Drone wing assembly and drone equipped therewith

Abstract

The drone (18) is equipped with a fuselage (21), and this fuselage (21) is: - Rotating means (40, 60) for rotating two hemiwings (22, 23, 24, 25) on each side of the fuselage around two axes of rotation, wherein the rotating means (40, 60) are configured such that, during the deployment of a wing assembly (20) consisting of four hemiwings on both sides of the fuselage, the rotation of these hemiwings on the same side of the fuselage is carried out in opposite directions until these hemiwings come into contact. -Means (29, 30) for connecting together when the half-wings on the same side of the fuselage come into contact with each other. It is equipped with. In some embodiments, the rotating means (40, 60) are configured such that, along with the length of the half-wings (22, 23, 24, 25) located on the same side of the fuselage (21), contact between these half-wings occurs at the free ends of these half-wings.

Description

Technical Field

[0001] The present invention relates to a drone wing assembly and a drone equipped with the same. In particular, the present invention is applicable to drones launched in a folded configuration.

Background Art

[0002] Drones that are generally launched from a launch tube in a folded configuration have a wing assembly rotatably attached to a rotation axis. Therefore, the fixing portion of the wing assembly to the body of the drone is small. Accordingly, vibrations of the wing assembly caused by air flow are hardly attenuated by these fixing portions. Further, these fixing portions are exposed to vibration forces, which affects the lifespan of the fixing portions. Therefore, due to these vibrations, heavier mechanical components are required, which affects the payload of the drone. These vibrations also limit the flight control ability of these drones, reduce the operability of the drones, and reduce the accuracy of the drone's trajectory. Also, these vibrations increase drag at the expense of the drone's speed and flight endurance.

Summary of the Invention

[0003] The wing assembly, which is the subject of the present invention, includes two half-wings rotatably attached to each side of the body with respect to a substantially parallel rotation axis, and these half-wings are preferably deployed in opposite rotation directions until they contact at their ends. Means for connecting these ends of the half-wings located on the same side of the body reduces the vibrations of these half-wings by reducing the degrees of freedom of movement of the half-wings. This improves the rigidity of the wing assembly and also improves the control and drag of the drone during aerial flight.

[0004] The connecting means can be composed of 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, the wing assembly is rhomboidal when fully extended.

[0006] Preferably, the two half-wings deployed on each side of the fuselage are superimposed in the folded configuration and, through helical motion, reach a position symmetrical with respect to the plane passing through the main axis of the fuselage in the deployed configuration. Preferably, the deployment means for deploying the wing assembly is purely mechanical and therefore does not require any electrical energy source.

[0007] The present invention aims to improve all or part of the shortcomings of the prior art. To this end, the present invention conceives a drone having a fuselage, which is: - A rotating means for rotating two hemiwings on each side of the fuselage around two axes of rotation, wherein the rotating means is configured such that, during the deployment of a wing assembly consisting of four hemiwings on both sides of the fuselage, the rotation of these hemiwings on the same side of the fuselage is carried out in opposite directions until these hemiwings come into contact; -Means for connecting together the hemiwings on the same side of the fuselage when they come into contact It is equipped with.

[0008] Thus, the means for connecting these ends of hemiwings located on the same side of the fuselage reduces vibration of these hemiwings by reducing the degrees of freedom of motion of the hemiwings. This improves the rigidity of the wing assembly 20 and also improves the control and drag of the drone's aerial flight.

[0009] In some embodiments, the rotating means is configured such that, along with the length of the half-wings on the same side of the fuselage, contact between these half-wings occurs at the free ends of these half-wings.

[0010] Therefore, one half of the wing does not extend beyond these connecting means, thereby eliminating the risk of vibration in such extended portion.

[0011] In some embodiments, the coupling means consists of at least one notch formed on at least one half-wing. Thus, coupling is achieved by a portion of one half-wing entering the notch of the other half-wing.

[0012] In some embodiments, the connecting means is located on the same side of the fuselage: -One half-wing, with at least one notch formed in the wingtip plate of this half-wing; - The other half-wing, at least one horizontal notch and It is composed of.

