A wing folding structure for unmanned aerial vehicle

Abstract

The present invention discloses a wing folding structure for a drone, comprising: the drone comprises a fuselage and two wings symmetrically arranged on both sides of the fuselage; one end of each wing is hinged to the fuselage, and the other end is hinged to a multi-link mechanism, the multi-link mechanism is hinged to a straight rod through a connecting shaft, an arc groove is arranged on the fuselage, the connecting shaft can slide along the arc groove, the other end of the straight rod is arranged with a driving member, the driving member is connected to the straight rod, the driving direction of the driving member is arranged along the length direction of the fuselage, the driving member drives the straight rod to move linearly, and then drives the wings on the same side to unfold or fold. The wing folding structure adopts a full-link form to achieve a large-angle wing sweep, and it can be extended to drones with slightly larger structures.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a wing folding structure for unmanned aerial vehicles. Background Art

[0002] Unmanned aircraft, or "drones" for short, are aircraft that are controlled by radio remote control equipment and self-contained program control devices. Drones have been widely used in both military and civilian fields, with a wide range of civilian applications such as aerial photography, agriculture, express delivery, and power inspection. The popular Evotl concept has further expanded the concept of drones from non-manned to manned.

[0003] Drones can be divided into rotary wing and fixed wing in terms of their flight mode. Fixed wing aircraft have a greater cruising speed and cruising range than rotary wing aircraft due to their aerodynamic performance advantages, but the wings of drones are designed to be slender to obtain better aerodynamic characteristics. The slenderness of the wings will inevitably affect the transportation and parking of the aircraft. In the future, if drones are to enter ordinary people's homes like cars, the storage space requirements must be solved, so it is necessary to design a reasonable folding mechanism that can be used on drones. Summary of the invention

[0004] In view of the above problems existing in the prior art, it is intended to provide a wing folding structure for a UAV.

[0005] The specific technical solutions are as follows:

[0006] A wing folding structure for a drone, mainly comprising: the drone comprises a fuselage and two wings symmetrically arranged on both sides of the fuselage;

[0007] One end of one side of each wing is hinged to the fuselage, and the other end is hinged to a multi-link mechanism. The multi-link mechanism is hinged to a straight rod through a connecting shaft. An arc groove is provided on the fuselage, and the connecting shaft can slide along the arc groove. A driving member is provided at the other end of the straight rod, and the driving member is connected to the straight rod in a driving direction. The driving direction of the driving member is set along the length direction of the fuselage. The driving member drives the straight rod to move in a straight line, thereby driving the wing on the same side to unfold or fold.

[0008] The above-mentioned wing folding structure for a drone also has the following characteristics: the multi-link mechanism includes a first link, a second link and a bending rod, one end of the first link is hinged to the wing, and the other end is hinged to the second link, the second link is hinged to the bending rod, and the bending rod is hinged to the straight rod through the connecting shaft.

[0009] The above-mentioned wing folding structure for a drone also has the following feature: a limit rod is also provided on the first connecting rod, one end of the limit rod is hinged to the first connecting rod, and the other end is hinged to a fixed block provided on the fuselage.

[0010] The above-mentioned wing folding structure for a drone also has the following feature: two lugs are provided on the same side of the wing, namely a first lug and a second lug, the first lug is hinged to the fuselage, and the second lug is hinged to the multi-link mechanism.

[0011] The above-mentioned wing folding structure for a drone also has the feature that the fixing block is close to the second lug.

[0012] The above-mentioned wing folding structure for a UAV also has the following characteristics: the driving member is an actuator, and the actuator is a cylinder, a hydraulic cylinder or an electric push rod.

[0013] The above-mentioned wing folding structure for a UAV also has the following feature: the two straight rods on both sides share one driving member or each of them corresponds to one driving member.

[0014] The positive effects of the above technical solution are:

[0015] The present invention provides a wing folding structure for a UAV, which adopts a full-link form to achieve a large-angle wing sweep, and can be extended to UAVs with slightly larger structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic diagram of the first state structure of the wing folding structure for a drone provided by the present invention;

[0017] Figure 2 A schematic diagram of the second state structure of the wing folding structure for a UAV provided by the present invention.

[0018] In the accompanying drawings: 1, fuselage; 11, arc groove; 2, wing; 21, first lug; 22, second lug; 3, multi-link mechanism; 31, first link; 32, second link; 33, bending rod; 4, connecting shaft; 5, straight rod; 6, driving member; 7, limit rod; 8, fixing block. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below through embodiments and in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0020] The serial numbers of the components herein, such as "first", "second", etc., are only used to distinguish the objects described and do not have any order or technical meaning. The "connection" and "coupling" mentioned in this application, unless otherwise specified, include direct and indirect connections (couplings). In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc. are based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present invention.

[0021] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0022] See also Figure 1 and Figure 2 The present invention discloses a wing folding structure for a UAV. First, the UAV comprises a fuselage 1 and two wings 2 symmetrically arranged on both sides of the fuselage 1. Figure 1 and Figure 2 The fuselage 1 and the wing 2 are shown in simplified form.

