DRONE SILVER AND DRONE WITH IT
The drone wing design with rotating half-wings and opposing deployment directions addresses oscillation issues, enhancing rigidity and control, and reducing drag without electrical energy.
Patent Information
- Application Number
- FR2023009066
- Authority / Receiving Office
- FR · FR
- Patent Type
- Utility models
- Current Assignee / Owner
- Priority Date
- 2023-07-03
- Filing Date
- 2023-08-29
- Publication Date
- 2025-01-10
- Estimated Expiration
- 2033-08-29
AI Technical Summary
Drones launched in a folded configuration experience oscillations due to weak anchoring of wings, leading to reduced lifespan, maneuverability, navigation control, increased drag, and reduced payload capacity.
The drone wing design features two half-wings rotating around parallel axes, deploying in opposite directions with attachment means at their ends to reduce oscillations, enhancing rigidity and control, and deploying without electrical energy.
The solution improves wing rigidity, navigation control, and reduces drag, while maintaining maneuverability and payload capacity without the need for electrical energy.
Smart Images
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Abstract
Description
Title of the invention: DRONE WING AND DRONE COMPRISING IT Technical field of the invention
[0001] The present invention relates to a drone wing and a drone comprising it. It applies, in particular, to drones launched in a folded configuration. State of the art
[0002] Drones launched in a folded configuration, generally from a launch tube, have wings mounted to rotate relative to an axis of rotation. As a result, their anchoring to the fuselage of the drone is small. The oscillations of the wings caused by the airflow are therefore only very little damped by these anchors. In addition, these anchors are subjected to oscillating forces that are detrimental to their lifespan. These oscillations therefore require heavier mechanical parts to the detriment of the drone's payload. These oscillations also limit the navigation control capabilities of these drones, which makes them less maneuverable and reduces the precision of their trajectory. These oscillations also increase the drag of the drone to the detriment of its speed and range. Presentation of the invention
[0003] The wing structure according to the invention comprises, on each side of the fuselage, two half-wing structures mounted in rotation relative to two substantially parallel axes of rotation, these half-wing structures deploying in opposite directions of rotation until they come into contact, preferably at their ends. Means for attaching these ends of the half-wing structures located on the same side of the fuselage to each other reduce the degrees of freedom of movement of the half-wing structures and therefore the oscillations of these half-wing structures. The rigidity of the wing structure is thus improved, as well as the control of air navigation and the drag of the drone.
[0004] The attachment means may comprise a notch formed in one of the half-wings and / or a hook shape at the end of the other of these half-wings.
[0005] Preferably, once fully deployed, the sail is rhomboidal.
[0006] Preferably, two half-wings which deploy on either side of the fuselage are superimposed in the folded configuration and follow a helical movement to reach, in the deployed configuration, symmetrical positions relative to a vertical plane passing through the main axis of the fuselage.
[0007] Preferably, the means of deploying the sail are purely mechanical and do not require any source of electrical energy. Brief description of the figures
[0008] Other advantages, aims and particular characteristics of the invention will emerge from the following non-limiting description of at least one particular embodiment of the device and the substation which are the subject of the present invention, with reference to the appended drawings, in which:
[0009] [Fig. 1] represents, in perspective, a particular embodiment of a wing and a drone which are the objects of the invention, in a folded configuration,
[0010] [Fig.2] represents, in top view, the wing and the drone illustrated in [Fig.l], in the folded configuration,
[0011] [Fig.3] represents, in side view, the wing and the drone illustrated in figures 1 and 2, in the folded configuration,
[0012] [Fig.4] represents, in front view, the wing and the drone illustrated in figures 1 to 3, in the configuration folded in a launch tube,
[0013] [Fig.5] represents, in perspective, the wing and the drone illustrated in figures 1 to 4, in a partially deployed configuration,
[0014] [Fig.6] represents, in top view, the wing and the drone illustrated in [Fig.5], in the partially deployed configuration,
[0015] [Fig.7] represents, in side view, the wing and the drone illustrated in figures 5 and 6, in the partially deployed configuration,
[0016] [Fig.8] represents, in front view, the wing and the drone illustrated in figures 5 to 7, in the partially deployed configuration,
[0017] [Fig.9] represents, in perspective, the wing and the drone illustrated in figures 1 to 8, in a fully deployed configuration,
