EP4200577A1

EP4200577A1 - A deployable wing arrangement for a projectile, a projectile comprising such a wing arrangement, an use of such a wing arrangement and a method for deploying a wing blade for a projectile

Info

Publication number: EP4200577A1
Application number: EP21858710.3A
Authority: EP
Inventors: Jan-Peter ROSÉN; Henrik Karlsson
Original assignee: Saab AB
Current assignee: Saab AB
Priority date: 2020-08-19
Filing date: 2021-08-19
Publication date: 2023-06-28
Anticipated expiration: 2041-08-19
Also published as: EP4200577B1; EP4200577C0; WO2022039659A1; EP4200577A4; PL4200577T3; SE544987C2; SE2000144A1

Abstract

The invention relates to a wing arrangement (10) for a projectile (1). The wing arrangement (10) comprising: an elongated wing base (20) configured to be arranged at a circumferential wall (2) of the projectile (1); a wing blade (30) configured to be attached to the wing base (20) along a pivot axis (P) extending along a longitudinal extension of the wing base (20); a deployment arrangement (40) configured to control a pivotal movement of the wing blade (30) around the pivot axis (P) from a folded state to a deployed state. The deployment arrangement (40) comprises a power source (41), a drive block (42) and an elongated drive pin (43). The power source (41) is configured to displace the drive block (42) whereby a distal end (45) of the drive pin (43) slides along a groove (33) in the wing blade (30) so that the wing blade (30) is pivoted around the pivot axis (P) to the deployed state. The invention also relates to a method for deploying a wing blade (30), use of a wing arrangement (10) and a projectile (1).

Description

A DEPLOYABLE WING ARRANGEMENT FOR A PROJECTILE, A PROJECTILE COMPRISING SUCH A WING ARRANGEMENT, AN USE OF SUCH A WING ARRANGEMENT AND A METHOD

FOR DEPLOYING A WING BLADE FOR A PROJECTILE

TECHNICAL FIELD

The present invention relates to a wing arrangement for a projectile. The invention further relates to use of such a wing arrangement for deploying of a wing blade during launch of a projectile and a projectile comprising such a wing arrangement. The invention also relates to a method for deploying a wing blade for a projectile by using a wing arrangement.

BACKGROUND

Projectiles often comprise wings for enhancing flight characteristics. However, during storage and at launch, the projectiles are often accommodated in narrow compartments, such as canisters and launch tubes. In order to fit the projectiles into storage compartments and launchers, 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. There are many different solutions for unfolding of wings comprising deployment actuators of various configurations. However, there may still be a need for a more compact solution enabling efficient deployment of a wing blade.

One known solution for deploying fins for a missile from a stored to a deployed position is disclosed in document US 4,778,127 A. The document discloses a hinged wing and an initiator that powers the deployment of the fins.

SUMMARY OF THE INVENTION

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. The herein mentioned objects are achieved by: a wing arrangement for a projectile, use of such a wing arrangement for deployment of a wing blade during launch of a projectile, a projectile comprising such a wing arrangement, and a method for deploying a wing blade for a projectile by using a wing arrangement, as set out in the appended independent claims.

Hence, according to an aspect of the present disclosure, a wing arrangement for a projectile is provided. The wing arrangement being configured to be altered between a folded state and a deployed state. The 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. 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 is connected to the drive block and the distal end extends into a groove in the wing blade. The power source is configured to displace the drive block whereby the distal end of the drive pin slides along the groove in the wing blade so that the wing blade is pivoted around the pivot axis to the deployed state.

According to another aspect of the present disclosure, a method for deploying a wing blade for a projectile by using a wing arrangement is provided. The wing arrangement being configured to be altered between a folded state and a deployed state. The 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. 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 is connected to the drive block and the distal end extends into a groove in the wing blade. The method comprises the steps of: activating the power source; displacing the drive block by the powers source, whereby the distal end of the drive pin slides along the groove in the wing blade so that the wing blade is pivoted around the pivot axis to the deployed state.

According to another aspect of the present disclosure, a use of a wing arrangement as disclosed herein for deployment of a wing blade during launch of a projectile is provided.

According to another aspect of the present disclosure, 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. Some of the most crucial properties of wing arrangement for deployment of wing blades are their robustness, compactness, weight and effect on aerodynamics. In the present disclosure, the wing arrangement may essentially be arranged in association with the circumferential wall of the projectile body. Thereby, 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. In addition, a smooth and streamlined wing arrangement may be achieved, reducing drag and further improving the aerodynamic properties of the projectile. Even though the wing arrangement as disclosed herein is relatively compact, it is still forceful and reliable, enabling efficient deployment and enhanced stabilising effects. Thus, precise and steady flight characteristics may be achieved.

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. By altering the dimensions of the wing arrangement and the force of the power source, 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.

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. 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.

