Bidirectional folding omnidirectional wheel device for unmanned aerial vehicle body bracket

Abstract

The utility model relates to the technical field of packaging and transportation, and discloses a bidirectional folding omnidirectional wheel device for a fuselage bracket of an unmanned aerial vehicle, which comprises design realization of a normal movement form of an omnidirectional wheel, design realization of forward folding and backward folding, and design realization of different height differences between a putting-down form of the omnidirectional wheel and the forward folding and the backward folding. By means of the simple mechanical device design, the technical problem that the unmanned aerial vehicle body bracket is horizontally pushed forwards and backwards into packaging boxes with different height differences is solved, operation is easy, and the process is safe.

Description

Technical Field

[0001] The utility model relates to the technical field of packaging and transportation, and is a bidirectional folding omnidirectional wheel device for a drone fuselage bracket. Background Art

[0002] In the design of drone packaging and transportation, when separating the fuselage from the central wing, the fuselage bracket needs to be pushed backward into the central wing packaging box. The height difference between the bottom plate of the central wing packaging box and the ground is about 160mm. The omnidirectional wheels need to be folded forward to ensure that the omnidirectional wheels can bear the load after folding and the height difference before and after folding meets the requirement of 160mm. The fuselage bracket is transported and fixed, and the fuselage bracket needs to be pushed forward into the fuselage packaging box. The fuselage packaging box is designed with a sinking guide groove with a sinking height of about 20mm. The height difference between the bottom plate of the packaging box and the ground is about 140mm. The omnidirectional wheels need to be folded backward to ensure that the omnidirectional wheels can bear the load after folding and the height difference before and after folding meet the requirement of 140mm.

[0003] The maximum weight that the fuselage bracket and its upper part can bear is about 1200kg to 1500kg in total. This load requirement must be met both before and after the omnidirectional wheels are folded.

[0004] A bidirectional folding omnidirectional wheel device for a drone fuselage bracket realizes forward / backward folding of the omnidirectional wheel by designing a fixed rotating shaft, a second axle pin and a third axle pin that can be quickly disassembled and assembled. The welding angle and welding height of the limit stop rod are designed to meet the load-bearing requirements after the omnidirectional wheel is folded and the height difference requirements before and after the folding of the omnidirectional wheel.

[0005] A bidirectional foldable omnidirectional wheel device for a drone fuselage bracket. The load-bearing direction of the omnidirectional wheel after folding is consistent with the load-bearing requirement of the traveling direction of the fuselage bracket entering a packaging box. The fuselage bracket has the best load-bearing effect, ensuring the safe travel of the fuselage bracket pushing the box horizontally. Utility Model Content

[0006] In order to overcome the deficiencies of the prior art, the utility model provides a bidirectional folding omnidirectional wheel device for a UAV fuselage bracket, which solves the problems of the prior art such as complex device, difficult operation, great safety hazards, high cost, and low human-machine efficiency.

[0007] The technical solution adopted by the utility model to solve the above problems is:

[0008] A bidirectional foldable omnidirectional wheel device comprises: three axle pin holes are designed at the three end points of an inverted T-shaped load-bearing steel plate on an omnidirectional wheel assembly, which are respectively a forward axle pin hole, a middle axle pin hole and a rearward axle pin hole; three axle pin fixing ears are designed on a fuselage bracket, which are respectively matched with the forward axle pin hole, the middle axle pin hole and the rearward axle pin hole; a first axle pin, a second axle pin and a third axle pin; a front limit stop rod and a rear limit stop rod.

[0009] As a preferred technical solution, the inverted T-shaped load-bearing steel plate on the omni-directional wheel assembly has axle pin holes at the three ends of the inverted T-shaped load-bearing steel plate. The cross plate length of the inverted T-shaped load-bearing steel plate is limited, requiring that the ends cannot touch the ground after the omni-directional wheel is folded.

[0010] As a preferred technical solution, the fuselage bracket is matched with an inverted T-shaped load-bearing steel plate and three load-bearing ears are set at the three end points, and the load-bearing ears and the shaft pin holes meet the coaxiality requirements on the center line of the shaft.