[0018] [Fig. 10] represents, in top view, the wing and the drone illustrated in [Fig.9], in the fully deployed configuration,
[0019] [Fig. 11] represents, in side view, the wing and the drone illustrated in figures 9 and 10, in the fully deployed configuration,
[0020] [Fig. 12] represents, in front view, the wing and the drone illustrated in figures 9 to 11, in the fully deployed configuration,
[0021] [Fig. 13] represents, in front view, an articulation of two upper half-wings of the drone illustrated in figures 1 to 12, in the folded wing configuration,
[0022] [Fig. 14] represents, in front view, the articulation of the two upper half-wings illustrated in [Fig. 13], in the wing configuration being deployed,
[0023] [Fig. 15] represents, in front view, the articulation of the two upper half-wings illustrated in figures 13 and 14, in the deployed wing configuration,
[0024] [Fig. 16] is an artist's view, in perspective, of an articulation of two lower half-wings, and
[0025] [Fig. 17] is a schematic longitudinal sectional view of the drone illustrated in figures 1 to 16. Description of the embodiments
[0026] The present description is given without limitation, each characteristic of an embodiment being able to be combined with any other characteristic of any other embodiment in an advantageous manner.
[0027] It should be noted from now on that the figures are to scale.
[0028] As understood from reading this description, various concepts The inventive methods may be implemented by one or more methods or devices described below, several examples of which are provided herein. The actions or steps performed in carrying out the method or device may be ordered in any suitable manner. Accordingly, it is possible to construct embodiments in which the actions or steps are performed in a different order than illustrated, which may include performing certain acts simultaneously, even if they are shown as sequential acts in the illustrated embodiments.
[0029] The expression "and / or", as used herein and in the claims, is to be understood to mean "either or both" of the elements so conjoined, i.e., elements which are present conjunctively in some cases and disjunctively in other cases. Multiple elements listed with "and / or" are to be interpreted in the same way, i.e., "one or more" of the elements so conjoined. Other elements may optionally be present, other than the elements specifically identified by the "and / or" clause, whether or not they are related to these specifically identified elements.Thus, by way of non-limiting example, a reference to "A and / or B", when used in conjunction with open language such as "comprising" may refer, in one embodiment, to A only (optionally including elements other than B); in another embodiment, to B only (optionally including elements other than A); in yet another embodiment, to both A and B (optionally including other elements); etc.
[0030] As used herein in the description and claims, "or" is to be understood inclusively.
[0031] As used in this specification and in the claims, the expression "at least one", with reference to a list of one or more elements, is to be understood to mean at least one element selected from one or more elements in the list of elements, but not necessarily including at least one of each element specifically listed in the list of elements and not excluding any combination of elements in the list of elements. This definition also allows for the optional presence of elements other than the elements specifically identified in the list of elements to which the expression "at least one" refers, whether or not related to these specifically identified elements. Thus, by way of non-limiting example, "at least one of A and B" (or, equivalently, "at least one of A or B", or, equivalently, "at least one of A and / or B") may refer, in one embodiment, to at least one, optionally including more than one, A, without B present (and optionally including elements other than B); in another embodiment, to at least one, optionally including more than one, B, without A present (and optionally including elements other than A); in yet another embodiment, to at least one, optionally including more than one, A, and at least one, optionally including more than one, B (and optionally including other elements); etc.
[0032] In the claims, as well as in the description below, all transitional expressions such as "comprising", "including", "carrying", "having", "containing", "involving", "holding", "composed of", and the like, are to be understood as being open, i.e., as meaning including but not limited to. Only the transitional expressions "consisting of" and "consisting essentially of" are to be understood as closed or semi-closed transitional expressions, respectively.
[0033] Throughout the description, the term "top" or "upper" refers to what is at the top when the drone is flying, "bottom" or "lower" refers to what is at the bottom when the drone is flying, "left" refers to what is on the left when looking at the drone from above, towards the front, that is to say from the rear end of its fuselage towards the front end of the fuselage, and "right" refers to what is on the right in this position.
