Loading structure of empennage of unmanned aerial vehicle

Abstract

The utility model relates to the technical field of storage and transportation equipment of empennages of unmanned aerial vehicles, in particular to a loading structure of an empennage of an unmanned aerial vehicle, which comprises two frame bodies arranged at an interval, and the interval between the two frame bodies forms an accommodating space of an empennage body; each frame body comprises an upper cross beam and a lower cross beam which are vertically arranged at an interval, and an oblique beam is jointly welded at the front ends of the upper cross beam and the lower cross beam; a plurality of supporting plates are welded between the lower cross beams of the two frame bodies; a plurality of empennage fixing plates are mounted between the oblique beams of the two frame bodies through screws; and a trailing edge mounting plate and a trailing edge middle supporting plate are mounted between the upper cross beams of the two frame bodies through screws. The loading structure provided by the utility model is simple in structure, can load the empennage body and the tail edge of the wing at the same time, and effectively improves the loading efficiency. The loading structure is used for loading the empennage body and the tail edge of the wing, so that the whole can be conveniently put into a container for transportation.

Description

Technical Field

[0001] The utility model relates to the technical field of storage and transportation equipment for unmanned aerial vehicle (UAV) tail wings, and in particular to a loading structure for the UAV tail wing. Background Art

[0002] For large drones, during transportation and transshipment, it is often necessary to remove the wings and tail of the drone from the fuselage, and then place them on a bracket. The bracket with the wings, tail and fuselage is then placed in a container and transported using a flatbed truck.

[0003] like Figure 1 、 Figure 2 As shown, for a certain type of drone, the disassembled tail structure includes the tail body 100 and the wing trailing edge 200. The tail body 100 is only provided with a fixing hole plate 101 at the front end for fixing. The wing trailing edge 200 has a triangular connecting lug 201 near the bottom of the front end, with a flat bottom. Since both the tail body 100 and the wing trailing edge 200 are of irregular shapes, how to load them for transportation after they are removed from the drone is a pressing issue. Utility Model Content

[0004] The main purpose of the utility model is to provide a loading structure for the tail wing of a UAV, aiming to solve the above-mentioned technical problems.

[0005] To achieve the above-mentioned purpose, the utility model proposes a loading structure for the tail of an unmanned aerial vehicle, comprising two frame bodies spaced apart from each other, the space between the two frame bodies forming an accommodating space for the tail body; each frame body comprises an upper crossbeam and a lower crossbeam spaced apart from each other, an oblique beam being welded to the front end of the upper crossbeam and the lower crossbeam; a plurality of support plates are welded between the lower crossbeams of the two frame bodies; a plurality of tail fixing plates are installed between the oblique beams of the two frame bodies by screws; a tail edge mounting plate and a tail edge middle support plate are installed between the upper crossbeams of the two frame bodies by screws.

[0006] Preferably, the number of the support plates is at least three, and a concave block is provided on the top surface of each support plate, and a concave support groove is provided on the top surface of the concave block.

[0007] Preferably, a vibration-damping pad is bonded to the concave supporting groove of the concave block.

[0008] Preferably, the frame body also includes multiple vertical rods and multiple first diagonal bracing rods; the multiple vertical rods are arranged in parallel and spaced apart, the upper ends of the vertical rods are welded to the upper cross beam, and the lower ends are welded to the lower cross beam; a diagonal bracing rod is arranged between two adjacent vertical rods; the upper end of the diagonal bracing rod is welded to the intersection of one of the vertical rods and the upper cross beam, and the lower end is welded to the intersection of the other vertical rod and the lower cross beam.

[0009] Preferably, connecting rods are welded between the front and rear ends of the lower cross beams of the two frame bodies; multiple connecting rods are welded between the vertical rods at the rear ends of the two frame bodies; and multiple connecting rods are welded between the rear ends of the upper cross beams of the two frame bodies.

[0010] Preferably, the middle part of the tail wing fixing plate protrudes to form a boss, and the two end surfaces of the boss form limiting surfaces for clamping between the oblique beams of the two frame bodies; the two ends of the boss extend to form edge plates, which are used to rest on the oblique beams and be screwed to the oblique beams.