By using a wing arrangement for deployment of a wing blade during launch of a projectile, a quick, reliable and effective deployment at launch may be accomplished. Consequently, the stabilising effects during launch and flight of the projectile may increase. Thus, by means of the present disclosure, an advantageous projectile with improved flight characteristics may be achieved.

Further objects, advantages and novel features of the present invention will become apparent to one skilled in the art from the following details, and also by putting the invention into practice. Whereas the invention is described below, it should be noted that it is not restricted to the specific details described. Specialists having access to the teachings herein will recognise further applications, modifications and incorporations within other fields, which are within the scope of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

For fuller understanding of the present invention and further objects and advantages of it, the detailed description set out below should be read together with the accompanying drawings, in which the same reference notations denote similar items in the various drawings, and in which:

Figure 1 schematically illustrates a projectile according to an example; Figures 2a-2c, schematically illustrate a wing arrangement according to an example;

Figures 3a-3c, schematically illustrate details of a wing arrangement according to an example;

Figures 4a-4c, schematically illustrate details of a wing arrangement according to an example;

Figures 5a-5c, schematically illustrate details of a wing arrangement according to an example;

Figures 6a-6b schematically illustrate details of a wing arrangement according to an example;

Figures 7a-7b schematically illustrate details of a wing arrangement according to an example; and

Figure 8 schematically illustrates a block diagram of method steps according to examples.

DETAILED DESCRIPTION

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.

According to an aspect of the present disclosure, a wing arrangement for a projectile is provided. The wing arrangement being configured to be altered between a folded state and a deployed state. The 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, 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 is connected to the drive block and the distal end extends into a groove in the wing blade, the power source is configured to displace the drive block whereby the distal end of the drive pin slides along the groove in the wing blade so that the wing blade is pivoted around the pivot axis to the deployed state.

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. 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. According to specific examples, 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. According to specific examples, 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. According to examples, 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. Thus, the wing arrangement as disclosed herein may be configured for relatively large and forceful projectiles. However, the wing arrangement as disclosed herein may be scaled down as well as scaled up depending on the current application.

According to an example, the wing arrangement may be configured for a projectile, which is configured to be launched by a weapon. The weapon may comprise a missile launcher, a grenade launcher or any other suitable weapon. The projectile may be configured to be launched from a weapons platform, such as land-based launchers, aircrafts and/or ships.

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.

According to an example, 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. According to an example, 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. According to an example, the wing arrangement may comprise a fixing arrangement for fastening the wing base to the circumferential wall. According to an example, 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. By the use of floating anchor nuts, the positioning tolerances may be increased. This may in turn facilitate the manufacturing and assembly of the wing arrangement. According to an example, the fixing arrangement may also comprise guiding pins and corresponding guiding holes in the circumferential wall. By means of the guiding pins and the corresponding guiding holes, it may be ensured that the wing base is mounted at a correct angle in relation to the centre axis of the projectile, i.e. that the wing base is mounted in an upright position in the deployed state, perpendicular to the centre axis of the projectile. Thus, the guide pins and the corresponding guiding holes may be manufactured with relatively tight tolerances, in order to reassure proper assembly of the wing arrangement. 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 hinge mechanism may comprise at least one hinge shaft and at least one corresponding hinge shaft socket. Thus, the at least one hinge shaft socket may accommodate the hinge shaft. The at least one hinge shaft socket may be arranged in the wing blade and the wing base. The hinge mechanism may be configured as a barrel hinge, butt hinge, ball bearing hinge or any other suitable type of hinge.

By means of the deployment arrangement controlling the pivotal movement of the wing blade around the pivot axis from the folded state to the deployed state, a rigid and reliable deployment of the wing blade may be achieved. According to an example, the deployment arrangement may be fastened to the circumferential wall of the projectile by means of the fixing arrangement as previously described herein. By using the same fixing arrangement for fastening both the wing base and the deployment arrangement, a more time- and cost effective manufacturing and assembly of the wing arrangement may be achieved. In addition, the number of holes through the circumferential wall may be reduced. This is favourable since numerous holes in the circumferential wall may decrease the strength and robustness of the projectile.

According to an example, the power source may comprise mechanical or electric power, such as spring force or an electric motor. Alternatively, the power source may comprise hydraulic or pneumatic power. This means that the power source may e.g. comprise pressurized fluid, such as a liquid or a gas. Another option may be that the power source may comprise explosives. According to a specific example, the power source may comprise a spring element. The spring element may comprise a pretensioned spring element. The spring element may for example comprise a compression spring or an extension spring. According to an example, the compression spring, or the extension spring, may be arranged to encircle at least a part of the drive block. Thereby, a compact deployment arrangement may be achieved.