[0034] According to Wikipedia ®, the term "wing" can designate the entire supporting wing of an aerodyne (free wing, delta wing, flying wing), but also a particular element of this wing (right or left wing, upper or lower wing, front or rear wing). To avoid this ambiguity of the term "wing" representing the whole or its parts, in this document, the term "half-wing" (right or left, front or rear) is used, the wing of the drone being made up of a front lower wing and a rear upper wing, each being made up of a right half-wing and a left half-wing.
[0035] The term "main axis" of the fuselage refers to the central axis of the cylinder exscribed from the body of the fuselage. This main axis of the fuselage is referenced 33 in the figures. In the deployed configuration of the wing 20, the drone 18 is symmetrical with respect to a vertical plane passing through the main axis of the fuselage 33, with the exception of the deployment articulations of the wing 20 and the overlap zone of the half-wings. This symmetry is notably visible in [Fig. 12].
[0036] In the particular embodiment of the drone 18 illustrated in the figures, the wing 20 is rhomboidal, when fully deployed. That is, the projections of the main axes of the half-wings onto a plane perpendicular to the main axis of the fuselage and onto a horizontal plane passing through the main axis of the fuselage are diamonds, two half-wings (the front half-wings in this embodiment) are anchored below the fuselage and two half-wings (the rear half-wings, in this embodiment) are anchored above the fuselage. Of course, the present invention is not limited to this rhomboidal wing shape, but concerns all wings in which the ends of half-wings located on the same side of the fuselage can join, for example a wing in a plane forming a diamond or a wing whose projection onto a horizontal plane passing through the main axis of the fuselage is a diamond and whose projection onto a plane perpendicular to the main axis of the fuselage forms a "V".
[0037] It can be seen, in figures 1 to 12, that the wing 20 comprises: - a left upper half-wing 22, - a right upper half-wing 23, - a left lower half-wing 24 and - a right lower half-wing 25.
[0038] The half-wings 22 to 25 are carried by a fuselage 21 provided with a propeller 26, here positioned at the rear of the fuselage 21. In other embodiments, the propeller is positioned at the front of the fuselage or several propellers are carried by the fuselage, for example at the front and rear, or by half-wings. The upper half-wings 22 and 23 are rotatable about a rear axis of rotation 27, substantially vertical: the acute angle between the main axis 33 of the fuselage and the axis 27 is of the order of 80 degrees and oriented towards the rear of the fuselage 21, the upper half-wings 22 and 23 thus describing a conical surface when they are deployed.
[0039] The lower half-wings 24 and 25 are movable in rotation around an axis of forward rotation 28.
[0040] The lower half-wings 24 and 25 are movable in rotation around a front axis of rotation 28, substantially vertical: the acute angle between the main axis 33 of the fuselage and the axis 28 is of the order of 88 degrees and oriented towards the rear of the fuselage 21, the upper half-wings 24 and 25 thus describing a conical surface when they are deployed.
[0041] Thus, the axes of rotation 27 and 28 are substantially parallel. Preferably, these axes of rotation 27 and 28 form, with a straight line which intersects them, for example the main axis 33 of the fuselage 21, angles whose difference is less than or equal to twenty degrees. In the preferred case where the axes of rotation 27 and 28 of the means 40 and 60 for rotating the half-wings 22 to 25 are intersecting, preferably, they form, between them, an angle less than or equal to twenty degrees.
[0042] As can be seen particularly in [Fig.4], in the launch tube 31, the left 22 and right 23 half-wings are superimposed above the fuselage 21, the upper right half-wing 23 being located between the fuselage 21 and the upper left half-wing 22. Similarly, the left 24 and right 25 half-wings are superimposed below the fuselage 21, the lower left half-wing 24 being located between the fuselage 21 and the lower right half-wing 25.
[0043] As illustrated in figures 5 to 8, during deployment of the wing 20, seen from above and as illustrated by the broken arrows in [Fig.6]: - the upper left half-wing 22 rotates counterclockwise around the rear rotation axis 27, - the upper right half-wing 23 rotates clockwise around the rear rotation axis 27, - the lower left half-wing 24 rotates clockwise around the front rotation axis 28 and - the right lower half-wing 25 rotates counterclockwise around the front rotation axis 28.