[0011] Preferably, an adjustment pad is provided between the edge plate and the oblique beam.

[0012] Preferably, a recessed groove is provided on the top surface of the trailing edge mounting plate for supporting the connecting ear plate of the wing trailing edge, and a threaded hole is provided on the bottom of the recessed groove; a limiting slot is provided on the top surface of the trailing edge support plate for supporting and clamping at the middle position of the bottom of the wing trailing edge; a trailing edge rear support plate is also installed between the upper cross beams of the two frame bodies by screws, and the trailing edge rear support plate is used to be supported on the bottom surface of the rear part of the wing trailing edge and is screwed to the wing trailing edge.

[0013] Preferably, a bearing support plate is welded on the lower cross beam, and a rolling bearing is rollingly mounted on the bearing support plate; the bearing support plate and the rolling bearing are connected by an axle pin; the axle pin passes through the rolling bearing and the bearing support plate in sequence and is screwed with a nut; a cotter pin is provided between the nut and the axle pin.

[0014] Preferably, the loading structure further includes a locking block having an arc-shaped clamping portion and a bolt mounting portion, the arc-shaped clamping portion is provided with an arc-shaped surface for clamping on the outer peripheral surface of the rolling bearing; the bolt mounting portion is provided with a bolt through hole.

[0015] Due to the adoption of the above technical solution, the beneficial effects of the utility model are as follows:

[0016] (1) When loading the tail body and the wing trailing edge, the tail body can be placed in the gap between the two frame bodies, and the support plate is used to support the bottom edge of the tail body. At the same time, the tail fixing plate is screwed to the fixing hole plate of the tail body, and the tail body can be fixedly loaded in the loading structure. At the same time, by using the trailing edge mounting plate to support the connecting ear plate of the wing trailing edge, and the trailing edge mounting plate is screwed to the connecting ear plate of the wing trailing edge, and the trailing edge middle support plate is supported at the middle position of the bottom surface of the wing trailing edge, the wing trailing edge can be fixedly mounted on the loading structure. By adopting the loading structure provided by the utility model, it is convenient to load the tail body and the wing trailing edge removed from the drone, and by using the loading structure to load the tail body and the wing trailing edge, it is convenient to put the whole into a container for transportation.

[0017] (2) The loading structure provided by the present invention is simple in structure and can load the tail body and the wing trailing edge at the same time, thereby effectively improving the loading efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0019] Figure 1 Schematic diagram of the structure of the tail body;

[0020] Figure 2 is a structural diagram of the wing trailing edge;

[0021] Figure 3 This is an exploded schematic diagram of the loading structure for fixing the tail of a UAV provided by the present invention;

[0022] Figure 4 for Figure 3 Enlarged view of point A in the middle;

[0023] Figure 5 Schematic diagram of the loading structure for fixing the tail of the UAV provided by the utility model Figure 1 ;

[0024] Figure 6 Schematic diagram of the loading structure for fixing the tail of the UAV provided by the utility model Figure 2 ;

[0025] Figure 7 This is a schematic structural diagram of the tail wing fixing plate in the present invention;

[0026] Figure 8 This is a schematic structural diagram of the trailing edge mounting plate in the present invention;

[0027] Figure 9 This is a schematic structural diagram of the trailing edge support plate in the present invention;

[0028] Figure 10 It is a structural diagram of the vibration damping pad in the utility model;

[0029] Figure 11 It is a structural diagram of the axle pin in the utility model;

[0030] Figure 12 This is a schematic structural diagram of the locking block in the present invention;

[0031] Figure 13 This is a schematic diagram of the loading structure proposed in the present invention after loading the tail body and the wing trailing edge. Figure 1 ;

[0032] Figure 14 for Figure 13 Enlarged view of point B in the middle;

[0033] Figure 15 This is a schematic diagram of the loading structure proposed in the present invention after loading the tail body and the wing trailing edge. Figure 2 ;

[0034] Figure 16 for Figure 15 Enlarged view of point C in the middle.