According to another example, the power source may comprise a compressed gas. Thus, according to a specific example, the power source may comprise a gas pressure arrangement. The gas pressure arrangement may comprise a gas chamber comprising compressed gas, wherein the gas chamber may be arranged in fluid connection with an expansion chamber. The expansion chamber may be arranged in the drive block. When the compressed gas in the gas chamber is released, the gas may expand into the expansion chamber and displace the drive block. According to a specific example, the gas chamber may comprise compressed gas wherein the release of the compressed gas may be initiated by a release mechanism controlled by e.g. a control device. Such a release mechanism my thus be referred to as an actuator arrangement. According to another example, a combustion in the gas chamber may generate the gas, which in turn may exert pressure on the drive block. According to an example, the gas pressure arrangement may comprise a plug element for sealing and redirecting the gas flow from the gas chamber towards the expansion chamber.

The force of the power source may be affected by the gas pressure and the geometrical configuration of the expansion chamber. For example, the area differential of the drive block on different sides of the expansion chamber may affect the power exerted on the drive block. Thus, 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.

According to an example, the gas chamber may supply gas to multiple wing arrangements. This means that one gas chamber may be in fluid connection to multiple expansion chambers arranged in different wing arrangements. Such a configuration may be more cost effective and assures that all the wing arrangements connected to the gas chamber may be altered from the folded state to the deployed state simultaneously. Alternatively, each wing arrangement may comprise their own separate gas chamber.

According to examples, the drive block may be configured as an elongated drive block, wherein the extension of elongated drive block may be arranged essentially in parallel with the pivot axis. Thereby, a more compact wing arrangement may be achieved which saves valuable space within the wing blade as well as inside of the projectile. This may in turn facilitate disassembly of the circumferential wall without requiring removal of the wing arrangement.

According to an example, the drive pin may be longitudinally arranged in a direction essentially perpendicular to the direction of the force exerted by the power source. Thus, the power source may exert force in a direction perpendicular to the longitudinal extension of the drive pin. This means that the drive pin may be arranged perpendicular to the longitudinal extension of the drive block. According to an example, the drive block may be displaced by the powers source in a direction parallel to the pivot axis for obtaining the deployed state. According to an example, 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.

Since the drive pin extends longitudinally between a proximal end and a distal end through an aperture in the wing base, the deployment arrangement may at least partly be accommodated within the wing base. Thus, the aperture may be a throughgoing aperture, i.e. a through hole. The aperture may extend essentially perpendicular to the pivot axis. This is favourable since such a configuration saves valuable space inside the projectile as well as inside the wing blade, while enabling a smooth and aerodynamic outer surface of the wing arrangement.

By means of the configuration of the drive pin, where the proximal end of the drive pin may be connected to the drive block and the distal end extends into the groove in the wing blade, the wing blade may be pivoted around the pivot axis to the deployed state when the power source displaces the drive block. This means that 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. Hence, 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.

Thus, by means of the 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.

For transportation and storage, the wing arrangement for the projectile may be arranged in the folded state, in order to save space and protect the wing blades from being damaged prior to launch. At launch, the power source may be activated 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. Due to the force exerted by the power source on the drive block, the drive block may be displaced. The proximal end of the drive block may be affected by the drive block and the drive pin may thus be displaced correspondingly to the displacement of the drive block. The displacement of the drive block and the drive pin may thus be a joint movement. The drive block and/or the drive pin may be displaced in a direction perpendicular to the longitudinal extension of the drive pin. The drive block and/or the drive pin may be displaced in a direction parallel to the pivot axis. The drive pin may be a rigid component. Consequently, the distal end of the drive pin may be displaced correspondingly to the movement of the proximal end. Since the distal end of the drive pin extends into the groove in the wing blade, the distal end may slide along the groove in the wing blade and force the wing blade to rotate around the pivot axis from the folded state to the deployed state when the drive block displaces the proximal end of the drive pin. The wing blade in the deployed state may provide favourable stabilising effects and facilitate a steady flight, which in turn may increase the target accuracy.

According to an example, the deployment arrangement may comprise an actuator arrangement. The actuator arrangement may actuate the power source. According to examples, the actuator arrangement 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 may be triggered by e.g. an electric signal transmitted from a control device or any other suitable way.

According to an example, the power source and the drive block are configured to be arranged on the inside of the circumferential wall of the projectile. By means of arranging the power source and the drive block on the inside of the circumferential wall of the projectile, a larger and more powerful power source may be applied compared to the option of arranging the power source in a more limited space, such as inside the wing blade. Thus, a more potent deployment may be facilitated, which increase the possibilities of upscaling the dimensions of the projectile and/or the wing blade.

According to an example, the wing arrangement may further comprise a locking arrangement for retaining the wing blade in the deployed state. In certain cases, the engagement of the distal end of the drive pin in the groove in the wing blade and the remaining power exerted by the power source, such as e.g. remaining spring force, may not be sufficient to hold the wing blade steady in a deployed state, when exposed to air resistance and vibrations during flight. A locking arrangement may then be useful for maintaining the wing blade in the deployed state. The locking arrangement may also increase the stability of the wing blades, compared to holding the wing blade in the deployed state merely by the drive pin. This may in turn further increase the stabilising effect of the projectile in motion. According to examples, the locking arrangement 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 and/or the wing base of the projectile. After the projectile has been launched and the wing blade has been unfolded to the deployed state by means of the power source, the locking arrangement may be activated by means of release of e.g. spring force, pneumatic pressure or hydraulic fluid pressure. Alternatively, the locking arrangement may comprise magnets, e.g. a magnetic lock.