[0011] As an optimal technical solution, a simple mechanical structure is used, three points of load bearing are carried, and the diameters of the first, second and third axle pins are reasonably selected to meet the load requirements. Through the reasonable arrangement of the axle pins, the first axle pin at the end of the inverted T-shaped vertical plate is fixedly installed as a rotating shaft, and the second and third axle pins at the end of the T-shaped horizontal plate are designed for quick disassembly and assembly, and the omnidirectional wheels are rotated and folded in two directions.

[0012] As a preferred technical solution, the limit stop rod is welded on the fuselage bracket and arranged on both sides of the inverted T-shaped vertical plate.

[0013] As an optimal technical solution, the rectangular tube cross-sectional area and thickness of the limit stop rod are reasonably selected, and the limit stop rod meets the load-bearing requirements after the omnidirectional wheel is folded.

[0014] As an optimal technical solution, the welding angle and welding height of the limit stop rod are reasonably selected, and the height difference of the omnidirectional wheel after folding satisfies the height difference of the fuselage bracket entering the box.

[0015] Compared with the prior art, the utility model has the following beneficial effects:

[0016] (1) The utility model can realize the omnidirectional wheel rotating and folding in two directions around the first axle pin at the end point of the vertical plate by removing the second axle pin and the third axle pin at the end point of the inverted T-shaped horizontal plate.

[0017] (2) Remove the second or third axle pin at the end of the cross plate, and the process of entering the packaging box in the forward direction is blocked by the bottom beam. The omnidirectional wheels fold in the opposite direction of movement by themselves without additional power or manual intervention. The folding process is blocked by the limit stop rod, and the folding height is limited. The folding process and the limit stop can be achieved by a simple mechanism.

[0018] (3) The utility model has a simple and reliable structure, low manufacturing cost, low technical requirements for users, good safety effects, and a wide range of application scenarios. It can be used on all brackets with height differences that require two-way access. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1This is a schematic diagram of the structure of a UAV fuselage bracket bidirectional folding omnidirectional wheel device of the utility model

[0020] Figure 2 This is a schematic diagram of the right folding of a two-way folding omnidirectional wheel device of a UAV fuselage bracket of the utility model

[0021] Figure 3 This is a schematic diagram of the left-folding of a two-way folding omnidirectional wheel device for a UAV fuselage bracket of the utility model. The markings and corresponding parts names in the attached figure are: 1. forward axle pin hole, 2. middle axle pin hole, 3. front limit stop rod, 4. rear limit stop rod, 5. rear axle pin hole, 6. inverted T-shaped load-bearing steel plate, 7. omnidirectional wheel, 8. first axle pin, 9. second axle pin, 10. third axle pin. DETAILED DESCRIPTION

[0022] The present invention will be further described in detail below in conjunction with the embodiments and drawings, but the implementation manner of the present invention is not limited thereto.

[0023] like Figure 1 to Figure 3 As shown, the utility model can be implemented in the following manner:

[0024] (I) Device composition and position relationship:

[0025] a) Overall composition:

[0026] The inverted T-shaped load-bearing steel plate 6 of the omnidirectional wheel, three load-bearing ears on the fuselage bracket, three axle pins 8, and a front limit stop 3 / rear limit stop rod 4.

[0027] b) Component refinement:

[0028] Three pin holes are set at the three ends of the inverted T-shaped load-bearing steel plate 6, and the pin hole diameter is 22mm. Three load-bearing ears are welded on the fuselage bracket, and the inner hole diameter is 22mm. The outer diameters of the first shaft pin 8, the second shaft pin 9, and the third shaft pin 10 are all 21.5mm. The front ends of the second shaft pin 9 and the third shaft pin 10 are designed to be conical, with a taper of 20 degrees and a cone head length of 5mm; the lengths of the first shaft pin 8, the second shaft pin 9, and the third shaft pin 10 are greater than the width of the load-bearing ears on the fuselage bracket that match the forward shaft pin hole 1, the middle shaft pin hole 2, and the rear shaft pin hole 5, which are about 15mm. The front limit stop rod 3 and the rear limit stop rod 4 are selected from 50 square tubes with a thickness of 3mm.