[0044] Thus, the wing 20 of the drone 18 comprises, on each side of the fuselage 21, two half-wings which deploy in rotational movements around substantially parallel axes, these rotations being in opposite directions, until their ends meet.
[0045] It is also observed, in figures 5 to 8, that the lower half-wings 24 and 25 each carry, at their free end, a notch 29. The notches are in the vertical plane of a winglet 32. Their openings are oriented towards the front of the drone. It is recalled here that the winglet 32 are curves at the wingtips which reduce the drag of the wing 20 and therefore the energy consumption of the drone 18.
[0046] These wingtip fins 32 are, in the folded configuration of the wing 20, folded onto the lower half-wings 24 and 25 and therefore substantially parallel to these half-wings, as illustrated in FIGS. 1 to 4. For this purpose, a hinge 54 at each end of the lower half-wing, 24 or 25, connects this half-wing to a wingtip fin 32. During deployment of the wing 20, a spring mounted on this hinge 54 separates the wingtip fin 32 from the half-wing, up to a vertical orientation illustrated in [Fig. 12].
[0047] The upper half-wings 22 and 23 carry, at their free end, hooks 30 practically in a horizontal plane and whose openings are oriented towards the rear of the drone.
[0048] When deploying the wing 20, the hooks 30 and the notches 29 gradually move closer together.
[0049] As illustrated in Figures 9 to 12, once fully deployed, the half-wings located on the same side of the fuselage 21, join at their free ends. The hooks 30 penetrate into the notches 29 and thus immobilize, relative to each other, the ends of the left half-wings 22 and 24, on the one hand, and the ends of the right half-wings 23 and 25.
[0050] As can be seen in figures 10 and 12, the entire wing forms, in top view and in front view, a rigid diamond which is therefore very little deformable.
[0051] In [Fig. 13], in front view, we observe an articulation 40 of two upper half-wings 22 and 23 of the drone 18, in the folded wing configuration 20.
[0052] The articulation 40 comprises a fixed central shaft 49 on which rings 41 and 42 of the half-wings 23 and 22, respectively, perform helical movements during the deployment or folding of these half-wings. The ring 41 comprises a spar 43 carrying the half-wing 23 and a laterally toothed helical projection 45 on its lower surface. It is noted that the term “spar” designates, throughout the description, both a spar and a false spar. The ring 41 is also provided with a lower housing 47.
[0053] The crown 42 comprises a spar 44 carrying the half-wing 22 and a laterally toothed helical projection 46 on its upper surface. The crown 42 is also provided with an upper housing 48.
[0054] A toothed wheel 50 has teeth corresponding to the teeth of the helical projections 45 and 46.
[0055] In a manner not shown, the crown 41 has a tenon (or lug) connection moving in a helical groove (or groove) with the fixed central shaft 49. According to the variants, the tenon is carried by the fixed central shaft 49 or by the crown 41 and, respectively, the groove is formed in the crown 41 or the fixed central shaft 49. Similarly, the crown 42 has a tenon (or lug) connection moving in a helical groove (or groove) with the fixed central shaft 49. According to the variants, the tenon is carried by the fixed central shaft 49 or by the crown 42 and, respectively, the groove is formed in the crown 42 or the fixed central shaft 49. Of course, the geometries of the helical shapes correspond to each other, that is to say that the same angle of rotation corresponds to the same translation along the axis 27.
[0056] The rotation of the toothed wheel 50, represented by a circular arrow in the clockwise direction in [Fig. 14] for the deployment movement of the wing (and therefore in the opposite direction for the folding movement) synchronizes the movements of the crown 41 in a descending helical movement and of the crown 42 in an ascending helical movement, at the same angular speed.
[0057] At the end of the rotation of the toothed wheel 50, illustrated in [Fig.15], that is to say at the end of the deployment of the wing 20, the shaft of the toothed wheel 50 is housed in the accommodations 47 and 48.
[0058] The articulation 60 for deploying the lower half-wings 24 and 25 is similar at the articulation 40 of the upper half-wings 22 and 23 illustrated in figures 13 to 15.
