.
• a relatively small and compact wing arrangement also reduces the weight of the projectile, which is favourable.
• a smooth and streamlined wing arrangement may be achieved, reducing drag and further improving the aerodynamic properties of the projectile.
• the aerodynamic properties of the projectile may be affected by the smoothness of the projectile and wings, since the amount of drag generated by an object depends on the shape and evenness of the object.
• Commonly known wing folding solution comprising hinge suspended wing blades may often comprise gaps, recesses and protruding parts, which increases drag.
• the configuration of the wing arrangement according to the present disclosure allows for a smoother configuration compared to other known solutions, both on the inside and the outside of the circumferential wall of the projectile.
• the streamlined configuration on the outside of the projectile has the benefit of decreasing drag.
• the smooth configuration on the inside may be favourable since it saves valuable space within the projectile and enables dismantling of the circumferential wall of the projectile without having to disassemble the wings from the circumferential wall. Hence, service and maintenance of the projectile may be less time consuming, which in turn reduces costs.
• the configuration of the deployment arrangement increase the possibilities of upscaling the dimensions of the projectile and/or the wing blade, while maintaining the wing blades relatively thin.
• the wing arrangement may be customized to the present application, without impacting the aerodynamic properties. Thereby, an advantageous wing arrangement may be achieved, adaptable to the current configuration of the projectile.
• a wing blade By deploying a wing blade by using a wing arrangement as disclosure herein, an efficient, forceful and reliable deployment of the wing blade may be achieved.
• the drive block By activating the power source, the drive block may be displaced. As a result, the deploying motion of the wing blade is set into motion. Thereby, a robust, steady and effective deployment of the wing blade may be achieved.
• the wing arrangement for a projectile will be described in further detail below. It is understood that all the various examples of the wing arrangement also applies for the use of a such a wing arrangement for deployment of a wing blade during launch of a projectile, the projectile comprising such a wing arrangement and the method for deploying a wing blade for a projectile.
• a wing arrangement for a projectile comprising: an elongated wing base configured to be arranged at a circumferential wall of the projectile, the wing base extending longitudinally between a first end and a second end; a wing blade configured to be attached to the wing base along a pivot axis extending along the longitudinal extension of the wing base, the wing blade being folded towards the circumferential wall of the projectile in the folded state and extending away from the circumferential wall in the deployed state; a deployment arrangement configured to control a pivotal movement of the wing blade around the pivot axis from the folded state to the deployed state, the deployment arrangement comprises a power source, a drive block and an elongated drive pin, the drive pin extending longitudinally between a proximal end and a distal end through an aperture in the wing base, the proximal end of the drive pin
• the wing arrangement as disclosed herein may be used for any projectile with deployable wings, such as a missile or a grenade.
• a missile may often comprise deployable wings arranged at a front or middle portion of a missile body, and deployable steerable wings, which may also referred to as fins, arranged at the rear of the missile body.
• deployable wings By means of steerable fins, the missile's flight trajectory may be controlled after launch.
• Grenades may also comprise wings. However, these wings are generally not steerable.
• the deployable wing blade as disclosed herein may essentially be used for fixed wings stabilising the motion of the projectile. However, the wing arrangement as disclosed herein may also be applicable for deployable steerable wings.
• the wing arrangement may be configured for projectiles of a length along a centre axis A of more than 1.5 metres, or more than 2 metres, or more than 2.5 metres, or more than 3 metres, or more than 3.5 metres, or more than 4 metres.
• the wing arrangement may be configured for projectiles with a cross-sectional diameter of more than 0.2 metre, or more than 0.3 metre, or more than 0.4 metre, or more than 0.45 metre.
• the wing blade may extend more than 0.05 metre, or more than 0.1 metre, or more than 0.14 metre, away from the circumferential wall of the projectile in the deployed state.
• the wing arrangement as disclosed herein may be configured for relatively large and forceful projectiles.
• the wing arrangement as disclosed herein may be scaled down as well as scaled up depending on the current application.
