Framework structure of unmanned aerial vehicle wing

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a skeleton structure of an unmanned aerial vehicle wing. The girder is provided with a plurality of first positioning strips and a plurality of second positioning strips; the first positioning strip is provided with a plurality of first positioning grooves; the second positioning strip is provided with a plurality of second positioning grooves; the first positioning groove is connected with a first wing rib; and the second positioning groove is connected with a second wing rib. The first positioning strip and the second positioning strip are arranged on the two sides of the girder respectively, and the first positioning strip and the second positioning strip are fixedly arranged in the girder, so that the position of the first positioning groove and the position of the second positioning groove are fixed, and when the first wing rib and the second wing rib are installed, the first wing rib and the second wing rib are fixed. The first wing rib and the second wing rib are mounted in the first positioning groove and the second positioning groove correspondingly, so that the first wing rib and the second wing rib are not prone to displacement, and the mounting accuracy of the framework of the unmanned aerial vehicle wing is improved; in addition, the first positioning strip and the second positioning strip can enhance the strength of the girder.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to a skeleton structure of unmanned plane wing. BACKGROUND

[0002] In the field of unmanned plane manufacturing, with the continuous expansion of unmanned plane application scenarios, from the conventional aerial photography, surveying and mapping, gradually extending to logistics distribution, agricultural plant protection and other diversified fields, higher requirements are put forward for the performance and stability of the unmanned plane wing. The skeleton of the unmanned plane wing, as the key support structure of the wing, the connection mode of the girder and the rib directly affects the reliability of the whole wing.

[0003] At present, in the manufacturing of the skeleton of the unmanned plane wing, the mainstream technical means is to fix the rib and the girder with glue. The traditional fixing scheme is to apply glue on the bonding surface of the girder and the rib, and then align the two by artificial or simple tool, and realize the connection by the adhesive force of the cured glue, so as to achieve the technical effect of supporting the wing shape and ensuring the structural strength of the wing.

[0004] However, due to the lack of effective positioning structure of the girder at present, the rib is prone to displacement in the process of complete curing and drying of the glue, which makes it difficult to ensure the precision of the wing skeleton in the assembly process, and further affects the aerodynamic shape of the whole wing, reduces the stability and maneuverability of the unmanned plane in flight, so that the unmanned plane cannot meet the strict requirements of actual application when facing complex airflow environment or performing high-precision flight tasks. UTILITY MODEL CONTENTS

[0005] The utility model aims at the above-mentioned deficiencies in the prior art, and provides a skeleton structure of unmanned plane wing.

[0006] The utility model aims at the above-mentioned deficiencies in the prior art, and provides a skeleton structure of unmanned plane wing.

[0007] The first positioning slot is provided with a first rib; the second positioning slot is provided with a second rib.

[0008] The utility model is further provided with the second rib being a triangular structure; the second rib is provided with a second positioning block matched with the second positioning slot; glue is arranged between the second positioning block and the second positioning slot.

[0009] The utility model further sets up, first wing rib is quadrilateral structure, one end of first wing rib is equipped with with first left positioning piece of first positioning slot draw -in joint, be equipped with glue between first left positioning piece and first positioning slot.

[0010] The utility model further sets up, first wing rib is equipped with first through -hole, second wing rib is equipped with second through -hole.

[0011] The utility model further sets up, the framework structure of unmanned aerial vehicle wing still includes auxiliary beam, one side of auxiliary beam is equipped with a plurality of third positioning strips, the other side of auxiliary beam is equipped with a plurality of fourth positioning strips, third positioning strip and fourth positioning strip all are along auxiliary beam length direction setting,

[0012] The third positioning strip is equipped with a plurality of third positioning slots along the length direction, the fourth positioning strip is equipped with a plurality of fourth positioning slots along the length direction, the fourth positioning slot is connected with third wing rib, and the first wing rib is located between first positioning slot and third positioning slot.

[0013] The utility model further sets up, third wing rib is triangular structure, third wing rib is equipped with with fourth positioning slot draw -in joint of third positioning piece, be equipped with glue between third positioning piece and fourth positioning slot.