[0059] As can be seen in Figures 16 and 17, in this articulation 60 there is a fixed central shaft 69 on which rings 61 and 62 of the half-wings 25 and 24, respectively, perform helical movements during the deployment of these half-wings. The ring 61 comprises a spar 63 carrying the half-wing 25. The ring 62 comprises a spar 64 carrying the half-wing 24. A support 65 holds the shaft 69 in position inside the fuselage 21, in its lower part.
[0060] The shaft 69 and the parts that it directly supports are thus inside the fuselage 21, to protect them, in particular during the landing of the drone 18, and to reduce the turbulence generated by the articulation 60. Similarly, the shaft 49 and the crowns 41 and 42 are supported inside the fuselage 21. Unlike the spars 63 and 64, the spars 43 and 44 have vertical offsets 56 and 57 to reduce the turbulence due to the articulation 40.
[0061] In the launch tube 31, the half-wings 24 and 25 are held folded by their support on the vertical walls of the tube 31. To cause the deployment of the half-wings 24 and 25, as soon as the drone has been launched from the launch tube 31, the ends of a helical spring 68 positioned around a fixed axis 66 are held on vertical lugs 67 of the spars 63 and 64. The spring 68 is compressed by the folding of the half-wings 24 and 25. The deployment of the half-wings 24 and 25 is thus very rapid. On the contrary, the upper half-wings 22 and 23 have a delayed or slower deployment such that the notches 29 are already in place when the hooks 30 reach the end of their travel and engage on the notches 29.
[0062] Numerous means for delaying the end of deployment of the upper half-wings 22 and 23 relative to the end of deployment of the lower half-wings 24 and 25 can be put in place. In a first example (not shown), a finger passing through the upper half-wings 22 and 23 holds them in position until a mechanical part actuated by the almost complete deployment of the lower half-wings 24 and 25, spreads this finger and releases the half-wings 22 and 23. In a second example (not shown), a spring for spreading the upper half-wings 22 and 23 has a stiffness substantially lower than the stiffness of the spring 68, and / or an angular travel substantially greater than that of the spring 68.In a third example (not shown), a gear or connecting rod between the joints 40 and 60 delays and / or slows down the deployment of the upper half-wings 22 and 23, relative to that of the lower half-wings 24 and 25.
[0063] When the half-wings are fully deployed, the springs have, for their part, not completed their entire course, that is, they have not reached their position resting. They are therefore still under tension. As for the front half-wings, this residual tension fights against the relative wind. As for the rear half-wings, this residual tension keeps these half-wings well deployed and the locking between the front half-wings and the rear half-wings in support under stress.
[0064] It is noted that the maintenance of this locking can, alternatively or additionally, be ensured by mechanical locking, for example using one or more magnets.
[0065] It is noted that the means, in particular the articulations 40 and 60, for rotating two half-wings, 22 and 24 or 23 and 25 located on the same side of the fuselage 21, are solely mechanical, and therefore do not require any source of electrical energy, as is the case in the drone 18 illustrated in FIGS. 1 to 16. In variants (not shown), at least one electric motor and / or at least one electromechanical actuator are implemented.
[0066] In order for this helical movement kinematics to be carried out smoothly between the right 23 and left 22 half-wings, the half-wing furthest from the fuselage 21, in the folded configuration of the wing, comprises a part of the half-wing closest to the fuselage 21, in this folded configuration. In the embodiment shown in the figures, the upper left half-wing 22 comprises an extension 52 consisting of a part 51 removed from the upper right half-wing 23. For example, this part 52 is what protrudes above a helicoid corresponding to the relative movement of the half-wings 22 and 23. Thus, this part 52 perfectly complements the upper right half-wing 23 to make the wing 20 of the drone 18 symmetrical with respect to the vertical plane passing through the main axis 33 of the fuselage 21.
[0067] For the purposes of the present invention, the “opposite direction” rotations are observed by looking vertically, from above or from below the drone 18.
[0068] Variants
[0069] In the particular embodiment described above, the rotation means 40 and 60 are configured, together with the lengths of the half-wings 22 and 24, on the one hand, and 23 and 25, on the other hand, on the same side of the fuselage 21 so that the contact between these half-wings is made at the free end of these half-wings. In other embodiments (not shown), the half-wings on the same side of the fuselage, i.e. to the right or left of the fuselage, come into contact at a point which is not the end of one of the half-wings or of none of the half-wings. In other words, there is an extension of at least one of the half-wings beyond the attachment means.