[0013] Therefore, the notches on the two hemiplanes interlock, completely eliminating the degree of freedom of one hemiplane relative to the other.

[0014] In some embodiments, the drone comprises, on each side of the fuselage, an upper half-wing rotated by a rotating mechanism positioned above the fuselage and a lower half-wing rotated by a rotating mechanism positioned below the fuselage, such that the wing assembly is rhomboid when fully extended.

[0015] Therefore, the drone offers the advantages of a rhomboid wing assembly.

[0016] In some embodiments, on both sides of the fuselage, at least one half-wing is provided with a hinged endplate, the hinge being equipped with a spring configured to separate the endplate from the supporting half-wing as the half-wing moves away from the fuselage. In this way, the endplate is extended during the deployment of the half-wing that supports it.

[0017] In some embodiments, the rotating means for rotating the hemiplane is configured to cause at least one hemiplane to undergo rotational motion combined with translational motion in a helical motion.

[0018] In this way, the wing assembly, when deployed, is symmetrical with respect to a plane passing through the principal axis of the drone.

[0019] In some embodiments, for two hemiplanes rotated by the same rotating means, one of these hemiplanes has an extended portion, and the other hemiplane has a recess having the same geometry as the extended portion, the extended portion being configured to fill the recess when the wing assembly 20 is deployed. This eliminates the risk of the hemiplanes contacting each other during the helical motion of the hemiplanes, but when deployed, the hemiplanes complement each other to form a wing assembly that is symmetrical with respect to a plane passing through the main axis of the fuselage.

[0020] In some embodiments, the elongated portion and the recessed portion are determined by the helical path followed by these hemiwings during their relative motion.

[0021] In some embodiments, the axes of rotation of the rotating means for rotating the half-wing intersect, forming an angle of 20° or less relative to each other.

[0022] In some embodiments, the drone includes means for delaying the completion of the deployment of one hemiwing relative to the completion of the deployment of another hemiwing located on the same side of the fuselage. This ensures a more secure integrated connection between these hemiwings.

[0023] In some embodiments, the rotational means for rotating the two hemiwings located on the same side of the fuselage is purely mechanical and therefore does not require any electrical energy source. Thus, the drone can remain launch-ready in the launch tube for extended periods, such as months or even years, without requiring recharging of the power source used for deploying the wing assemblies or maintenance of the electrical circuits used for deploying the wing assemblies.

[0024] Other advantages, purposes, and specific features of the present invention will become apparent from the following non-limiting description with reference to the drawings included in the accompanying document of at least one specific embodiment of the drone wing assembly and drone that are the subject of the present invention. [Brief explanation of the drawing]

[0025] [Figure 1] Figure 1 shows a perspective view in a folded configuration of a wing assembly and a drone, which are the subject matter of the present invention, in a particular embodiment. [Figure 2] Figure 2 shows a top view in a folded configuration of the wing assembly and the drone shown in Figure 1. [Figure 3] Figure 3 shows a side view in a folded configuration of the wing assembly and the drone shown in Figures 1 and 2. [Figure 4] Figure 4 shows a front view in a folded configuration within a launch tube of the wing assembly and the drone shown in Figures 1 to 3. [Figure 5] Figure 5 shows a perspective view in a partially deployed configuration of the wing assembly and the drone shown in Figures 1 to 4. [Figure 6] Figure 6 shows a top view in a partially deployed configuration of the wing assembly and the drone shown in Figure 5. [Figure 7] Figure 7 shows a side view in a partially deployed configuration of the wing assembly and the drone shown in Figures 5 and 6. [Figure 8] Figure 8 shows a front view in a partially deployed configuration of the wing assembly and the drone shown in Figures 5 to 7. [Figure 9] Figure 9 shows a perspective view in a fully deployed configuration of the wing assembly and the drone shown in Figures 1 to 8. [Figure 10] Figure 10 shows a top view in a fully deployed configuration of the wing assembly and the drone shown in Figure 9. [Figure 11] Figure 11 shows a side view in a fully deployed configuration of the wing assembly and the drone shown in Figures 9 and 10. [Figure 12] Figure 12 shows a front view in a fully deployed configuration of the wing assembly and the drone shown in Figures 9 to 11. [Figure 13] Figure 13 shows a front view in a folded configuration of the wing assembly of the joints of two upper half-wings of the drone shown in Figures 1 to 12. [Figure 14]Figure 14 shows a front view of the two upper wing joints of the drone shown in Figure 13, in the configuration during deployment of the wing assembly. [Figure 15] Figure 15 shows a front view of the wing assembly in its deployed configuration, with the two upper half-wing joints shown in Figures 13-14. [Figure 16] Figure 16 shows an artistic perspective view of the joints of the two lower hemiwings. [Figure 17] Figure 17 is a schematic longitudinal cross-sectional view of the drone shown in Figures 1-16. [Modes for carrying out the invention]