[0014] The utility model further sets up, first wing rib is quadrilateral structure, the other end of first wing rib is equipped with with third positioning slot draw -in joint of first right positioning piece, be equipped with glue between first right positioning piece and third positioning slot.

[0015] The utility model further sets up, first positioning strip, second positioning strip and big beam are integrally formed, third positioning strip, fourth positioning strip and auxiliary beam are integrally formed.

[0016] The utility model further sets up, big beam and auxiliary beam are C type beam, and the end of big beam is equipped with connecting piece.

[0017] The utility model further sets up, the end of big beam is equipped with auxiliary strip, and the connecting piece is in abutment with auxiliary strip.

[0018] The utility model further sets up, be equipped with threading pipe between a plurality of first wing ribs.

[0019] The utility model discloses the beneficial effect: the utility model discloses a first positioning strip and second positioning strip are set up respectively in the both sides of girder, because first positioning strip and second positioning strip are fixed in girder, make the position of first positioning groove and the position of second positioning groove are fixedly change, when installing first wing rib and second wing rib, first wing rib and second wing rib are installed respectively at first positioning groove and second positioning groove, make first wing rib and second wing rib not easy to appear the condition of displacement, improve the precision of unmanned aerial vehicle wing frame installation, in addition, the setting of first positioning strip and second positioning strip can strengthen the strength of girder. BRIEF DESCRIPTION OF DRAWINGS

[0020] The embodiment in the accompanying drawings does not constitute any limitation to the utility model, and other drawings can be obtained by the following accompanying drawings without creative labor for the ordinary skilled in the art.

[0021] Figure 1 It is structural schematic diagram of the utility model embodiment 1;

[0022] Figure 2 It is structural exploded view of the utility model embodiment 1;

[0023] Figure 3 It is structural exploded view of another view of the utility model embodiment 1;

[0024] Figure 4 It is Figure 2 The local enlarged view of A part in;

[0025] Figure 5 It is structural schematic diagram of the utility model embodiment 2;

[0026] Wherein: 11, girder;12, auxiliary beam;21, first positioning strip;22, second positioning strip;23, third positioning strip;24, fourth positioning strip;31, first positioning groove;32, second positioning groove;33, third positioning groove;34, fourth positioning groove;4, first wing rib;41, first left positioning block;42, first right positioning block;43, first through hole;5, second wing rib;51, second positioning block;52, second through hole;6, third wing rib;61, third positioning block;81, connecting piece;82, auxiliary strip;9, threading pipe. DETAILED DESCRIPTION

[0027] The utility model is further described in connection with the following embodiments.

[0028] Embodiment 1, by Figures 1 to 4It can be known that the skeleton structure of the unmanned aerial vehicle wing comprises a girder 11; a plurality of first positioning strips 21 are arranged on one side of the girder 11; a plurality of second positioning strips 22 are arranged on the other side of the girder 11; the first positioning strips 21 and the second positioning strips 22 are arranged along the length direction of the girder 11;

[0029] The first positioning strip 21 is provided with a plurality of first positioning grooves 31 along the length direction; the second positioning strip 22 is provided with a plurality of second positioning grooves 32 along the length direction; the first positioning groove 31 is connected with a first wing rib 4; the second positioning groove 32 is connected with a second wing rib 5.

[0030] Specifically, the skeleton structure of the unmanned aerial vehicle wing comprises a girder 11; a plurality of first positioning strips 21 are arranged on one side of the girder 11; a plurality of second positioning strips 22 are arranged on the other side of the girder 11; the first positioning strips 21 and the second positioning strips 22 are arranged along the length direction of the girder 11;

[0031] The skeleton structure of the unmanned aerial vehicle wing comprises a girder 11; a plurality of first positioning strips 21 are arranged on one side of the girder 11; a plurality of second positioning strips 22 are arranged on the other side of the girder 11; the first positioning strips 21 and the second positioning strips 22 are arranged along the length direction of the girder 11;

[0032] The skeleton structure of the unmanned aerial vehicle wing comprises a girder 11; a plurality of first positioning strips 21 are arranged on one side of the girder 11; a plurality of second positioning strips 22 are arranged on the other side of the girder 11; the first positioning strips 21 and the second positioning strips 22 are arranged along the length direction of the girder 11;

[0033] The first wing rib 4 is provided with a first through hole 43; the second wing rib 5 is provided with a second through hole 52. Through the above setting, longitudinal wing ribs can be arranged between the plurality of first wing ribs 4, and longitudinal wing ribs can be arranged between the plurality of second wing ribs 5, so as to strengthen the overall strength.