According to an example, the locking arrangement may be arranged inside the wing base and the wing blade. This means that the locking arrangement may be accommodated within the wing base and the wing blade. Thereby, a smooth and streamlined outer surface of the wing arrangement may be obtained.

Since the deployment arrangement may essentially be arranged in the wing base and on the inside of the circumferential wall, there may be sufficient space in the wing blade for accommodating more than one locking arrangement. Thus, according to an example, the wing arrangement may comprise multiple locking arrangement arranged in the wing base and the wing blade. The multiple locking arrangement may be arranged along the longitudinal extension of the wing base. Thereby the locking force may be evenly distributed along the wing blade, and deflection of the deployed wing blade may be reduced. The number of locking arrangements may depend on the current configuration and application of the wing arrangement.

According to an example, the locking arrangement may comprise at least one spring biased locking element and at least one corresponding locking slot. According to examples, the locking element may comprise a locking pin and/or a locking wedge. According to an example, the locking element may be shaped as a circular cylinder, a rectangular pin or any other suitable shape. According to an example, the locking element may be a tapered locking element. According to examples, the locking element may be wedge shaped or cone shaped. Thus, the at least one spring biased locking element and the at least one corresponding locking slot may have a conical shape.

According to an example, the at least one spring biased locking element is at least partly arranged within the wing blade and the at least one corresponding locking slot is arranged in the wing base. The at least one spring biased locking element may be accommodated within the wing blade in the folded state. By means of arranging the at least one locking element and the at least one corresponding locking slot in the wing shaft and wing blade, a compact and reliable solution for retaining the wing blade in the deployed state may be achieved.

The at least one spring biased locking element may be aligned with the corresponding locking slot in the deployed state. The at least one spring biased locking element may thus automatically flip into a locking position, when the wing blade reaches a deployed state. According to an example, the at least one spring biased locking element may be spring biased in a direction perpendicular to the pivot axis. Thus, a reliable and compact locking solution may be achieved, which do occupy valuable space within the projectile.

According to an example, the locking arrangement may be reset from the locked position by retraction of the spring biased locking element. According to an example, the wing base and/or the wing blade and/or the locking element may comprise at least one reset opening where a tool may be introduced in order to pull or push the spring biased locking element back when the wing blade is in the deployed state and the locking arrangement is in the locked position, and thereby enable folding of the wing blade. According to an example, the at least one reset opening may also act as a drainage hole. According to an example, the wing blade may comprise at least one vent hole. The at least one vent hole may counteract formation of vacuum in association with the locking arrangement. Vacuum in connection with the locking arrangement may negatively affect the movement of the spring biased locking element into the locked position.

According to an example, the wing base and the wing blade comprise mating surfaces abutting each other in the deployed state, wherein the mating surfaces extend along the longitudinal extension of the wing base. The mating surfaces abutting each other in the deployed state may work as an end stop when the wing blade reaches the deployed position. Dynamic load may thus be transferred from the rotating wing blade to the fixed wing base when the wing blade reaches the deployed position. The mating surfaces may also increase the stiffness of the wing blade in the deployed position and reduce the deflection of the wing blade. In addition, such a configuration may increase the aerodynamic properties of the wing arrangement since the intersection between the wing base and wing blade may be smooth and streamlined along the mating surfaces.

According to an example, the wing base may comprise a curved surface extending along the longitudinal extension of the wing base allowing the pivotal movement of the wing blade around the pivot axis. According to an example, the curved surface of the wing base may be arranged along an edge arranged adjacent to the mating surface of the wing base as previously described herein. Due to curved surface, the clearance between the wing blade and the wing base may be reduced, while enabling pivotal movement of the wing blade around the pivot axis. Thus, the smoothness of the intersection between the wing blade and the wing base may increase which is favourable in an aerodynamic point of view. In addition, in the case of that the wing arrangement comprises a spring biased locking element, the spring biased locking element may follow the curved surface during deployment. Thus, according to an example, the spring biased locking element abuts the curved surface in an intermediate state between a folded state and a deployed state. Thereby, a smooth and controlled locking motion may be achieved.

According to an example, the groove in the wing blade is at least partly configured as a helical groove. According to an example, the groove in the wing blade has at least partly a spiral shape. This means that the groove extends both in the direction of the longitudinal extension of the wing base and at least partly around the pivot axis. Due to the configuration of the groove in the wing blade, displacement of the drive block in a direction parallel to the pivot axis may be converted into rotational movement of the wing blade around the pivot axis via the drive pin. Thus, efficient transmission of deployment force may be achieved, while increasing the compactness of the wing arrangement. According to a specific example, the groove in the wing blade is a helical groove.