[0026] This description is non-limiting, and each feature of one embodiment can be advantageously combined with any other feature of any other embodiment.

[0027] Please note that the scale of the drawings is not accurate.

[0028] As can be understood from reading this description, one or more methods or devices described below can implement multiple different inventive concepts, some of which are given hereby. The actions or steps performed within the framework of the implementation of the method or device can be ordered in any suitable manner. As a result, it is possible to construct embodiments in which these actions or steps are performed in an order different from the order shown herein, including performing some actions simultaneously, even if they are presented as actions performed sequentially in the embodiments shown herein.

[0029] When used in this text, the expression "and / or" shall be understood to mean "one or other, or both" of the elements connected by the expression, i.e., elements that may be consecutive or separate. Similarly, multiple elements listed using "and / or" shall be interpreted as "one or more" of the elements connected by the expression. Other elements may exist, regardless of whether they are associated with the elements specifically identified by the "and / or" phrase. Therefore, as a non-restrictive example, when the expression "A and / or B" is used with non-restrictive phrases such as "comprising," it may refer to A only (but possibly including elements other than B); B only (but possibly including elements other than A); A and B (but possibly including other elements); etc. When used in this text, the expression "or" shall be understood in an inclusive sense.

[0030] When used in this text, the expression "at least one" in relation to a list of one or more elements shall 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, nor excluding any combination of multiple elements in the list of elements. This definition means that elements other than those specifically identified may be present, regardless of whether the expression "at least one" is associated with the elements specifically identified in the list of elements to which it pertains. Therefore, as a non-restrictive example, "at least one of A and B" (or, as a synonym, "at least one of A or B," or as a synonym, "at least one of A and / or B") may mean, in one embodiment, that there is at least one, possibly two or more A's and no B (but that other elements may be included); in another embodiment, that there is at least one, possibly two or more B's and no A (but that other elements may be included); in yet another embodiment, that there is at least one, possibly two or more A's and at least one, possibly two or more B's (but that other elements may be included); and so on.

[0031] In this document, all transitional expressions such as "comprising," "including," "bearing," "having," "containing," "involving," "made of," and "formed of" shall be understood as non-restrictive, meaning "including but not limited to." Only the transitional expressions "consisting of" and "consisting essentially of" shall be understood as restrictive or semi-restrictive, respectively. Throughout this explanation, the terms "top" or "upper" refer to the upper part of the drone during flight, "bottom" or "lower" refer to the lower part of the drone during flight, "left" refers to the left side when viewing the drone from above and looking forward, i.e., from the rear end of the fuselage to the front end of the fuselage, and "right" refers to the right side in this orientation.

