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EP-4739572-A1 - DRONE WING ASSEMBLY AND DRONE COMPRISING SAME

EP4739572A1EP 4739572 A1EP4739572 A1EP 4739572A1EP-4739572-A1

Abstract

The drone (18) comprises a fuselage (21) which comprises: - rotation means (40, 60) for rotating two half-wings (22, 23, 24, 25) about two axes of rotation, on each side of the fuselage, the rotation means being configured so that, during the deployment of the wing assembly (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 are performed in opposite directions until these half-wings come into contact, and - means (29, 30) for coupling together the half-wings on the same side of the fuselage when in contact. In some embodiments, 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 is made at the free end of these half-wings.

Inventors

  • VARIGAS, François

Assignees

  • Fly-R

Dates

Publication Date
20260513
Application Date
20240702

Claims (12)

  1. 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) about two axes of rotation (27, 28), on each side of the fuselage, the rotation means being configured so that, when deploying 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 of attachment (29, 30) between them, half-wings on the same side of the fuselage in contact.
  2. 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 is made at the free end of these half-wings.
  3. 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. 4. Drone (18) according to claim 3, in which the attachment means (29, 30) comprise, on the same side of the fuselage (21): - for a half-wing (24, 25), at least one notch (29) formed in a wing tip fin (32) of this half-wing, and - for the other half-wing (22, 23), at least one horizontal notch (30).
  5. 5. Drone (18) according to one of claims 1 to 4, 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.
  6. 6. Drone (18) according to one of claims 1 to 5, 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, when deploying the wing (20).
  7. 7. Drone (18) according to one of claims 1 to 6, 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.
  8. 8. Drone (18) according to claim 7, 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.
  9. 9. Drone (18) according to claim 8, in which the extension (52) and the withdrawal (51) are determined by the helicoid followed during the relative movement of these half-wings (22, 23).
  10. 10. Drone (18) according to one of claims 1 to 9, 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.
  11. 11. Drone (18) according to one of claims 1 to 10, 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).
  12. 12. Drone (18) according to one of claims 1 to 11, 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.

Description

DESCRIPTION TITLE: DRONE WING AND DRONE COMPRISING IT Technical field of the invention 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 Drones launched in a folded configuration, generally from a launch tube, have wings mounted in rotation relative to an axis of rotation. As a result, their anchoring to the drone fuselage is small. The oscillations of the wings caused by the air flow 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 drone's drag to the detriment of its speed and range. Presentation of the invention The wing object of the invention comprises, on each side of the fuselage, two half-wings mounted in rotation relative to two substantially parallel axes of rotation, these half-wings deploying in opposite directions of rotation until they come into contact, preferably at their ends. Means for attaching these ends of the half-wings located on the same side of the fuselage to each other reduce the degrees of freedom of movement of the half-wings and therefore the oscillations of these half-wings. The rigidity of the wing is thus improved, as well as the control of air navigation and the drag of the drone. 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. Preferably, once fully deployed, the wing is rhomboidal. 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. Preferably, the means for deploying the wing are purely mechanical and do not require any source of electrical energy. Summary of the invention The present invention aims to remedy all or part of the drawbacks of the prior art. To this end, the present invention aims at a drone which comprises a fuselage, this fuselage comprising: - means for rotating two half-wings around two axes of rotation, on each side of the fuselage, the rotation means being configured so that, when the wing, consisting of the four half-wings, on either side of the fuselage, is deployed, 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 attaching, between them, the half-wings on the same side of the fuselage in contact. Thus, the means of attachment between them of these ends of the half-wings located on the same side of the fuselage 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. In embodiments, the rotation means are configured, together with the lengths of the half-wings on the same side of the fuselage, so that contact between these half-wings occurs at the free end of these half-wings. 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. In embodiments, the attachment means comprise at least one notch formed on at least one half-wing. The attachment is thus carried out by penetration of a part of one half-wing into the notch of the other half-wing. In embodiments, the attachment means comprise, on the same side of the fuselage: - for a half-wing, at least one notch formed in a wing tip fin of this half-wing, and - for the other half-wing, at least one horizontal notch. The notches of the two half-wings therefore fit into each other, which eliminates any degree of freedom of one half-wing in relation to the other. In embodiments, the drone comprises, on each side of the fuselage, an upper half-wing rotated by a rotation means positioned above the fuselage and a lower half-wing, respectively, rotated by a rotation means positioned below the fuselage, the wing being, once fully deployed, rhomboidal. The drone thus has the advantages of rhomboidal wings. In embodiments, on each side of the fuselage, at least one half-wing comprises a wingtip fin mounted on a hinge 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 the deployment of the wing. Thus, the wingtip fin deploys during the deployment of the half-wing which carries it. In embodime