According to an example, 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. According to an example, the second stop end of the groove may be configured to retain the wing blade in the deployed state. According to an example, 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. Thereby, an efficient locking effect may be achieved holding the wing arrangement in the folded and/or the deployed state depending on the current state of the wing arrangement.

According to an example, the wing arrangement further comprises at least one tapered cover portion configured to be arranged at the first end and/or the second end of the wing base. By means of the tapered cover portion, aerodynamic properties of the wing arrangement may be improved. The tapered cover portion may for example cover the access to a mechanical bearing such as the hinge shaft of a hinge mechanism. According to an example, the at least one tapered cover portion may be attached to the wing base by at least one spring pin. According to an example, at least one tapered cover portion may be attached to the wing base by the at least one spring pin and a protruding end of a hinge shaft. When the spring pin and the tapered cover portion is removed, the hinge shaft may be accessible, for demounting the wing arrangement for service etc.

According to an example, the wing base may comprise at least one hinge shaft positioning arrangement. The at least one hinge shaft positioning arrangement may comprise a hinge shaft positioning opening arranged in the wing base and a hinge shaft spring pin configured to fixate the hinge shaft in relation to the wing base in an axial direction of the hinge shaft along the pivot axis. According to an example, the hinge shaft may comprise a recess or slot mating with the hinge shaft spring pin, thereby holding the hinge shaft in a desired axial position along the pivot axis. Due to the hinge shaft positioning arrangement, the hinge shaft may not be unintentionally displaced along the pivot axis, thereby ensuring that the hinge shaft may not block or obstruct the locking motion of the spring biased locking element.

According to an example, the wing arrangement comprises elastomeric seals. The elastomeric seals may according to an example be arranged between the deployment arrangement and the circumferential walls. The elastomeric seals may thus provide an electric seal off, which prevents interference and/or damages of electrical components that may arise due to e.g. lightning strikes.

According to an aspect of the disclosure, a method for deploying a wing blade for a projectile by using a wing arrangement is provided. The wing arrangement being configured to be altered between a folded state and a deployed state. The 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. 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 is connected to the drive block and the distal end extends into a groove in the wing blade. The method comprises the steps of: activating the power source; displacing the drive block by the powers source, whereby the distal end of the drive pin slides along the groove in the wing blade so that the wing blade is pivoted around the pivot axis to the deployed state.

According to an example, the wing arrangement may be configured as previously described herein. Thus, 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 step of activating the power source 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. Due to the force exerted by the power source on the drive block, the step of displacing the drive block may be achieved. When the proximal end of the drive pin is affected by the drive block, the drive pin may be displaced correspondingly to the displacement of the drive block. The displacement of the drive block and the drive pin may thus be a joint movement. The drive block and/or the drive pin may be displaced in a direction perpendicular to the longitudinal extension of the drive pin. The drive block and/or the drive pin may be displaced in a direction parallel to the pivot axis. Thus, the power source may exert force in a direction perpendicular to the longitudinal extension of the drive pin. Since the drive pin may be a rigid component, the distal end of the drive pin may be displaced correspondingly to the movement of the proximal end of the drive pin. The distal end of the drive pin extends into the groove in the wing blade, and the distal end may thus slide along the groove in the wing blade and force the wing blade to rotate around the pivot axis from the folded state to the deployed state when the drive block displaces the proximal end of the drive pin. The wing blade in the deployed state may provide favourable stabilising effects and facilitate a steady flight.

According to an example, the deployment arrangement may comprise an actuator arrangement. Thus, according to a specific example, the activating step may comprise activating the power source by the actuator arrangement. According to examples, the actuator arrangement 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 may be triggered by e.g. an electric signal transmitted from a control device or any other suitable way. In operation, the activation of the power source may be initiated at launch.

By means of the method for deploying a wing blade for a projectile by using a wing arrangement, an advantageous, forceful and reliable deployment of a folded wing blade may be achieved, which in turn may increase the stabilising effects and thereby increase the target accuracy.

According to an aspect of the present disclosure, use of a wing arrangement for deployment of a wing blade during launch of a projectile is provided. By using a wing arrangement for deployment of a wing blade during launch of a projectile, a quick, reliable and effective deployment may be accomplished. Consequently, the stabilising effects during launch and flight of the projectile may increase.

According to an aspect of the present disclosure, a projectile comprising at least one wing arrangement is provided. According to an example, the projectile may comprise any projectile with deployable wings, such as a missile or a grenade. Thereby, a projectile with improved flight characteristics may be achieved.

According to an example, the projectile may comprise at least four wing arrangements. According to an example, the projectile may comprise four wing arrangements, wherein the wing blades may be arranged in a cross configuration or a plus configuration in the deployed state.

According to example, the power source and the drive block may be arranged on the inside of the circumferential wall of the projectile. By arranging the power source and the drive block 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. Thus, 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. According to an example, the wing arrangement may be arranged in association with a fixed wing blade and/or a steering wing blade. Thus, this means that the wing arrangement may be arranged in connection to a fixed wing blade and/or a steering wing blade.