[0032] According to Wikipedia, the term "wing" can refer not only to the entire wing assembly that generates lift in a heavy aircraft (free wing (or flexible wing), delta wing, or all-wing), but also to specific elements of this wing assembly (right wing or left wing, upper wing or lower wing, forward wing or rear wing). To avoid this ambiguity of the term "wing" as referring to the whole or a part thereof, this document uses "half-wing" (right or left, forward or rear), and the drone's wing assembly consists of a lower and forward wing assembly and an upper and rear wing assembly, which are composed of a right half-wing and a left half-wing, respectively. The term "main axis" of the fuselage refers to the central axis of the excircling cylinder of the fuselage body. This main axis of the fuselage is represented by 33 in the drawings. In the deployed configuration of the wing assembly 20, the drone 18 is symmetrical with respect to the vertical plane passing through the main axis 33 of the fuselage, except for the deployment joints of the wing assembly 20 and the areas covered by the half-wings. This symmetry can be seen in Figure 12.

[0033] In a particular embodiment of the illustrated drone 18, the wing assembly 20 becomes rhomboid when fully deployed. That is, the projection of the hemiwing principal axes in a plane perpendicular to the fuselage principal axis, and the projection in a horizontal plane passing through the fuselage principal axis, are rhomboid, with two hemiwings (the forward hemiwings in this embodiment) tethered to the underside of the fuselage and two hemiwings (the rear hemiwings in this embodiment) tethered to the upper side of the fuselage. Naturally, the present invention is not limited to such rhomboid wing assembly shapes, but relates to any wing assembly in which the ends of hemiwings located on the same side of the fuselage can be joined together, such as a wing assembly in a plane forming a rhomboid, or a wing assembly in which the projection in a horizontal plane passing through the fuselage principal axis is rhomboid and the projection in a plane perpendicular to the fuselage principal axis is "V" shaped.

[0034] Figures 1-12 show the wing assembly 20: -upper left hemiwing 22; -Upper right hemiwing 23; - Lower left half wing 24; and -Lower right half wing 25 This indicates that it is composed of [something].

[0035] The half-wings 22-25 are supported by a fuselage 21 equipped with a propeller 26, where the propeller 26 is positioned at the rear of the fuselage 21. In other embodiments, one propeller is positioned at the front of the fuselage, or multiple propellers are supported by the fuselage, for example, at the front and rear, or by the half-wings. The upper half-wings 22, 23 can rotate around a rear rotation axis 27, which is approximately vertical, with an acute angle of about 80° between the main shaft 33 of the fuselage and the axis 27, and is facing the rear of the fuselage 21, so that the upper half-wings 22, 23 trace a conical surface when deployed. The lower half-wings 24, 25 can rotate around a front rotation axis 28.

[0036] The lower half wings 24 and 25 can rotate around the forward rotation axis 28, which is approximately vertical, and the acute angle between the main shaft 33 of the fuselage and the axis 28 is about 88°. Since it faces the rear of the fuselage 21, the upper half wings 24 and 25 trace a conical surface while deployed.

[0037] Therefore, the rotation axes 27 and 28 are substantially parallel. Preferably, these rotation axes 27 and 28 form an angle with respect to a straight line intersecting them, for example, the main axis 33 of the fuselage 21, with a difference of 20° or less. In a preferred embodiment in which the rotation axes 27 and 28 of the rotation means 40 and 60 for rotating the half-wings 22 to 25 intersect, they preferably form an angle with respect to each other of 20° or less.

[0038] In particular, as shown in Figure 4, inside the launch tube 31, the left half wing 22 and the right half wing 23 overlap on the upper side of the fuselage 21, with the upper right half wing 23 positioned between the fuselage 21 and the upper left half wing 22. Similarly, the left half wing 24 and the right half wing 25 overlap on the lower side of the fuselage 21, with the lower left half wing 24 positioned between the fuselage 21 and the lower right half wing 25.

[0039] As shown in Figures 5-8, when viewed from above during the deployment of the wing assembly 20, as indicated by the dashed arrow in Figure 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 forward rotation axis 28; - The lower right half-wing 25 rotates counterclockwise around the forward rotation axis 28.

[0040] Accordingly, the wing assembly 20 of the drone 18 comprises two hemiwings on each side of the fuselage 21, which are deployed by rotational motion around substantially parallel axes, with these rotations in opposite directions, and are carried out until the tips of the hemiwings meet.

