Auxiliary clamping device for folding wings of unmanned aerial vehicle

Abstract

The utility model belongs to the field of unmanned aerial vehicle design, and provides an unmanned aerial vehicle folding wing auxiliary clamping device which is mainly composed of a left wing 1, a right wing 2, a first rotating shaft 3, a second rotating shaft 4, a fuselage 5 and an auxiliary clamping assembly 6. The left wing 1 and the right wing 2 are installed at the bottom of the fuselage 5 through a first rotating shaft 3 and a second rotating shaft 4 respectively and can rotate around the first rotating shaft 3 and the second rotating shaft 4 respectively, and an auxiliary clamping assembly 6 is installed at the bottom of the fuselage 5 and located at the wing tip position after the wings are folded, so that when the left wing 1 and the right wing 2 rotate around the first rotating shaft 3 and the second rotating shaft 4 respectively to be in the folded state, the wings can be clamped. The rear edges of the wingtips of the left wing and the right wing can be clamped into the auxiliary clamping assembly 6, fixing and limiting of the left wing and the right wing in the folded state are achieved, the supporting rigidity of the wings in the folded state is improved, and the fatigue life of the connecting area of the wings and the fuselage is prolonged.

Description

TECHNICAL FIELD

[0001] The utility model relates to an unmanned vehicle folding wing auxiliary clamping device, especially relates to a large aspect ratio unmanned vehicle folding wing cantilever auxiliary clamping device. BACKGROUND

[0002] The unmanned vehicle folding wing is widely applied to various long-distance low-cost unmanned vehicles because of many advantages such as great lift, small lift-drag ratio and good economy. Meanwhile, the wing can be folded, the size of a packing box or a launching box can be reduced, the storage space utilization rate can be greatly improved, the land occupation area can be reduced, and the transportation and storage capacity can be improved. However, most unmanned vehicle folding wings rotate and fold around a rotating shaft at a wing root, and the whole wing is in a cantilever state only with a connecting point at the rotating shaft. In the process of transfer, hoisting and transportation, the wing inevitably vibrates greatly, and periodic bending load is generated on the connecting area of the rotating shaft of the fuselage, so that the fuselage is damaged by fatigue.

[0003] In view of the above-mentioned deficiencies of the unmanned vehicle folding wing, the utility model provides an unmanned vehicle folding wing auxiliary clamping device, which is simple, easy to assemble, has good clamping capacity for the wing tip of the folding wing, and effectively reduces the vibration of the wing in the state of transfer, hoisting and transportation. UTILITY MODEL CONTENTS

[0004] The utility model relates to an unmanned vehicle folding wing, especially a large aspect ratio unmanned vehicle folding wing, and designs an auxiliary clamping device at the wing tip, so that the vibration of the wing in the process of transfer, hoisting and transportation is inevitably reduced, the periodic bending load on the connecting area of the rotating shaft of the fuselage is reduced, and the fuselage is damaged by fatigue.

[0005] The technical scheme of the utility model is as follows:

[0006] The utility model provides an unmanned vehicle folding wing auxiliary clamping device, which mainly comprises a left wing 1, a right wing 2, a rotating shaft one 3, a rotating shaft two 4, a fuselage 5 and an auxiliary clamping assembly 6, the left wing 1 and the right wing 2 are respectively installed at the bottom of the fuselage 5 through the rotating shaft one 3 and the rotating shaft two 4, and the left wing 1 and the right wing 2 can rotate around the rotating shaft one 3 and the rotating shaft two 4 respectively to realize folding and unfolding. The auxiliary clamping assembly 6 is installed at the bottom of the fuselage 5 and at the wing tip position after folding of the wing, so that when the left wing 1 and the right wing 2 rotate around the rotating shaft one 3 and the rotating shaft two 4 to the folding state, the wing tip trailing edges of the left wing and the right wing can be clamped into the auxiliary clamping assembly 6, and the left wing and the right wing in the folding state are fixed and limited.

[0007] Further, the unmanned aerial vehicle folding wing auxiliary clamping device is characterized in that the auxiliary clamping assembly 6 comprises a V-shaped joint 61, a rubber pad 62 and a screw 63; the V-shaped joint 61 is symmetrically provided with ear pieces 612 on both sides of the top end, and the auxiliary clamping assembly 6 is connected and fixed with the fuselage 5 through the ear pieces 612; the V-shaped joint 61 is provided with V-shaped grooves 611 on both sides of the middle; the rubber pad 62 is bonded in the V-shaped grooves 611 of the V-shaped joint 61 and is fixed by the screw 63.

[0008] Further, the unmanned aerial vehicle folding wing auxiliary clamping device is characterized in that the V-shaped grooves 611 are symmetrically designed along the horizontal direction of the V-shaped joint 61, and the groove section is similar to the wing trailing edge section.

[0009] Further, the V-shaped joint 61 is designed as a sharp corner device on the front edge and the trailing edge.

[0010] Further, the V-shaped joint 61 can be designed as a triangle, a rhombus or other polygons.