The present disclosure will now be further illustrated with reference to the appended figures, wherein for the sake of clarity and understanding of the disclosure some details of no importance are deleted from the figures. Moreover, the figures shall not be considered drawn to scale as some features may be exaggerated in order to more clearly illustrate the invention.

Figure 1 schematically illustrates a projectile 1 comprising at least one wing arrangement 10 according to an example of the present disclosure. The wing arrangement 10 may be used for deployment of a wing blade 30 during launch of the projectile 1 . The wing arrangements 10 may be configured to be altered between a folded state and a deployed state. In figures 1 , the wing arrangements 10 are shown in the deployed state. The wing arrangement 10 will be further described in relation to figures 2a-2c, 3a-3c, 4a-4c, 5a-5c, 6a-6b and 7a-7b.

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, and 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 into a groove 33 in the wing blade 30, the power source 41 is configured to displace the drive block 42 whereby the distal end 45 of the drive pin 43 slides along the groove 33 in the wing blade 30 so that the wing blade 30 is pivoted around the pivot axis P to the deployed state.

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 .

For transportation and storage, the wing arrangement 10 for the projectile 1 may be arranged in the folded state. At launch, the power source 41 may be activated 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 displacement of the drive block 42 and the drive pin 43 may thus be a joint movement. 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. Thus, 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. Since 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.

According to an example, the wing base 20 may be fixedly arranged to the circumferential wall 2 of the projectile 1 . The wing base 20 may be fixedly arranged to the circumferential wall 2 of the projectile 1 by means of screws, bolts, rivets or any other suitable fastening device. According to an example, the wing arrangement may comprise a fixing arrangement 70, 71 for fastening the wing base 20 to the circumferential wall 2. According to an example, the fixing arrangement 70, 71 may comprises fixing fasteners 71 and a fixing plate 70 with holes. The fixing plate 70 may be rigidly connected to the wing base 20. The fixing arrangement may further comprise floating anchor nuts. According to an example, 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).

Figures 3a-3c schematically illustrates details of a wing arrangement 10 according to an example of the present disclosure. Figures 3a~3c show a cross sectional view of the wing arrangement 10, wherein the cross section is cut along the pivot axis P and the center axis A of the projectile 1 . The wing arrangement 10 in figures 3a-3c may be configured as disclosed in figures 2a-2c. Figure 3a shows the wing arrangement 10 in the folded state, figure 3b shows the wing arrangement 10 in the intermediate state between the folded state and the deployed state, and figure 3c shows the wing arrangement 10 in the deployed state.

The elongated wing base 20 may be configured to follow an outline of the circumferential wall 2 of the projectile 1 along the longitudinal extension of the wing base 20 between the first end 21 and the second end 22. The wing blade 30 may be configured to be attached to the wing base 20 along the pivot axis P by means of at least one mechanical bearing. According to an example, the mechanical bearing may comprise a hinge mechanism. According to the example shown in figures 3a-3c, the hinge mechanism may comprising at least one hinge shaft 27 and at least one corresponding hinge shaft socket 29. Thus, the at least one hinge shaft socket 29 may accommodate the hinge shaft 27. The at least one hinge shaft socket 29 may be arranged in the wing blade 30 and the wing base 20.

As schematically illustrated in the example shown in figures 2a-2c and 3a-3b, the power source 41 may comprise a spring element 91 . The spring element 91 may comprise a pretensioned spring element. The spring element 91 may for example comprise a compression spring or an extension spring. According to an example, the compression spring, or the extension spring, may be arranged to encircle at least a part of the drive block 42. According to an example, the drive block 42 may be configured as an elongated drive block 42, wherein the extension of elongated drive block 42 may be arranged essentially in parallel with the pivot axis P.

The drive pin 43 may be longitudinally arranged in a direction essentially perpendicular to the direction of the force exerted by the power source 41 . Thus, the power source 41 may exert force in a direction perpendicular to the longitudinal extension of the drive pin 42. Thus, the drive pin 43 may be arranged perpendicular to the longitudinal extension of the drive block 42. The drive block 42 may be displaced by the powers source 41 in a direction parallel to the pivot axis P for obtaining the deployed state. The pivot axis P may be arranged essentially in parallel with the centre axis A of the projectile 1 . Alternatively, the pivot axis P may be arranged at an angle relative the centre axis A of the projectile 1 .

Since the drive pin 43 extends longitudinally between a proximal end 44 and a distal end 45 through the aperture 50 in the wing base 20, the deployment arrangement 40 may at least partly be accommodated within the wing base. Thus, the aperture 50 may be a throughgoing aperture, i.e. a through hole. The aperture 50 may extend essentially perpendicular to the pivot axis P.

By means of the configuration of the drive pin 43, where the proximal end 44 of the drive pin 43 may be connected to the drive block 42 and the distal end 45 extends into the groove 33 in the wing blade 30, 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. This means that 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. Hence, 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.