[0070] In embodiments (not shown), the attachment means, 29 and 30, do not have a notch or have only one notch on one of the contacting half-wings. For example, the attachment means consist of magnets with opposite poles, or hooks.
[0071] In embodiments (not shown), the means for rotating the half-wings are both above or below the fuselage of the drone.
[0072] In embodiments (not shown), no half-wing includes a wingtip fin.
[0073] In embodiments (not shown), the means for rotating the half-wings are configured to cause the half-wings to follow a pure rotational movement, without translational movement, variable pitch helical movements, or movements formed using cams or connecting rods. Summary of the invention
[0074] The present invention aims to remedy all or part of the drawbacks of the prior art.
[0075] To this end, according to a first aspect, the present invention relates to a drone 18 which comprises a fuselage 21, this fuselage comprising: - means, 40 and 60, for rotating two half-wings, 22 and 24, on the one hand, and 23 and 25 on the other hand, around two axes of rotation, 27 and 28, on each side of the fuselage 21, the rotation means 40 and 60 being configured so that, during deployment of the wing 20, consisting of the four half-wings 22 to 25, on either side of the fuselage 21, the rotations of these half-wings on the same side of the fuselage take place in opposite directions until these half-wings come into contact, and - means of attachment, 29 and 30, between them, of the half-wings on the same side of the fuselage in contact.
[0076] Thus, the means for attaching these ends of the half-wings located on the same side of the fuselage together reduce the degrees of freedom of movement of the half-wings and therefore the oscillations of these half-wings. The rigidity of the wing 20 is thus improved, as well as the control of air navigation and the drag of the drone.
[0077] In embodiments, the rotation means 40 and 60 are configured, together with the lengths of the half-wings 22 and 24, on the one hand, and 23 and 25, on the other hand, on the same side of the fuselage 21 so that the contact between these half-wings takes place at the free end of these half-wings.
[0078] There is therefore no extension of one of the half-wings beyond these attachment means, which eliminates the risks of oscillation of such an extension.
[0079] In embodiments, the attachment means, 29 and 30, comprise at least one notch formed on at least one half-wing 22 to 25.
[0080] The attachment is thus made by penetration of a part of one half-wing into the notch of the other half-wing.
[0081] In embodiments, the attachment means, 29 and 30, comprise, on the same side of the fuselage 21: - for a half-wing, 24 or 25, at least one notch 29 formed in a wingtip fin 32 of this half-wing, and - for the other half-wing 22 or 23, at least one horizontal notch 30.
[0082] The notches of the two half-wings therefore fit into each other, which eliminates any degree of freedom of one half-wing relative to the other.
[0083] In embodiments, the drone 18 comprises, on each side of the fuselage 21, an upper half-wing, 22 or 23, rotated by a rotation means 40 positioned above the fuselage 21 and a lower half-wing, 24 or 25, respectively, rotated by a rotation means 60 positioned below the fuselage 21, the wing 20 being, once fully deployed, rhomboidal.
[0084] The drone thus has the advantages of rhomboidal wings.
[0085] In embodiments, on each side of the fuselage 21, at least one half-wing, 24 or 25, comprises a wingtip fin 32 mounted on a hinge 54 provided with a spring configured to separate this wingtip fin 32 from the half-wing, 24 or 25, which carries it, during the movement of this half-wing, 24 or 25 away from the fuselage 21, during the deployment of the wing 20.
[0086] Thus, the wingtip fin 32 deploys during deployment of the half-wing, 24 or 25, which carries it.
[0087] In embodiments, the means, 40 and 60, for rotating the half-wings, 22 to 25, are configured to cause at least one half-wing to follow a rotational movement combined with a translational movement in a helical movement.
[0088] Thus, once the wing 20 is deployed, it has symmetry with respect to a plane passing through the main axis 33 of the drone 18.
[0089] In embodiments, for two half-wings, 22 and 23, rotated by the same rotation means 40, one of these half-wings, 22, comprises an extension 52 and the other of these half-wings, 23, comprises a recess 51, of the same geometric shape as the extension 52, the extension being configured to, once the wing 20 is deployed, fill this recess 51.