• the wing arrangement is configured to be altered between a folded state and a deployed state. Due to the two different states, a compact configuration for storage and launch may be enabled in the folded state, and a relatively large wing area may be facilitated in the deployed state. According to an example, the wing blade may be folded towards the circumferential wall of the projectile in the folded state and extending in an essentially perpendicular direction from a centre axis of the projectile in the deployed state.
• the wing base may extend longitudinally essentially in parallel with a centre axis of the projectile, between the first end and the second end of the wing base.
• the wing base may be fixedly arranged to the circumferential wall of the projectile.
• the wing base may be fixedly arranged to the circumferential wall of the projectile by means of screws, bolts, rivets or any other suitable fastening device.
• the wing arrangement may comprise a fixing arrangement for fastening the wing base to the circumferential wall.
• the fixing arrangement may comprises fixing fasteners and a fixing plate with holes.
• the fixing plate may be rigidly connected to the wing base.
• the fixing arrangement may further comprise floating anchor nuts.
• the elongated wing base may be configured to follow an outline of the circumferential wall of the projectile along the longitudinal extension of the wing base between the first end and the second end. Thereby, a streamlined intersection between the wing base and the circumferential wall may be obtained, and drag may be reduced. Due to that the wing blade may be configured to be attached to the wing base along the pivot axis along at least a part of the longitudinal extension of the elongated wing base, the wing blade may securely be coupled to the circumferential wall of the projectile.
• the wing blade may be configured to be attached to the wing base along the pivot axis by means of at least one mechanical bearing. According to an example, the mechanical bearing may comprise a hinge mechanism.
• the power source may comprise mechanical or electric power, such as spring force or an electric motor.
• the power source may comprise hydraulic or pneumatic power.
• the power source may e.g. comprise pressurized fluid, such as a liquid or a gas.
• the power source may comprise explosives.
• the force of the power source may be affected by the gas pressure and the geometrical configuration of the expansion chamber.
• the area differential of the drive block on different sides of the expansion chamber may affect the power exerted on the drive block.
• the power exerted by the gas may be tuned by means of altering the gas pressure and/or the geometrical configuration of the expansion chamber.
• the drive pin may be longitudinally arranged in a direction essentially perpendicular to the direction of the force exerted by the power source.
• the power source may exert force in a direction perpendicular to the longitudinal extension of the drive pin.
• the drive pin may be arranged perpendicular to the longitudinal extension of the drive block.
• the drive block may be displaced by the powers source in a direction parallel to the pivot axis for obtaining the deployed state.
• the pivot axis may be arranged essentially in parallel with the centre axis of the projectile. Alternatively, the pivot axis may be arranged at an angle relative the centre axis of the projectile.
• the wing blade may be pivoted around the pivot axis to the deployed state when the power source displaces the drive block.
• the power source displaces the drive block, which in turn moves the drive pin, which in turn relocates the wing blade.
• the relocation of the wing blade may be obtained by means of that the distal end of the drive pin is forced to slide along the groove in the wing blade, due to that the drive block exert force on the proximal end of the drive pin.
• the wing blade rotates to the deployed state and a forceful and reliable deployment may be facilitated while saving valuable space in the projectile and in the wing blade.
• wing arrangement comprising a wing base, a wing blade and a deployment arrangement as disclosed herein, an advantageous, reliable and compact wing arrangement may be achieved, which enables a forceful and reliable deployment of a folded wing blade, and thus increases the stabilising effects without reducing the cargo space within the projectile or impairing the aerodynamic properties.
• the configuration of the wing arrangement according to the present disclosure allows for a streamlined and aerodynamic configuration, without major gaps or projections. Thereby, the stabilising effects of the wing blade may be improved and the flight characteristics of the projectile further enhanced.
• the groove in the wing blade comprises a first stop end and a second stop end, wherein the distal end of the drive pin is arranged in the first stop end in the folded state and in the second stop end in the deployed state, wherein the first stop end of the groove is configured to retaining the wing blade in the folded state.