[0011] Further, the V-shaped joint 61 is suitable for the left and right wings in the same plane after folding, and can also be partially changed for the wings folded in a scissors shape.

[0012] Further, the wing tips of the left and right wings are clamped into the V-shaped grooves of the auxiliary clamping assembly 6 to limit the rotation and movement of the left and right wings in the folded state.

[0013] The beneficial effects of the utility model are as follows:

[0014] 1. The unmanned aerial vehicle folding wing auxiliary clamping device provided by the utility model realizes the change of the wing folding state of the unmanned aerial vehicle from a single-point cantilever device to a head-tail double-point supporting device, effectively improves the loading condition of the folding wing, reduces the vibration amplitude of the wing under the working conditions of lifting and transportation, improves the stress distribution and bending deformation of the wing in the folded state, and improves the fatigue life of the wing connection area with the fuselage.

[0015] 2. The device is small in size, simple and compact in structure, high in bearing capacity, and easy to realize and install.

[0016] 3. The V-shaped joint in the device is designed as a sharp corner structure on the front and rear edges, and meets the requirement of the unmanned aerial vehicle in air free flight.

[0017] 4. The rubber pad in the V-shaped groove of the device can avoid the collision or friction caused by the rigid contact of the wing tip and the joint, and reduce the vibration of the wing. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 The folding wing auxiliary clamping device principle diagram (unfolded state) of the utility model is shown in Figure 1.

[0019] Figure 2 The folding wing auxiliary clamping device explosion view of the utility model is shown in Figure 2.

[0020] Figure 3 The auxiliary support assembly three-dimensional model diagram of the utility model is shown in Figure 3.

[0021] Figure 4 The auxiliary support assembly explosion view of the utility model is shown in Figure 4.

[0022] Figure 5 The folding wing auxiliary clamping device principle diagram (folded state) of the utility model is shown in Figure 5.

[0023] Figure 6 The auxiliary support assembly partial enlarged view of the utility model is shown in Figure 6.

[0024] In the figure, 1 is a left wing, 2 is a right wing, 3 is a rotating shaft one, 4 is a rotating shaft two, 5 is a fuselage, 6 is an auxiliary clamping assembly, 61 is a V-shaped joint, 611 is a V-shaped groove, 612 is an ear piece, 62 is a rubber pad, and 63 is a screw. DETAILED DESCRIPTION

[0025] This part is an embodiment of the utility model, which is used to explain and illustrate the technical scheme of the utility model. In the case of no conflict, the embodiments of the utility model and the features in the embodiments can be combined with each other.

[0026] The specific embodiments of the utility model will be further described in detail in combination with the drawings and embodiments. The following embodiments are used to illustrate the utility model, but not to limit the scope of the utility model.

[0027] As Figure 1 , Figure 2 , Figure 5 , Figure 6The utility model provides a kind of unmanned aerial vehicle folding wing auxiliary clamping device, it is mainly by left wing 1, right wing 2, pivot one 3, pivot two 4, fuselage 5, auxiliary clamping assembly 6 composition, left wing 1, right wing 2 are installed in fuselage 5 bottom by pivot one 3 and pivot two 4 respectively, left wing 1, right wing 2 can rotate respectively around pivot one 3 and pivot two 4 and realize folding and unfolding.Fuselage 5 bottom, auxiliary clamping assembly 6 is installed in wing tip position after wing folding, left wing 1, right wing 2 respectively rotate around pivot one 3 and pivot two 4 to folding state, left and right wing tip trailing edge can be inserted into auxiliary clamping assembly 6;Realize that the front end of wing has pivot one 3 and pivot two 4 connection, rear end has auxiliary clamping assembly 6 support, limit wing rotation around pivot by increasing auxiliary support, simultaneously reduce vibration amplitude, reduce wing bending deformation, reduce wing root and the fatigue load of connection area with fuselage.

[0028] As Figure 3 , Figure 4 Auxiliary clamping assembly 6 includes V-shaped joint 61, rubber pad 62, screw 63, as shown in the drawing, ear piece 612 is symmetrically arranged on both sides of the top end of V-shaped joint 61, and auxiliary clamping assembly 6 is connected and fixed with fuselage 5 through ear piece 612; V-shaped groove 611 is arranged on both sides of the middle of V-shaped joint 61; V-shaped groove is symmetrically designed along the horizontal direction of V-shaped joint 61, and the groove section is similar to the section of the trailing edge of the wing; rubber pad 61 is bonded in V-shaped groove 611 and fixed with screw 63. Rubber pad 62 is made of silicone rubber material, which can ensure better coplanar fitting between the trailing edges of left and right wings and V-shaped joint 61, increase the friction resistance, and avoid rigid contact between the wing and V-shaped groove 611, causing friction damage to the joint or the trailing edge of the wing.