[0090] Thus, during the helical movement of the half-wings, there is no risk of contact between them, but, once deployed, the half-wings complement each other to form a wing symmetrical with respect to a plane passing through the main axis 33 of the fuselage 21.
[0091] In embodiments, the extension 52 and the retraction 51 are determined by the helicoid followed during the relative movement of these half-wings 22 and 23.
[0092] In embodiments, the axes of rotation, 27 and 28, of the means, 40 and 60, for rotating the half-wings, 22 to 25, are intersecting and form, between them, an angle less than or equal to twenty degrees.
[0093] In embodiments, the drone 18 comprises a means for delaying the end of deployment of one half-wing, 22 or 23, relative to the end of deployment of the other half-wing, 24 or 25, respectively, located on the same side of the fuselage 21. The attachment between these half-wings is thus more reliable.
[0094] In embodiments, the means, 40 and 60, for rotating two half-wings, 22 and 24 or 23 and 25, located on the same side of the fuselage 21, are solely mechanical, and therefore do not require any source of electrical energy. The drone can thus remain for a very long time, for example months, or even years, ready for launch in a launch tube, without having to recharge a source of electricity dedicated to the deployment of the wing, or to carry out maintenance on an electrical circuit dedicated to the deployment of the wing.
Claims
Claims
1. Drone (18) which comprises a fuselage (21), characterized in that this fuselage comprises: - means (40, 60) for rotating two half-wings (22, 23, 24, 25) around two axes of rotation (27, 28), on each side of the fuselage, the rotation means being configured so that, during deployment of the wing (20) consisting of the four half-wings on either side of the fuselage, the rotations of these half-wings on the same side of the fuselage take place in opposite directions until these half-wings come into contact, and - means (29, 30) for attaching together half-wings on the same side of the fuselage in contact.
2. Drone (18) according to claim 1, in which the rotation means (40, 60) are configured, together with the lengths of the half-wings (22, 23, 24, 25) on the same side of the fuselage (21) so that the contact between these half-wings takes place at the free end of these half-wings.
3. Drone (18) according to one of claims 1 or 2, in which the attachment means (29, 30) comprise at least one notch formed on at least one half-wing (22, 23, 24, 25).
4. Drone (18) according to one of claims 1 to 3, which comprises, on each side of the fuselage (21), an upper half-wing (22, 23) rotated by a rotation means (40) positioned above the fuselage and a lower half-wing (24, 25) rotated by a rotation means (60) positioned below the fuselage, the wing (20) being, once fully deployed, rhomboidal.
5. Drone (18) according to one of claims 1 to 4, in which, on each side of the fuselage (21), at least one half-wing (24, 25) comprises a wingtip fin (32) mounted on a hinge (54) provided with a spring configured to separate this wingtip fin from the half-wing which carries it during the movement of this half-wing away from the fuselage, during deployment of the wing (20).
6. Drone (18) according to one of claims 1 to 5, in which the means (40, 60) for rotating the half-wings (22, 23, 24, 25) are configured to cause at least one half-wing to follow a rotational movement combined with a translational movement, in a helical movement.
7. Drone (18) according to claim 6, in which for two half-wings (22, 23) rotated by the same rotation means (40), one (22) of these half-wings comprises an extension (52) and the other (23) of these half-wings comprises a recess (51) of the same geometric shape as the extension, the extension being configured to, once the wing (20) is deployed, fill this recess.
8. Drone (18) according to one of claims 1 to 7, in which the axes of rotation (27, 28) of the means (40, 60) for rotating the half-wings (22, 23, 24, 25) are intersecting and form, between them, an angle less than or equal to twenty degrees.
9. Drone (18) according to one of claims 1 to 8, which comprises a means for delaying the end of deployment of one half-wing (22, 23) relative to the end of deployment of the other half-wing (24, 25) located on the same side of the fuselage (21).
10. Drone (18) according to one of claims 1 to 9, in which the means (40, 60) for rotating two half-wings (22 and 24 or 23 and 25) located on the same side of the fuselage (21), are solely mechanical, and therefore do not require any source of electrical energy.