[0041] Figures 5-8 also show that the lower half-wings 24 and 25 each have notches 29 at their free ends. The notches are located in the vertical plane of the end plate 32. The opening of the notch faces forward of the drone. The end plate 32 is the curved tip of the wing that reduces the energy consumption of the drone 18 by reducing the drag of the wing assembly 20.

[0042] In the folded configuration of the wing assembly 20, these endplates 32 fold onto the lower hemiplanes 24, 25 so that they are substantially parallel to the hemiplanes as shown in Figures 1-4. For this purpose, hinges 54 at each end of the lower hemiplanes 24 or 25 connect the hemiplane to the endplates 32. During the deployment of the wing assembly 20, springs attached to these hinges 54 move the endplates 32 away from the hemiplanes until they are in a vertical orientation as shown in Figure 12. The upper hemiplanes 22, 23 are equipped with hooks 30 at their free ends, which are substantially in the horizontal plane and whose openings face the rear of the drone. During the deployment of the wing assembly 20, the hooks 30 and the notches 29 gradually move closer together.

[0043] As shown in Figures 9-12, when fully deployed, the hemiplanes located on the same side of the fuselage 21 join together at their free ends. The hooks 30 engage with the notches 29, securing the ends of the left hemiplanes 22 and 24 to the ends of the right hemiplanes 23 and 25 relative to each other. As can be seen in Figures 10 and 12, the wing assembly as a whole forms a rhomboid shape in the top and front views, which is highly rigid and cannot be easily deformed.

[0044] Figure 13 shows a front view of the joint 40 of the two upper hemiplanes 22 and 23 of the drone 18 in the folded configuration of the wing assembly 20. The joint 40 includes a fixed central shaft 49 on which the collars 41 and 42 of the hemiplanes 23 and 22 perform a helical motion during the deployment or folding of these hemiplanes. The collar 41 includes a spar 43 that supports the hemiplane 23 and a helical projection 45 on its underside with teeth running laterally. Throughout this description, the term "spar" refers to both a spar and a pseudo-spar. The collar 41 also includes an underside recess 47.

[0045] Collar 42 includes a spar 44 that supports the half-wing 22 and a helical projection 46 on its upper surface with teeth oriented laterally. Collar 42 also includes an upper recess 48. Gear 50 has teeth corresponding to the teeth of the helical projections 45 and 46. Although not shown, collar 41 has a tenon connector (or lug) that moves within a helical slot (or channel) by a fixed central shaft 49. Depending on the modification, this tenon is supported by the fixed central shaft 49 or collar 41, and the slot is formed in collar 41 or the fixed central shaft 49, respectively. Similarly, collar 42 has a tenon connector (or lug) that moves within a helical slot (or channel) by a fixed central shaft 49. Depending on the modification, this tenon is supported by the fixed central shaft 49 or collar 42, and the slot is formed in collar 42 or the fixed central shaft 49, respectively. Naturally, these helical geometries correspond to each other, meaning that the same rotation angle corresponds to the same translational movement along axis 27. The rotation of gear 50, represented by the clockwise circular arrow in Figure 14 for the deployment motion of the wing assembly (and therefore in the opposite direction for the folding motion), synchronizes the downward helical motion of collar 41 and the upward helical motion of collar 42 at the same angular velocity.

[0046] At the end of the rotation of gear 50 shown in Figure 15, i.e., at the end of the deployment of the wing assembly 20, the shaft of gear 50 is retracted into recesses 47, 48. The deployment joints 60 of the lower wings 24, 25 are similar to the joints 40 of the upper wings 22, 23 shown in Figures 13-15.

[0047] As can be seen in Figures 16 and 17, the joint 60 has a fixed central shaft 69 on which the collars 61 and 62 of the hemiwings 25 and 24 perform a helical motion during the deployment of these hemiwings. Collar 61 includes a spar 63 that supports hemiwing 25. Collar 62 includes a spar 64 that supports hemiwing 24. A support 65 holds the shaft 69 in place at its lower end within the fuselage 21. Thus, the shaft 69 and the components it directly supports are located inside the fuselage 21, thereby protecting them, especially during the landing of the drone 18, and reducing the turbulence generated by the joint 60. Similarly, the shaft 49 and collars 41 and 42 are supported within the fuselage 21. Unlike the spars 63 and 64, the spars 43 and 44 have vertical offsets 56 and 57 to reduce the turbulence generated by the joint 40.