[0035] Explanation of the accompanying numbers: 1. Tail; 1a. Upper crossbeam; 1b. Lower crossbeam; 1c. Oblique beam; 1d. Vertical rod; 1e. First oblique support rod; 1f. Second oblique support rod; 2. Support plate; 3. Tail fixing plate; 3a. Boss; 3b. Edge plate; 4. Trailing edge mounting plate; 4a. Groove; 5. Middle support plate of trailing edge; 5a. Limiting slot; 6. Rear support plate of trailing edge; 7. Concave block; 8. Vibration damping pad; 9. Connecting rod; 10. Adjusting pad; 11. Bearing support plate; 12. Rolling bearing; 13. Axle pin; 14. Nut; 15. Split pin; 16. Locking block; 16a. Arc-shaped clamping portion; 16b. Bolt mounting portion; 100. Tail body; 101. Fixing hole plate; 200. Wing trailing edge; 201. Connecting ear plate. DETAILED DESCRIPTION

[0036] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0037] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0038] In addition, the descriptions of "first," "second," etc. in this utility model are for descriptive purposes only and should not be understood as indicating or implying their relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of such features. In addition, the technical solutions between the various embodiments can be combined with each other, but this must be based on the fact that they can be implemented by ordinary technicians in this field. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this utility model.

[0039] Combine Figures 3 to 16 As shown, a loading structure of a UAV tail wing includes two frame bodies 1 spaced apart from each other, and the gap between the two frame bodies 1 forms an accommodating space for the tail wing body 100; each frame body 1 includes an upper crossbeam 1a and a lower crossbeam 1b spaced apart from each other, and an oblique beam 1c is welded to the front end of the upper crossbeam 1a and the lower crossbeam 1b; a plurality of support plates 2 are welded between the lower crossbeams 1b of the two frame bodies 1, and the support plates 2 are used to support the bottom edge of the tail wing body 100; a plurality of tail wing fixing plates 3 are installed between the oblique beams 1c of the two frame bodies 1 by screws, and the tail wing fixing plates 3 are used to be screwed to the fixing hole plates 101 of the tail wing body 100; a trailing edge mounting plate 4 and a trailing edge middle support plate 5 are installed between the upper crossbeams 1a of the two frame bodies 1 by screws, and the trailing edge mounting plate 4 is used to support the connecting ear plate 201 of the wing trailing edge 200 and is screwed to the connecting ear plate 201; the trailing edge middle support plate 5 is used to be supported at the middle position of the bottom surface of the wing trailing edge 200.

[0040] Combine Figures 13 to 16As shown, by adopting the above structure, when loading the tail body 100 and the wing trailing edge 200, first remove the trailing edge mounting plate 4, the trailing edge middle support plate 5 and the tail fixing plate 3. At this time, the upper part and the front end of the entire loading structure are open, which is convenient for hoisting the tail body 100 into the gap between the two frame bodies 1. When the tail body 100 is placed in the gap between the two frame bodies 1, the support plate 9 supports the bottom of the tail body 100, adjust the position of the tail body 100, connect and fix the tail fixing plate 3 with the fixing hole plate 101 on the tail body 100 with screws, and then fix the two ends of the tail fixing plate 3 to the inclined beam 1c with screws. At this point, the loading and fixation of the tail body 100 is completed. The trailing edge mounting plate 4 and the trailing edge middle support plate 5 are then screwed to the upper crossbeams 1a of the two frame bodies 1. The wing trailing edge 200 is then loaded. The connecting lug 201 of the wing trailing edge 200 is placed on the trailing edge mounting plate 4 and screwed in. The trailing edge middle support plate 5 is then supported at the center of the bottom surface of the wing trailing edge 200. This secures the wing trailing edge 200 to the loading structure. Once the empennage body 100 and the wing trailing edge 200 are loaded onto the loading structure, the resulting structure can be placed in a container for transportation.

[0041] Combine Figure 3 、 Figure 5 As shown, to better support the empennage body 100, the support plates 2 are at least three in number. Each support plate 2 is provided with a concave block 7 on its top surface. Each concave block 7 has a concave support groove on its top surface, which supports and engages with the lower edge of the empennage body 100, providing excellent support. Furthermore, to prevent rigid contact between the empennage body 100 and the concave block 7 and to protect the empennage body 100, a vibration-damping pad 8 is bonded to the concave support groove of the concave block 7.