In figure 3-3c, 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. As shown in figures 3a-3c, 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. According to examples, 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 . After the projectile has been launched and the wing blade 30 has been unfolded to the deployed state by means of the power source 41 , the locking arrangement 60 may be activated by means of release of e.g. spring force, pneumatic pressure or hydraulic fluid pressure. Alternatively, the locking arrangement may comprise magnets, e.g. a magnetic lock.

According to the example shown in figures 3a-3c, the locking arrangement 60 may be arranged inside the wing base 20 and the wing blade 30. The wing arrangement 60 may comprise multiple locking arrangement 60 arranged in the wing base 20 and the wing blade 30. The multiple locking arrangement 60 may be arranged along the longitudinal extension of the wing base 20. Thereby the locking force may be evenly distributed along the wing blade 30, and deflection of the deployed wing blade 30 may be reduced. The number of locking arrangements 60 may depend on the current configuration and application of the wing arrangement 10.

Figures 4a-4c schematically illustrates details of a wing arrangement 10 according to an example of the present disclosure. Figures 4a-4c show a side view of the wing arrangement 10 and a crass sectional view along a section indicated in the figures. The wing arrangement 10 in figures 4a-4c may be configured as disclosed in figures 2a-2c and 3a-3c. Figure 4a shows the wing arrangement 10 in the folded state, figure 4b shows the wing arrangement 10 in the intermediate state between the folded state and the deployed state, and figure 4c shows the wing arrangement 10 in the deployed state.

As shown in the example shown in figures 3a-3c and 4a-4c, the locking arrangement

60 may comprise at least one spring biased locking element 61 and at least one corresponding locking slot 62. According to examples, the locking element 61 may comprise a locking pin and/or a locking wedge. According to the specific example shown in figures 3a-3c and 4a-4c, the wing arrangement 10 comprises four locking arrangements 60. The locking elements 61 are schematically illustrated as a tapered locking pin. As shown in figure 4a-4c, 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 at least one spring biased locking element 61 may be aligned with the corresponding locking slot 62 in the deployed state (shown in section C-C in figure 4c). The at least one spring biased locking element 61 may thus automatically flip into a locking position, when the wing blade 30 reaches a deployed state. According to an example, the at least one spring biased locking element 61 may be spring biased in a direction perpendicular to the pivot axis P.

According to an example, the locking arrangement 60 may be reset from the locked position by retraction of the spring biased locking element 61 . According to an example, 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. According to an example, 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.

According to an example, the wing base 20 and the wing blade 30 may comprise mating surfaces 80 abutting each other in the deployed state, wherein the mating surfaces 80 extends along the longitudinal extension of the wing base 20. The mating surfaces abutting each other in the deployed state may work as an end stop when the wing blade 30 reaches the deployed position. According to an example, the wing base 20 may comprise a curved surface 81 extending along the longitudinal extension of the wing base 20 allowing the pivotal movement of the wing blade 30 around the pivot axis P. According to an example, the curved surface 81 of the wing base may be arranged along an edge arranged adjacent to the mating surface 80 of the wing base 20 as previously described herein. According to an example, the spring biased locking element 61 may abut the curved surface 81 in the intermediate state between a folded state and a deployed state (shown in figure 4b).

As illustrated in figure 4a-4b, the groove 33 in the wing blade 30 may at least partly be configured as a helical groove. The groove 33 in the wing blade 30 may have at least partly a spiral shape. This means that the groove 33 extends both in the direction of the longitudinal extension of the wing base 20 and at least partly around the pivot axis P. The groove 33 in the wing blade 30 may comprise a first stop end 34 and a second stop end 35, wherein the distal end 45 of the drive pin 43 is arranged in the first stop end 34 in the folded state and in the second stop end 35 in the deployed state, wherein the first stop end 34 of the groove 33 is configured to retaining the wing blade 30 in the folded state. According to an example, the second stop end 35 of the groove 33 may be configured to retain the wing blade 30 in the deployed state. According to an example, 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.

According to an example, 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. According to an example, 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). According to an example, 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, and figure 5c shows the wing arrangement 10 in the deployed state.

According to the example shown in figures 5a-5c, the deployment arrangement 40 may comprise an actuator arrangement 90. The actuator arrangement 90 may actuate, i.e. activate, the power source 41. According to examples, 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. In the example shown in figures 5a-5c, 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. However, 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.

According to the example in figure 6a-6b, the power source 41 may comprise a compressed gas. Thus, according to a specific example, 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. When the compressed gas in the gas chamber 96 is released, the gas may expand into the expansion chamber 97 and displace the drive block 42. The release of the compressed gas in the gas chamber 96 may for example be initiated an actuator arrangement (not shown in the figures) controlled by e.g. a control device. As shown in the example in figure 6b, 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. However, 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 . As shown in figure 7a-7b, 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.