• the second stop end of the groove may be configured to retain the wing blade in the deployed state.
• the first stop end and/or the second stop end may be configured as a straight part of the groove extending in parallel with the pivot axis.
• the wing arrangement may be configured as previously described herein.
• all the various examples of the wing arrangement disclosed herein may also apply for the method for deploying a wing blade for a projectile.
• the power source and the drive block may be arranged on the inside of the circumferential wall of the projectile.
• a larger and more powerful powers source may be applied compared to the option of arranging the power source in a more limited space, such as inside the wing blade.
• a more potent deployment may be facilitated, which in turn may increase the possibilities of upscaling the dimensions of the projectile and/or the wing blade.
• Figures 2a-2c show perspective views of the wing arrangement 10 according to an example of the present disclosure.
• Figure 2a shows the wing arrangement 10 in the folded state
• figure 2b shows the wing arrangement 10 in an intermediate state, between the folded state and the deployed state
• figure 2c shows the wing arrangement 10 in the deployed state.
• the wing arrangement 10 may comprise: an elongated wing base 20 configured to be arranged at a circumferential wall 2 of the projectile 1, the wing base 20 extending longitudinally between a first end 21 and a second end 22; a wing blade 30 configured to be attached to the wing base 20 along a pivot axis P extending along the longitudinal extension of the wing base 20, the wing blade 30 being folded towards the circumferential wall 2 of the projectile 1 in the folded state and extending away from the circumferential wall 2 in the deployed state; a deployment arrangement 40 configured to control a pivotal movement of the wing blade 30 around the pivot axis P from the folded state to the deployed state, the deployment arrangement 40 comprises a power source 41, a drive block 42 and an elongated drive pin 43, the drive pin 43 extending longitudinally between a proximal end 44 and a distal end 45 through an aperture 50 in the wing base 20, the proximal end 44 of the drive pin 43 is connected to the drive block 42 and the distal end 45 extends
• the wing blade 30 may be folded towards the circumferential wall 2 of the projectile 1 in the folded state and extend in a perpendicular direction D from a centre axis A of the projectile 1 in the deployed state.
• the wing base 20 may extend longitudinally essentially in parallel with the centre axis A of the projectile 1.
• the drive block 42 and/or the drive pin 42 may be displaced in a direction perpendicular to the longitudinal extension of the drive pin 43.
• the drive block 42 and/or the drive pin 43 may be displaced in a direction parallel to the pivot axis P.
• the power source 41 may exert force in a direction perpendicular to the longitudinal extension of the drive pin 42.
• the distal end 45 of the drive pin 43 may be displaced correspondingly to the movement of the proximal end 44 of the drive pin 43.
• the fixing arrangement may also comprise guiding pins 4 and corresponding guiding holes in the circumferential wall 2 (shown in figures 3a-3c ).
• the deployment arrangement 40 may also be fastened to the circumferential wall 2 of the projectile 1 by means of the fixing arrangement 70, 71 as previously described herein (shown in figure 4a-4c ).
• the wing blade 30 may be pivoted around the pivot axis P to the deployed state when the power source 41 displaces the drive block 42.
• the power source 41 displaces the drive block 42, which in turn moves the drive pin 43, which in turn relocates the wing blade 30.
• the relocation of the wing blade 30 may be obtained by means of that the distal end 45 of the drive pin 43 is forced to slide along the groove 33 in the wing blade 30, due to that the drive block 42 exert force on the proximal end 44 of the drive pin 43.
• the wing blade 30 rotates to the deployed state and a forceful and reliable deployment may be facilitated while saving valuable space in the projectile 1 and in the wing blade 30.
• cargo 100 carried by the projectile 1 is schematically illustrated.
• Cargo 100 may thus be arranged within the projectile 1, on the inside of the circumferential wall 2.
• the power source 41 and the drive block 42 may be configured to be arranged on the inside of the circumferential wall 2 of the projectile 1.