[0048] The hemiwings 24 and 25 are kept folded within the launch tube 31 by being pressed against the vertical wall of the launch tube 31. To initiate the deployment of the hemiwings 24 and 25, after the drone is launched from the launch tube 31, the ends of a helical spring 68, positioned around a fixed axis 66, are held by the vertical lugs 67 of the spars 63 and 64. The spring 68 is compressed as the hemiwings 24 and 25 are folded. Thus, the deployment of the hemiwings 24 and 25 is very rapid. In contrast, the deployment of the upper hemiwings 22 and 23 is delayed or relatively slow, and by the time the hook 30 reaches the end of its movement and engages with the notch 29, the notch 29 is already in place.

[0049] Many means can be used to delay the completion of the deployment of the upper wings 22, 23 compared to the completion of the deployment of the lower wings 24, 25. In a first example (not shown), a pin passing through the upper wings 22, 23 holds them in place until a mechanical part, actuated by the nearly complete deployment of the lower wings 24, 25, moves the pin and releases the wings 22, 23. In a second example (not shown), a spring for separating the upper wings 22, 23 has a stiffness significantly lower than that of spring 68 and / or a significantly larger angular stroke than that of spring 68. In a third example (not shown), a meshing or connecting rod between joints 40 and 60 delays or slows down the deployment of the upper wings 22, 23 compared to the deployment of the lower wings 24, 25.

[0050] When a half-wing is fully deployed, the spring has not completed its stroke and has not reached its resting position. Therefore, the spring is still under tension. In the forward half-wing, this residual tension counteracts the relative wind. In the rear half-wing, this residual tension maintains these wings in the deployed state and also maintains the lock between the forward half-wing and the rear half-wing in contact with it under stress.

[0051] It should be noted that, in addition to or instead of this, the maintenance of this lock can also be achieved by a mechanical lock, such as one or more magnets.

[0052] It should be noted that the rotating means, particularly the joints 40, 60, for rotating the two hemiwings 22, 24, or the two hemiwings 23, 25 located on the same side of the fuselage 21 are purely mechanical, as in the case of the drone 18 shown in Figures 1-16, and therefore do not require any electrical energy source. In some modifications (not shown), at least one electric motor and / or at least one electromagnetic actuator are utilized.

[0053] To ensure that this helical motion process proceeds smoothly between the right hemiplane 23 and the left hemiplane 22, the hemiplane furthest from the fuselage 21 in the folded configuration of the wing assembly incorporates the portion of the hemiplane closest to the fuselage 21 in this folded configuration. In the illustrated embodiment, the upper left hemiplane 22 includes an extended portion 52, which is composed of a portion 51 removed from the upper right hemiplane 23. For example, this portion 52 is a part that protrudes upward in the helix in correspondence with the relative motion of hemiplanes 22, 23. Thus, this portion 52 completely complements the upper right hemiplane 23, thereby making the wing assembly 20 of the drone 18 symmetrical with respect to a vertical plane passing through the main axis 33 of the fuselage 21. For the purposes of the present invention, "in the opposite direction" rotation is observed by viewing the drone 18 vertically from above or below.

[0054] Variation In the particular embodiment described above, the rotating means 40, 60 are configured such that, along with the lengths of the half-wings 22, 24 and 23, 25 located on the same side of the fuselage 21, contact between these half-wings occurs at their free ends. In other embodiments (not shown), half-wings on the same side of the fuselage, i.e., the right or left side of the fuselage, contact occurs at a point that is neither the end of one half-wing nor the end of either half-wing. In other words, at least one of the half-wings extends beyond the connecting means.

[0055] In some embodiments (not shown), the connecting means 29, 30 either do not have notches or have notches on only one of the contacting half-wings. For example, the connecting means are formed by magnets of opposite poles or hooks.