According to an example, 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. For example, 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.

According to an example, the projectile 1 may comprise at least four wing arrangements 10. According to an example, the projectile 1 may comprise four wing arrangements 10, wherein the wing blades 30 may be arranged in a cross configuration or a plus configuration in the deployed state. According to example, the power source 41 and the drive block 42 may be arranged on the inside of the circumferential wall 2 of the projectile 1 .

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 wing arrangement 10 comprising: 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 into a groove 33 in the wing blade 30. The method comprises the steps of: activating s1 10 the power source 41 ; displacing s120 the drive block 42 by the powers source 41 , whereby the distal end 45 of the drive pin 43 slides along the groove 33 in the wing blade 30 so that the wing blade 30 is pivoted around the pivot axis P to the 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. Since 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.

According to an example, the deployment arrangement 40 may comprise an actuator arrangement 90. Thus, according to a specific example, the activating step s110 may comprise activating the power source 41 by the actuator arrangement 90. According to examples, 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 foregoing description of the preferred examples of the present disclosure is provided for illustrative and descriptive purposes. It is not intended to be exhaustive or to restrict the invention to the variants described. Many modifications and variations will obviously be apparent to one skilled in the art. The examples of the present disclosure have been chosen and described in order best to explain the principles of the invention and its practical applications and hence make it possible for specialists to understand the invention for various embodiments and with the various modifications appropriate to the intended use.

Claims

33 Claims

1. A wing arrangement (10) for a projectile (1 ), the wing arrangement (10) being configured to be altered between a folded state and a deployed state, the wing arrangement (10) comprising: 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 a throughgoing aperture (50) in the wing base (20), wherein the throughgoing aperture (50) extends perpendicular to the pivot axis (P) through 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 into a groove (33) in the wing blade (30), the power source (41 ) is configured to displace the drive block (42) whereby the distal end (45) of the drive pin (43) slides along the groove (33) in the wing blade (30) so that the wing blade (30) is pivoted around the pivot axis (P) to the deployed state.

2. The wing arrangement (10) according to claim 1 , wherein the power source (41 ) and the drive block (42) are configured to be arranged on the inside of the circumferential wall (2) of the projectile (1 ).

3. The wing arrangement (10) according to claim 1 or claim 2, wherein the wing arrangement (10) further comprises a locking arrangement (60) for retaining the wing blade (30) in the deployed state. 34

4. The wing arrangement (10) according to claim 3, wherein the locking arrangement (60) comprises at least one spring biased locking element (61 ) and at least one corresponding locking slot (62).

5. The wing arrangement (10) according to any one of the preceding claims, wherein the wing base (20) and the wing blade (30) comprise mating surfaces (80) abutting each other in the deployed state, wherein the mating surfaces (80) extends along the longitudinal extension of the wing base (20).

6. The wing arrangement (10) according to any one of the preceding claims, wherein the wing base (20) comprises a curved surface (81 ) extending along the longitudinal extension of the wing base (20) allowing the pivotal movement of the wing blade (30) around the pivot axis (P).

7. The wing arrangement (10) according to claim 4 and claim 6, wherein the spring biased locking element (61 ) abuts the curved surface (81 ) in an intermediate state between a folded state and a deployed state,

8. The wing arrangement (10) according to any one of the preceding claims, wherein the groove (33) in the wing blade (30) is at least partly configured as a helical groove.

9. The wing arrangement (10) according to any one of the preceding claims, wherein the groove (33) in the wing blade (30) comprises a first stop end (34) and a second stop end (35), wherein the distal end (45) of the drive pin (43) is arranged in the first stop end (34) in the folded state and in the second stop end (35) in the deployed state, wherein the first stop end (34) of the groove (33) is configured to retaining the wing blade (30) in the folded state.

10. The wing arrangement (10) according to any one of the preceding claims, wherein the wing arrangement (10) further comprises 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).

11. A method for deploying a wing blade (30) for a projectile (1 ) by using a wing arrangement (10), the wing arrangement (10) being configured to be altered between a folded state and a deployed state, the wing arrangement (10) comprising: 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 a throughgoing aperture (50) in the wing base (20), wherein the throughgoing aperture (50) extends perpendicular to the pivot axis (P) through 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 into a groove (33) in the wing blade (30); the method comprises the steps of: activating (s110) the power source (41 ); displacing (s120) the drive block (42) by the powers source (41 ), whereby the distal end (45) of the drive pin (43) slides along the groove (33) in the wing blade (30) so that the wing blade (30) is pivoted around the pivot axis (P) to the deployed state.

12. Use of a wing arrangement (10) according to any one of claims 1 -10, for deployment of a wing blade (30) during launch of a projectile (1 ).

13. A projectile (1), characterized in that it comprises at least one wing arrangement (10) according to any one of claims 1-10.

14. The projectile (1) according to claim 13, wherein the power source (41 ) and the drive block (42) are arranged on the inside of the circumferential wall (2) of the projectile (1).