• the wing arrangement 10 may comprise a locking arrangement 60 for retaining the wing blade 30 in the deployed state.
• the locking arrangement 60 may comprising locking wedges and corresponding recesses, locking pins and corresponding slots or any other suitable locking arrangement holding the wing blade still in a deployed position.
• Such wedges and/or pins and corresponding recess and/or slots may be arranged in association with the wing blade 30 and/or the wing base 20 of the projectile 1.
• the locking arrangement 60 may be activated by means of release of e.g. spring force, pneumatic pressure or hydraulic fluid pressure.
• the locking arrangement may comprise magnets, e.g. a magnetic lock.
• the locking arrangement 60 may comprise at least one spring biased locking element 61 and at least one corresponding locking slot 62.
• the locking element 61 may comprise a locking pin and/or a locking wedge.
• the wing arrangement 10 comprises four locking arrangements 60.
• the locking elements 61 are schematically illustrated as a tapered locking pin.
• the at least one spring biased locking element 61 may at least partly be arranged within the wing blade 30 and the at least one corresponding locking slot 62 may be arranged in the wing base 20.
• the at least one spring biased locking element 61 may be accommodated within the wing blade 30 in the folded state (shown in section A-A in figure 4a ).
• the locking arrangement 60 may be reset from the locked position by retraction of the spring biased locking element 61.
• the wing base 20 and/or the wing blade 30 and/or the locking element 61 may comprise at least one reset opening (not shown in the figures) where a tool may be introduced in order to pull or push the spring biased locking element 61 back when the wing blade 30 is in the deployed state and the locking arrangement 60 is in the locked position, and thereby enable folding of the wing blade 30.
• the wing blade 30 may comprise at least one vent hole (not shown in the figures). The at least one vent hole may counteract formation of vacuum in association with the locking arrangement 60.
• the second stop end 35 of the groove 33 may be configured to retain the wing blade 30 in the deployed state.
• the first stop end 34 and/or the second stop end 35 may be configured as a straight part of the groove 33 extending in parallel with the pivot axis P.
• the wing arrangement 10 may further comprise at least one tapered cover portion 23, 24 configured to be arranged at the first end 21 and/or the second end 22 of the wing base 20.
• the at least one tapered cover portion 23, 24 may be attached to the wing base 20 by at least one spring pin 25, 26 (shown in figures 3a-3c ).
• at least one tapered cover portion 23, 24 may be attached to the wing base 20 by the at least one spring pin 25, 26 and a protruding end of a hinge shaft 27. When the spring pin 25, 26 and the tapered cover portion 23, 24 is removed, the hinge shaft 27 may be accessible, for demounting the wing arrangement for service etc.
• Figures 5a-5c schematically illustrates details of a wing arrangement 10 according to an example of the present disclosure.
• Figures 5a-5c show a side view of the wing arrangement 10 and a cross sectional view along a section indicated in the figures.
• the wing arrangement 10 in figures 5a-5c may be configured as disclosed in figures 2a-2c , 3a-3c and 4a-4c .
• Figure 5a shows the wing arrangement 10 in the folded state
• figure 5b shows the wing arrangement 10 in the intermediate state between the folded state and the deployed state
• figure 5c shows the wing arrangement 10 in the deployed state.
• the deployment arrangement 40 may comprise an actuator arrangement 90.
• the actuator arrangement 90 may actuate, i.e. activate, the power source 41.
• the actuator arrangement 90 may comprise a mechanical linkage, a pull pin, a valve releasing compressed fluid or any other suitable arrangement depending on the application and current configuration of the wing arrangement.
• the actuator arrangement 90 may be triggered by e.g. an electric signal transmitted from a control device or any other suitable way.
• the actuator arrangement 90 comprises a mechanical linkage.
• the mechanical linkage comprises a stop element 93 blocking the displacement of the drive block 42 (shown in figure 5a ).
• Figures 6a-6b schematically illustrates details of a wing arrangement 10 according to an example of the present disclosure.