[0029] c) Installation position relationship:

[0030] The three pin holes set at the three ends of the inverted T-shaped load-bearing steel plate 6 are concentric with the axis of the load-bearing ear of the fuselage, and the deviation does not exceed 3mm. The length of the horizontal plate of the inverted T-shaped load-bearing steel plate 6 is limited, and the horizontal plate cannot touch the ground after the wheels are folded. The pin holes at the ends of the vertical plates of the inverted T-shaped load-bearing steel plate 6 are installed with the first axle pin 8, and the pin holes at the ends of the horizontal plates of the inverted T-shaped load-bearing steel plate 6 are installed with the second axle pin 9 and the third axle pin 10. The limit stop rod is installed on both sides of the vertical plate of the inverted T-shaped load-bearing steel plate 6, and the installation angle of the rear limit stop rod 4 is 42 degrees with the plumb line, and the installation angle of the front limit stop rod 3 is 38 degrees with the plumb line. After the front limit stop rod stops the folded omnidirectional wheel, H1-H3=150mm. After the rear limit stop rod stops the folded omnidirectional wheel, H1-H3=170mm.

[0031] (II) Working process:

[0032] a) Omni-directional wheels are not folded

[0033] Normal travel use, such as Figure 1 As shown, the first axle pin 8 in the middle axle pin hole 2 at the vertical plate end of the inverted T-shaped load-bearing steel plate 6 is installed in place, and the second axle pin 9 and the third axle pin 10 in the forward axle pin hole 1 and the rearward axle pin hole 5 at the horizontal plate end of the inverted T-shaped load-bearing steel plate 6 are installed in place.

[0034] b) Omnidirectional wheels fold to the left

[0035] Push the fuselage bracket to the left and place it into the packaging box. Figure 2 As shown, the first axle pin 8 in the median axle pin hole 2 at the vertical plate end of the inverted T-shaped load-bearing steel plate 6 is installed in place. During the left-moving process, when the omnidirectional wheel approaches the bottom beam of the packaging box, the second axle pin 9 and the third axle pin 10 in the forward axle pin hole 1 and the rearward axle pin hole 5 at the horizontal plate end of the inverted T-shaped load-bearing steel plate 6 are removed, and the omnidirectional wheel contacts the bottom beam of the packaging box, and the omnidirectional wheel is retracted and folded to the right. The rear limit stop rod 4 contacts the horizontal plate of the inverted T-shaped load-bearing steel plate 6, and the omnidirectional wheel folds and stops. The elevation difference is about 150 mm (considering the uneven ground factor). The folded omnidirectional wheel is pushed into the packaging box, contacts the floor of the packaging box, and the fuselage bracket is pushed flat to the left into the packaging box.

[0036] c) Omnidirectional wheels fold to the right

[0037] Push the fuselage bracket forward into the packaging box. Figure 3As shown, the first axle pin 8 in the middle pin hole 2 at the vertical plate end of the inverted T-shaped load-bearing steel plate 6 is installed in place. During the right-hand movement, when the omnidirectional wheel approaches the bottom beam of the packaging box, the second axle pin 9 and the third axle pin 10 in the forward axle pin hole 1 and the rearward axle pin hole 5 at the horizontal plate end of the inverted T-shaped load-bearing steel plate 6 are removed, and the omnidirectional wheel contacts the bottom beam of the packaging box. The omnidirectional wheel is retracted and folded to the left, and contacts the front limit stop rod 3. The horizontal plate of the inverted T-shaped load-bearing steel plate 6 and the omnidirectional wheel are folded and stopped. The elevation difference is about 170 mm (considering the uneven ground factor). The folded omnidirectional wheel is pushed into the packaging box, contacts the floor of the packaging box, and the fuselage bracket is pushed flat to the right into the packaging box.

[0038] In order to effectively solve the process of pushing the fuselage bracket to the right or left into the packaging box, the omnidirectional wheels are folded in both directions, and the height difference before and after the folding of the omnidirectional wheels is adjusted through the stop support of the limit stop rod, which effectively solves the left and right travel after the omnidirectional wheels are folded, and ensures that the force direction of the omnidirectional wheels during the travel process is consistent with the force application direction during the travel process.