[0042] Combine Figure 3 、 Figure 5As shown, the frame body 1 also includes multiple vertical rods 1d and multiple first diagonal braces 1e and second diagonal braces 1f. The multiple vertical rods 1d are arranged in parallel and spaced apart, with the upper ends of the vertical rods 1d welded to the upper crossbeam 1a and the lower ends welded to the lower crossbeam 1b. A diagonal brace 1e is provided between two adjacent vertical rods 1d. The upper end of the diagonal brace 1e is welded to the intersection of one vertical rod 1d and the upper crossbeam 1a, and the lower end is welded to the intersection of the other vertical rod 1d and the lower crossbeam 1b. The upper portion of the diagonal beam 1c extends beyond the upper crossbeam 1a. To increase stability, a second diagonal brace 1f is welded between the top of the diagonal beam 1c and the upper crossbeam 1a. The use of the vertical rods 1d, the first diagonal brace 1e, and the second diagonal brace 1f makes the entire frame body 1 more stable. Furthermore, in order to increase the stability of the entire loading structure, connecting rods 9 are welded between the front and rear ends of the lower cross beams 1b of the two frame bodies 1; multiple connecting rods 9 are welded between the vertical rods 1d at the rear ends of the two frame bodies 1; and multiple connecting rods 9 are welded between the rear ends of the upper cross beams 1a of the two frame bodies 1.

[0043] Combine Figure 7 As shown, the center of the tail wing fixing plate 3 protrudes to form a boss 3a, and the two end surfaces of the boss 3a form limiting surfaces for clamping between the oblique beams 1c of the two frame bodies 1. The two ends of the boss 3a extend to form edge plates 3b, which are used to rest on the oblique beams 1c and are screwed to the oblique beams 1c. When loading the tail wing body 100, the tail wing fixing plate 3 is first connected and fixed to the fixing hole plate 101 on the tail wing body 100 via screws. To facilitate the screw connection of the tail wing fixing plate 3 and the oblique beam 1c, an adjustment washer 10 is provided between the edge plate 3b and the oblique beam 1c. By using adjustment washer 10 of different thicknesses, the screw connection between the tail wing fixing plate 3 and the oblique beam 1c is facilitated.

[0044] Combine Figure 8 、 Figure 14 As shown, a recessed groove 4a is provided on the top surface of the trailing edge mounting plate 4 for supporting the connecting ear plate 201 of the wing trailing edge 200, and a threaded hole is provided on the bottom of the recessed groove 4a. When the connecting ear plate 201 is placed on the recessed groove 4a of the trailing edge mounting plate 4, the screw passes through the connecting ear plate 201 and is screwed into the threaded hole of the recessed groove 4a to fix it.

[0045] Combine Figure 8 and Figure 13 、 Figure 15 As shown, a limiting slot 5a is provided on the top surface of the trailing edge support plate 5 for supporting and clamping at the bottom middle position of the wing trailing edge 200. The limiting slot 5a plays a limiting role for the wing trailing edge 200.

[0046] Combine Figure 3、 Figure 5 、 Figure 15 and Figure 16 As shown, in order to better support the wing trailing edge 200, a trailing edge rear support plate 6 is also installed between the upper cross beams 1a of the two frame bodies 1 by screws. The trailing edge rear support plate 6 is used to support the bottom surface of the rear part of the wing trailing edge 200 and is screwed to the wing trailing edge 200.

[0047] Combine Figure 3 、 Figure 4 and Figure 11 As shown, a bearing support plate 11 is welded to the lower crossbeam 1b, on which a rolling bearing 12 is rollingly mounted. The bearing support plate 11 and the rolling bearing 12 are connected by a shaft pin 13. The shaft pin 13 passes through the rolling bearing 12 and the bearing support plate 11 in sequence, and then is screwed onto a nut 14. A cotter pin 15 is provided between the nut 14 and the shaft pin 13. The installation of the rolling bearing 12 facilitates the sliding of the entire loading structure inside the container when it is loaded.