• the wing arrangement 10 in figures 6a-6b may essentially be configured as disclosed in figures 2a-2c , 3a-3c , 4a-4c and 5a-5c .
• the deployment arrangement 40 in figures 6a-6b comprises another type of power source 41.
• Figure 6a shows a side view of the wing arrangement 10 in the folded state and figure 6b shows a cross sectional view (section G-G in figure 6a ) of the deployment arrangement 40.
• the power source 41 may comprise a compressed gas.
• the power source 41 may comprise a gas pressure arrangement 95.
• the gas pressure arrangement 95 may comprise a gas chamber 96 comprising compressed gas, wherein the gas chamber 96 may be arranged in fluid connection with an expansion chamber 97.
• the expansion chamber 97 may be arranged in the drive block 42.
• the gas pressure arrangement 95 may comprise a plug element 98 for sealing and redirecting the gas flow from the gas chamber 96 towards the expansion chamber 97.
• Figures 7a-7b schematically illustrates details of a wing arrangement 10 according to an example of the present disclosure.
• the wing arrangement 10 in figures 7a-7b may essentially be configured as disclosed in figure 3c .
• the locking arrangement 60 in figures 7a-7b comprises another configuration of locking elements.
• Figure 7a shows a side view of the wing arrangement 10 in the deployed state and a cross sectional view (section H-H) of the locking arrangement 60.
• Figure 7b a cross sectional view of the locking arrangement 60 in the deployed state, wherein the cross section is cut along the pivot axis P and the center axis A of the projectile 1.
• the locking arrangement 60 may comprising two spring biased locking elements 61 and two corresponding locking slots 62.
• the locking elements 61 may be configured as locking wedges.
• the wing base 20 may comprise at least one hinge shaft positioning arrangement 28 (shown in figures 2b-2c , 6a and 7a-7b ).
• the at least one hinge shaft positioning arrangement 28 may comprise a hinge shaft positioning opening arranged in the wing base 20 and a hinge shaft spring pin configured to fixate the hinge shaft 27 in relation to the wing base 20 in the axial direction along the pivot axis P.
• the hinge shaft 27 may comprise a recess or slot mating with the hinge shaft spring pin, thereby holding the hinge shaft 27 in a desired axial position along the pivot axis P.
• Figure 8 schematically illustrates a block diagram of a method for deploying a wing blade 30 for a projectile 1 by using a wing arrangement 10 according to an example.
• the method may relate to the wing arrangement 10 as disclosed in figures 1 , 2a-2c , 3a-3b , 4a-4c , 5a-5c , 6a-6b , and 7a-7b .
• the wing arrangement 10 being configured to be altered between a folded state and a deployed state.
• the activation s110 of the power source 41 may be accomplished by release of spring force, release of compressed gas or any other type of actuating step applicable for the current configuration of the wing arrangement 10. Due to the force exerted by the power source 41 on the drive block 42, the displacing s120 of the drive block 42 may be achieved. When the proximal end 44 of the drive pin 43 is affected by the drive block 42, the drive pin 43 may be displaced correspondingly to the displacement of the drive block 42.
• the distal end 45 of the drive pin 43 extends into the groove 33 in the wing blade 30, the distal end 45 may slide along the groove 33 in the wing blade 30 and force the wing blade 30 to rotate around the pivot axis P from the folded state to the deployed state when the drive block 42 displaces the proximal end 44 of the drive pin 43.

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• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)
• Engineering & Computer Science (AREA)
• General Engineering & Computer Science (AREA)
• Toys (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

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• 2020
  • 2020-08-19 SE SE2000144A patent/SE544987C2/en unknown
• 2021
  • 2021-08-19 PL PL21858710.3T patent/PL4200577T3/pl unknown
  • 2021-08-19 WO PCT/SE2021/050813 patent/WO2022039659A1/en not_active Ceased
  • 2021-08-19 EP EP21858710.3A patent/EP4200577B1/en active Active

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