[0056] In some embodiments (not shown), both rotational means for rotating the hemiwings are located above or below the drone's fuselage.

[0057] In some embodiments (not shown), none of the half-wings are equipped with end plates.

[0058] In some embodiments (not shown), the rotating means for rotating the half-wing is configured such that the half-wing performs pure rotational motion without translational motion, variable-pitch helical motion, or motion formed by a cam or connecting rod.

Claims

1. A drone (18) having a body (21), The aforementioned fuselage is: - Rotating means (40, 60) for rotating two hemiwings (22, 23, 24, 25) on each side of the fuselage around two pivot axes (27, 28), wherein the rotating means (40, 60) are configured such that, during the deployment of a wing assembly (20) consisting of the four hemiwings on both sides of the fuselage, the rotation of the hemiwings on the same side of the fuselage is carried out in opposite directions until the hemiwings make contact. - Means (29, 30) for integrally connecting the half-wings when the half-wings located on the same side of the fuselage come into contact with each other. A drone (18) characterized by having the following features.

2. The drone (18) according to claim 1, wherein the rotating means (40, 60) is configured such that, along with the length of the hemiwings (22, 23, 24, 25) located on the same side of the fuselage (21), contact between the hemiwings occurs at the free ends of the hemiwings.

3. The drone (18) according to claim 1 or 2, wherein the means for connecting (29, 30) comprises at least one notch formed on at least one of the half-wings (22, 23, 24, 25).

4. The means for connecting (29, 30) are located on the same side of the fuselage (21): - One of the aforementioned half-wings (24, 25), with at least one notch (29) formed in the wingtip plate (32) of the half-wing; - The other half-wing (22, 23) has at least one horizontal notch (30) and A drone (18) according to claim 3, comprising the above.

5. Each side of the fuselage (21) is provided with an upper half-wing (22, 23) that is rotated by a rotating means (40) positioned above the fuselage, and a lower half-wing (24, 25) that is rotated by a rotating means (60) positioned below the fuselage. The wing assembly (20) is rhomboid when fully deployed, the drone (18) according to any one of claims 1 to 4.

6. A drone (18) according to any one of claims 1 to 5, wherein at least one hemiwing (24, 25) on each side of the fuselage (21) is provided with a wingtip plate (32) attached to a hinge (54), and the hinge is provided with a spring configured to separate the wingtip plate from the hemiwing that supports the wingtip plate (32) during the movement of the hemiwing away from the fuselage when the wing assembly (20) is deployed.

7. The drone (18) according to any one of claims 1 to 6, wherein the rotating means (40, 60) for rotating the hemiplanes (22, 23, 24, 25) is configured to cause at least one hemiplane to perform rotational motion combined with translational motion in a helical motion.

8. The drone (18) according to claim 7, wherein, with respect to two half-wings (22, 23) that are rotated by the same rotating means (40), one of the half-wings (22) has an extension portion (52), and the other half-wing (23) has a recess (51) having the same geometry as the extension portion, and the extension portion is configured to fill the recess when the wing assembly (20) is deployed.

9. The drone (18) according to claim 8, wherein the extended portion (52) and the recess (51) are determined by the spiral traced during the relative motion of the half-wings (22, 23).

10. The drone (18) according to any one of claims 1 to 9, wherein the rotation axes (27, 28) of the rotating means (40, 60) for rotating the hemiwings (22, 23, 24, 25) intersect and form an angle of 20° or less with respect to each other.

11. A drone (18) according to any one of claims 1 to 10, comprising means for delaying the completion of the deployment of one of the aforementioned hemiwings (22, 23) relative to the completion of the deployment of another aforementioned hemiwing (24, 25) located on the same side of the fuselage (21).

12. The drone (18) according to any one of claims 1 to 11, wherein the rotating means (40, 60) for rotating the two hemiwings (22 and 24, or 23 and 25) located on the same side of the fuselage (21) is purely mechanical and therefore does not require any electrical energy source.

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