[0029] V-shaped joint 61 is designed for drag reduction and fairing along the heading, and the leading edge and the trailing edge are designed as sharp corner devices. The leading edge and the trailing edge of V-shaped joint 61 can be triangular, rhombic or polygonal in shape, which can effectively reduce the aerodynamic drag of the unmanned aerial vehicle. Considering the drag reduction effect, flight speed and processing technology, the leading edge and the trailing edge are designed as acute angle structures with an angle of 40-70 degrees, which has the best aerodynamic drag reduction effect.

[0030] The trailing edge of the wing tip of the left and right wings is inserted into the V-shaped groove 611 of the auxiliary clamping assembly 6 to limit the bending deformation of the left and right wings under the action of gravity in the folded state, and also prevents the trailing edge of the wing from colliding with the bottom of the fuselage during vibration.

[0031] The V-shaped joint 61 considers the bearing and light weight requirements, selects aluminum alloy, titanium alloy processing forming, or composite material molding; it can also be molded using carbon fiber composite materials. Because the size is small, whether metal or composite materials are selected, the overall weight has no effect, so the material selection range, forming method has multiple.

[0032] The V-shaped groove 611 is symmetrically designed along the horizontal direction of the V-shaped joint 61 on both sides, and the groove section is similar to the wing trailing edge section, suitable for folding the left and right wings in the same plane.

[0033] In addition, the V-shaped groove 611 can be opened in an up-down staggered manner to be suitable for folding the wings in an up-down staggered manner, like a scissors-like folding wing auxiliary clamping and fixing.

[0034] The utility model discloses an unmanned aerial vehicle folding wing auxiliary clamping device to realize unmanned aerial vehicle wing folding state from single-point cantilever device to head-tail double-point support device, effectively improve the folding wing load condition, reduce the wing vibration amplitude under the working conditions such as hoisting, transportation, improve the stress distribution and bending deformation of the wing in the folding state, improve the fatigue life of the wing and fuselage connection place. The utility model has the advantages of small size, simple and compact structure, strong bearing capacity, easy installation and the like.

[0035] Although the preferred embodiments of the present application have been described, those skilled in the art can make further changes and modifications to the embodiments once they know the basic inventive concept. Therefore, the scope of protection of the present application is intended to include the preferred embodiments and all changes and modifications falling within the scope of the present application. Obviously, those skilled in the art can make various modifications and variations to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the present application and its equivalent technology, the present application also intends to include these modifications and variations.

Claims

1. An unmanned aerial vehicle folding wing auxiliary clamping device, mainly composed of a left wing (1), a right wing (2), a rotating shaft I (3), a rotating shaft II (4), a fuselage (5), and an auxiliary clamping assembly (6), wherein the left wing (1) and the right wing (2) are respectively installed at the bottom of the fuselage (5) through the rotating shaft I (3) and the rotating shaft II (4), and the left wing (1) and the right wing (2) can rotate around the rotating shaft I (3) and the rotating shaft II (4) respectively to realize folding and unfolding, characterized in that The auxiliary clamping assembly (6) is arranged at the bottom of the fuselage (5) and at the wing tip position after the wing folding, so that when the left wing (1) and the right wing (2) rotate to the folded state around the rotating shaft I (3) and the rotating shaft II (4) respectively, the wing tip trailing edges of the left wing and the right wing can be clamped into the auxiliary clamping assembly (6), and the left wing and the right wing in the folded state are fixed and limited.

2. The unmanned aerial vehicle folding wing assist clamp device of claim 1, wherein The auxiliary clamping assembly (6) comprises a V-shaped joint (61), a rubber pad (62) and a screw (63), the V-shaped joint (61) is symmetrically provided with an ear piece (612) on both sides of the upper end, the auxiliary clamping assembly (6) is connected and fixed with the fuselage (5) through the ear piece (612), and the V-shaped joint (61) is provided with a V-shaped groove (611) on both sides of the middle part, the rubber pad (62) is bonded in the V-shaped groove (611) and is fixed by the screw (63).

3. The unmanned aerial vehicle folding wing assist clamp of claim 2, wherein The V-shaped joint (61) is symmetrically provided with a V-shaped groove (611) at the lower end, the groove section is similar to the wing trailing edge section, and the auxiliary clamping and fixing of the left and right wings in the same plane after folding are suitable.

4. The unmanned aerial vehicle folding wing assist clamp of claim 2, wherein The V-shaped joint (61) is designed by the drag reduction fairing along the heading, and the leading edge and the trailing edge are both designed as sharp corner devices.

5. The unmanned aerial vehicle folding wing assist clamp device of claim 2, wherein The sharp corners of the leading edge and the trailing edge of the V-shaped joint (61) can be designed as acute angles of 40-70 degrees.

6. The unmanned aerial vehicle folding wing assist clamp of claim 2, wherein The V-shaped joint (61) is symmetrically provided with a V-shaped groove (611) on both sides, and the V-shaped grooves (611) on both sides are staggered upward and downward.

7. The unmanned aerial vehicle folding wing assist clamp device of claim 1, wherein The wing tip trailing edges of the left and right wings are clamped into the V-shaped grooves of the auxiliary clamping assembly (6), so that the left and right wings in the folded state can only realize normal rotation and movement.

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