[0048] Combine Figure 3 、 Figure 4 and Figure 12 As shown, the loading structure also includes a locking block 16, which has an arcuate engaging portion 16a and a bolt mounting portion 16b, with bolt holes provided on the bolt mounting portion 16b. Once the loading structure is moved to a designated position within the container, the locking block 16 is used to lock the entire loading structure. Specifically, the bolt mounting portion 16b is bolted to the container, while the arcuate engaging portion 16a has an arcuate surface for engaging with the outer circumferential surface of the rolling bearing 12 to achieve locking.

[0049] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. All equivalent structural transformations made based on the concept of the present invention and the contents of the present invention description and drawings, or direct / indirect application in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A loading structure for a UAV tail wing, characterized by: The invention comprises two frame bodies (1) spaced apart from each other, wherein the space between the two frame bodies (1) forms a space for accommodating a tail wing body (100); each frame body (1) comprises an upper crossbeam (1a) and a lower crossbeam (1b) spaced apart from each other, and an oblique beam (1c) is welded to the front ends of the upper crossbeam (1a) and the lower crossbeam (1b); A plurality of support plates (2) are welded between the lower cross beams (1b) of the two frame bodies (1); A plurality of tail wing fixing plates (3) are installed between the oblique beams (1c) of the two frame bodies (1) by screws; A trailing edge mounting plate (4) and a trailing edge middle supporting plate (5) are mounted between the upper cross beams (1a) of the two frame bodies (1) by means of screws.

2. The UAV tail wing loading structure according to claim 1, characterized in that: The number of the support plates (2) is at least three, and a concave block (7) is provided on the top surface of each support plate (2), and a concave support groove is provided on the top surface of the concave block (7).

3. The UAV tail wing loading structure according to claim 2, characterized in that: A vibration-damping pad (8) is bonded to the concave supporting groove of the concave block (7).

4. The UAV tail wing loading structure according to claim 1, characterized in that: The frame body (1) further comprises a plurality of vertical rods (1d) and a plurality of first diagonal bracing rods (1e); A plurality of vertical rods (1d) are arranged in parallel and at intervals, the upper ends of the vertical rods (1d) are welded to the upper crossbeam (1a), and the lower ends of the vertical rods (1d) are welded to the lower crossbeam (1b); An oblique support rod (1e) is provided between two adjacent vertical rods (1d); the upper end of the oblique support rod (1e) is welded to the intersection of one of the vertical rods (1d) and the upper crossbeam (1a), and the lower end is welded to the intersection of the other vertical rod (1d) and the lower crossbeam (1b).

5. The UAV tail wing loading structure according to claim 4, characterized in that: Connecting rods (9) are respectively welded between the front and rear ends of the lower cross beams (1b) of the two frame bodies (1); A plurality of connecting rods (9) are welded between the vertical rods (1d) at the rear ends of the two frame bodies (1); A plurality of connecting rods (9) are welded between the rear end portions of the upper cross beams (1a) of the two frame bodies (1).

6. The UAV tail wing loading structure according to claim 1, characterized in that: The middle part of the tail wing fixing plate (3) protrudes to form a boss (3a), and the two end surfaces of the boss (3a) form limiting surfaces for clamping between the oblique beams (1c) of the two frame bodies (1); the two ends of the boss (3a) extend to form edge plates (3b), and the edge plates (3b) are used to be placed on the oblique beams (1c) and are screwed to the oblique beams (1c).

7. The UAV tail wing loading structure according to claim 6, characterized in that: An adjustment pad (10) is provided between the edge plate (3b) and the oblique beam (1c).

8. The UAV tail wing loading structure according to claim 1, characterized in that: A bearing support plate (11) is welded on the lower cross beam (1b), and a rolling bearing (12) is rolling-mounted on the bearing support plate (11); the bearing support plate (11) and the rolling bearing (12) are connected via an axle pin (13); the axle pin (13) passes through the rolling bearing (12) and the bearing support plate (11) in sequence and is then screwed with a nut (14); a cotter pin (15) is provided between the nut (14) and the axle pin (13).

9. The UAV tail wing loading structure according to claim 8, characterized in that: The locking block (16) is also included. The locking block (16) has an arc-shaped clamping portion (16a) and a bolt mounting portion (16b). The arc-shaped clamping portion (16a) is provided with an arc-shaped surface for clamping onto the outer peripheral surface of the rolling bearing (12); and the bolt mounting portion (16b) is provided with a bolt through hole.

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