[0023] One end of each side of the wing 2 is hinged to the fuselage 1, and the other end is hinged to a multi-link mechanism 3. The multi-link mechanism 3 is hinged to a straight rod 5 through a connecting shaft 4. An arc groove 11 is provided on the fuselage 1, and the connecting shaft 4 can slide along the arc groove 11. A driving member 6 is provided at the other end of the straight rod 5. The driving member 6 is drivingly connected to the straight rod 5. The driving direction of the driving member 6 is set along the length direction of the fuselage 1. The driving member 6 drives the straight rod 5 to move in a straight line, thereby driving the wing 2 on the same side to unfold or fold.

[0024] Specifically, in this embodiment, the wings 2 on both sides are symmetrically arranged in the same manner, so only the arrangement of the wing 2 on one side is described. The number of wings 2, multi-link mechanism 3, connecting shaft 4, straight rod 5 and driving member 6 are all multiplied by 2, that is, two wings 2, multi-link mechanism 3, connecting shaft 4, straight rod 5 and driving member 6 are each provided, and are symmetrically arranged on the fuselage 1.

[0025] Optionally, the multi-link mechanism 3 includes a first link 31, a second link 32 and a bent rod 33, one end of the first link 31 is hinged to the wing 2, and the other end is hinged to the second link 32, the second link 32 is hinged to the bent rod 33, and the bent rod 33 is hinged to the straight rod 5 through the connecting shaft 4. Specifically, Figure 1 and Figure 2 As shown, the bending direction of the bending rod 33 is away from the wing 2 on the corresponding side.

[0026] Furthermore, a limit rod 7 is also provided on the first connecting rod 31 , one end of the limit rod 7 is hinged to the first connecting rod 31 , and the other end of the limit rod 7 is hinged to a fixing block 8 provided on the fuselage 1 .

[0027] Optionally, in this embodiment, two lugs are provided on the same side of the wing 2, namely a first lug 21 and a second lug 22, the first lug 21 is hinged to the fuselage 1, and the second lug 22 is hinged to the multi-link mechanism 3. Optionally, the fixing block 8 is close to the second lug 22.

[0028] Optionally, the driving member 6 is an actuator, and the actuator is a cylinder, a hydraulic cylinder or an electric push rod.

[0029] It should be noted that the two straight rods 5 on both sides may share one driving member 6 or each of them may have one driving member 6 , so the number of the driving members 6 may be one or two.

[0030] Optionally, in this embodiment, the arc groove 11 takes the hinge point where the wing 2 and the fuselage 1 are hinged as the center, and the length of the arc groove 11 can control the angle at which the wing 2 is opened or folded. For example, in this embodiment, each arc groove 11 is symmetrically arranged along the straight line where the hinge points on both sides are located, and the angle of the arc groove 11 is 90 degrees, which can control the unfolding angle of the wing 2 from 0° to 90°, and at the same time, the angle of each link of the multi-link mechanism 3 and the angle between the links.

[0031] like Figure 1 As shown, the wing 2 is in the unfolded state, and the drive member 6 is in the retracted state. Figure 2 As shown, the wing 2 is in a folded state, and at this moment, the driving member 6 is in an extended state.

[0032] The wing folding structure for a UAV provided by the present invention adopts a full-link form to achieve a large-angle wing sweep, and can be extended to UAVs with slightly larger structures.

[0033] Only one driving member 6 is required to realize the unfolding and folding functions of the wings on both sides, thus saving unnecessary waste.

[0034] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0035] The above embodiments only express several implementation methods of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the attached claims.

Claims

1. A wing folding structure for a drone, characterized in that: include: The drone comprises a fuselage and two wings symmetrically arranged on both sides of the fuselage; One end of each side of the wing is hinged to the fuselage, and the other end is hinged to a multi-link mechanism, the multi-link mechanism is hinged to a straight rod through a connecting shaft, an arc groove is provided on the fuselage, the connecting shaft can slide along the arc groove, and the angle of the arc groove is 90 degrees, which can control the wing deployment angle from 0° to 90°, the other end of the straight rod is provided with a driving member, the driving member is connected to the straight rod, the driving direction of the driving member is set along the length direction of the fuselage, the driving member drives the straight rod to move linearly, and then drives the wing on the same side to unfold or fold, the multi-link mechanism includes a first link, a second link and a bending rod, one end of the first link is hinged to the wing, and the other end is hinged to the second link, the second link is hinged to the bending rod, and the bending rod is hinged to the straight rod through the connecting shaft; A limiting rod is also arranged on the first connecting rod, one end of the limiting rod is hinged to the first connecting rod, and the other end of the limiting rod is hinged to a fixing block arranged on the fuselage.

2. The wing folding structure for a drone according to claim 1, characterized in that: Two lugs are arranged on the same side of the wing, namely a first lug and a second lug, wherein the first lug is hinged to the fuselage, and the second lug is hinged to the multi-link mechanism.

3. The wing folding structure for a drone according to claim 2, characterized in that: The fixing block is close to the second lug.

4. The wing folding structure for a drone according to any one of claims 1 to 3, characterized in that: The driving member is an actuator, and the actuator is a cylinder, a hydraulic cylinder or an electric push rod.

5. The wing folding structure for a drone according to claim 1, characterized in that: The two straight rods on both sides share one driving member or each of them corresponds to one driving member.

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