[0039] The utility model realizes the bidirectional folding of bidirectional omnidirectional wheels through a simple mechanical structure, without any special processing and manufacturing process, and has a simple and reliable structure, low manufacturing cost, low technical ability requirements for users, and a wide range of application scenarios. It can be used in the design of a bracket that needs to achieve height difference movement.

[0040] As described above, the utility model can be implemented well.

[0041] The above is only a preferred embodiment of the utility model and does not limit the utility model in any form. According to the technical essence of the utility model, within the spirit and principles of the utility model, any simple modification, equivalent replacement and improvement made to the above embodiment still falls within the protection scope of the technical solution of the utility model.

Claims

1. A UAV fuselage bracket bidirectional folding omnidirectional wheel device, characterized in that: The invention comprises an omnidirectional wheel (7), an inverted T-shaped load-bearing steel plate (6), a first axle pin (8), a second axle pin (9), and a third axle pin (10); three axle pin holes are designed at the three end points of the inverted T-shaped load-bearing steel plate (6), namely a forward axle pin hole (1), a middle axle pin hole (2), and a rearward axle pin hole (5); three axle pin fixing ears are designed on the fuselage bracket, and a front limit stop rod (3) and a rear limit stop rod (4) are designed to match the forward axle pin hole (1), the middle axle pin hole (2), and the rearward axle pin hole (5), and are in contact with the plate surface of the inverted T-shaped load-bearing steel plate (6) of the omnidirectional wheel, so as to support the omnidirectional wheel after flipping and folding; when the omnidirectional wheel is folded forward and backward, the height difference before and after flipping is inconsistent; When the omnidirectional wheels are fully folded, the load-bearing capacity is approximately 1200kg to 1500kg.

2. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: The middle axle pin hole (2) and the corresponding fixed lug on the fuselage bracket are fixedly installed and serve as the rotation axis for the omnidirectional wheel to flip and fold forward and backward; the second axle pin (9) and the third axle pin (10) in the forward axle pin hole (1) and the backward axle pin hole (5) are quickly released and anti-dropping treatment is performed on them.

3. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 2, characterized in that: By installing and removing the axle pins (8) of the forward axle pin hole (1) and the backward axle pin hole (5), the omnidirectional wheel rotates around the middle axle pin hole (2), thereby realizing the functions of lowering and fixing the omnidirectional wheel, flipping and folding forward, and flipping and folding backward.

4. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 3, characterized in that: The second axle pin (9), the first axle pin (8) and the third axle pin (10) are installed in the three axle pin holes, namely the forward axle pin hole (1), the middle axle pin hole (2) and the rearward axle pin hole (5), so as to realize the safety and stability of the omnidirectional wheel lowering and flipping and folding bearing movement.

5. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: The front limit stop rod (3) and the rear limit stop rod (4) are mainly used to realize the backward flipping and folding stop of the omnidirectional wheel. Both are made of 50 square tube material with a thickness of 3mm. Theoretically, they can bear a force of ≮3000kg.

6. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: By adjusting the welding angle and welding height of the front limit stop rod (3), the height of the omnidirectional wheel after flipping and folding can meet the height requirement for rightward movement into the box.

7. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: By adjusting the welding angle and welding height of the rear limit stop rod (4), the height of the omnidirectional wheel after flipping and folding can meet the height requirement for rightward movement into the box.

8. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: The first shaft pin (8), the second shaft pin (9) and the third shaft pin (10) each having a diameter of about 21.5 mm can theoretically withstand a force of ≮3000 kg.

9. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: The length dimension of the transverse plate of the inverted T-shaped load-bearing steel plate (6) is reasonably designed to ensure that after the omnidirectional wheel is flipped and folded, the inverted T-shaped load-bearing steel plate (6) cannot contact the ground, thereby limiting the movement of the fuselage bracket.

10. The UAV fuselage bracket bidirectional folding omnidirectional wheel device according to claim 1, characterized in that: The fixing ear of the fuselage bracket is designed to meet the coaxiality requirements with the forward axle pin hole (1), the middle axle pin hole (2) and the rearward axle pin hole (5); the front ends of the second axle pin (9) and the third axle pin (10) are provided with a certain taper to facilitate quick installation.

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