[0034] The skeleton structure of the unmanned aerial vehicle wing further comprises an auxiliary beam 12; one side of the auxiliary beam 12 is provided with a plurality of third positioning strips 23; the other side of the auxiliary beam 12 is provided with a plurality of fourth positioning strips 24; the third positioning strip 23 and the fourth positioning strip 24 are arranged along the length direction of the auxiliary beam 12;

[0035] The third positioning strip 23 is provided with a plurality of third positioning grooves 33 along the length direction; the fourth positioning strip 24 is provided with a plurality of fourth positioning grooves 34 along the length direction; the fourth positioning groove 34 is connected with the third wing rib 6; the first wing rib 4 is arranged between the first positioning groove 31 and the third positioning groove 33.

[0036] Specifically, the third positioning strip 23 and the fourth positioning strip 24 are arranged on both sides of the auxiliary beam 12 respectively, and the third positioning groove 33 and the fourth positioning groove 34 are fixedly arranged in the auxiliary beam 12, so that the first wing rib 4 and the third wing rib 6 are arranged in the third positioning groove 33 and the fourth positioning groove 34 respectively when the first wing rib 4 and the third wing rib 6 are installed, so that the first wing rib 4 and the third wing rib 6 are not easy to displace, and the precision of the skeleton installation of the unmanned aerial vehicle wing is improved.

[0037] The skeleton structure of the unmanned aerial vehicle wing, the third wing rib 6 is a triangular structure; the third wing rib 6 is provided with a third positioning block 61 which is connected with the fourth positioning groove 34; the third positioning block 61 and the fourth positioning groove 34 are connected by glue.

[0038] Specifically, through the action of the third positioning block 61 and the fourth positioning groove 34, the positioning between the third wing rib 6 and the auxiliary beam 12 is accurate, and the third wing rib 6 can be stably fixed on the auxiliary beam 12 by glue; the triangular structure of the third wing rib 6 can make the formed unmanned aerial vehicle wing have good flight performance.

[0039] The first wing rib 4 is a quadrilateral structure, one end of the first wing rib 4 is provided with the first left positioning block 41 which is connected with the first positioning slot 32, and the other end of the first wing rib 4 is provided with the first right positioning block 42 which is connected with the third positioning slot 33. Specifically, through the first left positioning block 41 and the first right positioning block 42, the first wing rib 4 and the auxiliary beam 12 are positioned accurately, and the first wing rib 4 is stably fixed on the auxiliary beam 12 through the glue.

[0040] The first positioning strip 21, the second positioning strip 22 and the girder 11 are integrally formed, and the third positioning strip 23, the fourth positioning strip 24 and the auxiliary beam 12 are integrally formed. When producing, the first positioning strip 21 and the second positioning strip 22 are put into the girder 11 forming die, so that when the girder 11 is formed, the first positioning strip 21 and the second positioning strip 22 are integrally formed in the girder 11, and the stability of the overall structure is enhanced. Similarly, when producing, the third positioning strip 23 and the fourth positioning strip 24 are put into the auxiliary beam 12 forming die, so that when the auxiliary beam 12 is formed, the third positioning strip 23 and the fourth positioning strip 24 are integrally formed in the auxiliary beam 12, and the stability of the overall structure is enhanced.

[0041] The girder 11 and the auxiliary beam 12 are both C-shaped beams, which makes the overall structure stable and reliable. The end of the girder 11 is provided with a connecting piece 81, which is convenient for connecting with the remaining structure of the unmanned aerial vehicle.

[0042] The end of the girder 11 is provided with an auxiliary strip 82, and the connecting piece 81 abuts against the auxiliary strip 82. Specifically, the cross-sectional shape of the end of the girder 11 is irregular, and the cross-sectional shape of the connecting piece 81 is rectangular. By providing the auxiliary strip 82, the cross-sectional shape of the end of the girder 11 is formed into a rectangular shape which matches the cross-sectional shape of the connecting piece 81.

[0043] Embodiment 2, as Figure 5 shown, is different from embodiment 1. The skeleton structure of the unmanned aerial vehicle wing of the embodiment is provided with a wire pipe 9 between the plurality of first wing ribs 4. Through the above-mentioned arrangement, the wire processing is facilitated.

[0044] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, and are not limited to the scope of the present application. Although the present application has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present application can be modified or replaced by equivalents without departing from the essence and scope of the technical solutions of the present application.

Claims

1. A skeleton structure of a drone wing, characterized by: The utility model provides a kind of skeleton structure of unmanned aerial vehicle wing, including girder (11);The one side of the girder (11) is equipped with multiple first positioning strips (21);The other side of the girder (11) is equipped with multiple second positioning strips (22);The first positioning strip (21) and second positioning strip (22) are all arranged along the length direction of girder (11); The first positioning strip (21) is equipped with multiple first positioning grooves (31) along length direction;The second positioning strip (22) is equipped with multiple second positioning grooves (32) along length direction;The first positioning groove (31) is connected with first wing rib (4);The second positioning groove (32) is connected with second wing rib (5).

2. The skeleton structure of a wing of a UAV according to claim 1, characterized in that: The second wing rib (5) is triangular structure;The second wing rib (5) is equipped with the second positioning block (51) of second positioning groove (32) clamping;Between the second positioning block (51) and second positioning groove (32), glue is equipped.

3. The skeleton structure of a wing of a UAV according to claim 1, characterized in that: The first wing rib (4) is quadrilateral structure;One end of the first wing rib (4) is equipped with the first left positioning block (41) of first positioning groove (31) clamping;Between the first left positioning block (41) and first positioning groove (31), glue is equipped.

4. The skeleton structure of a wing of a UAV according to claim 1, characterized in that: The first wing rib (4) is equipped with first through hole (43) through;The second wing rib (5) is equipped with second through hole (52) through.

5. The skeleton structure of a wing of a UAV according to claim 1, characterized in that: The skeleton structure of unmanned aerial vehicle wing further includes auxiliary beam (12);One side of the auxiliary beam (12) is equipped with multiple third positioning strips (23);The other side of the auxiliary beam (12) is equipped with multiple fourth positioning strips (24);The third positioning strip (23) and fourth positioning strip (24) are all arranged along the length direction of auxiliary beam (12); The third positioning strip (23) is equipped with multiple third positioning grooves (33) along length direction;The fourth positioning strip (24) is equipped with multiple fourth positioning grooves (34) along length direction;The fourth positioning groove (34) is connected with third wing rib (6);The first wing rib (4) is arranged between first positioning groove (31) and third positioning groove (33).

6. The skeleton structure of a wing of a UAV according to claim 5, characterized in that: The third wing rib (6) is triangular structure;The third wing rib (6) is equipped with the third positioning block (61) of fourth positioning groove (34) clamping;Between the third positioning block (61) and fourth positioning groove (34), glue is equipped.

7. The skeleton structure of a wing of a UAV according to claim 5, characterized in that: The first wing rib (4) is quadrilateral structure;The other end of the first wing rib (4) is equipped with the first right positioning block (42) of third positioning groove (33) clamping;Between the first right positioning block (42) and third positioning groove (33), glue is equipped.

8. The skeleton structure of a wing of a UAV according to claim 5, characterized in that: The first positioning strip (21), second positioning strip (22) and girder (11) are integrally formed;The third positioning strip (23), fourth positioning strip (24) and auxiliary beam (12) are integrally formed.

9. The skeleton structure of a wing of a UAV according to claim 5, characterized in that: The girder (11) and auxiliary beam (12) are both C-shaped beams;The end of the girder (11) is equipped with connecting piece (81); The end of the girder (11) is equipped with auxiliary strip (82);The connecting piece (81) and auxiliary strip (82) abut.

10. The skeleton structure of a wing of a UAV according to claim 1, characterized in that: Multiple first wing ribs (4) are equipped with threading pipe (9).

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