A wing quick release mechanism and aircraft

Abstract

The utility model discloses a kind of wing quick-release mechanism and aircraft, wing quick-release mechanism includes: inner wing mounting seat and outer wing mounting seat;Two ends of inner wing mounting seat are respectively provided with butt joint tenon, first connecting hole is provided on butt joint tenon;Two ends of outer wing mounting seat are respectively provided with butt joint groove, first fixed boss and second fixed boss are provided with on butt joint groove two sides;Butt joint tenon and butt joint groove are fixed to an entity with inner wing mounting seat and outer wing mounting seat;When butt joint tenon is clamped in butt joint groove, first bolt is inserted first fixed boss and is inserted in one end of first connecting hole, second bolt is inserted second fixed boss and is inserted in the other end of first connecting hole.The utility model is fixed to an entity with inner wing mounting seat and outer wing mounting seat by setting butt joint tenon and clamping groove, by accurate cooperation of butt joint tenon and clamping groove, reduce the butt joint difficulty of inner and outer wing, simultaneously, reduce butt joint time.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a wing quick-release mechanism and an aircraft. Background Technology

[0002] With the increasing maturity of civil aircraft technology, their applications are widely used in aerial photography / surveillance, power line inspection, environmental protection, agriculture, logistics and transportation, and other fields. In particular, with the rapid development of the low-altitude economy, large-wingspan aircraft (wingspan greater than 10 meters) have become very common. Due to the diversification of aircraft application scenarios and the high frequency of switching between different usage scenarios, aircraft need to be disassembled and transported frequently in different usage scenarios, making the disassembly and assembly of large-wingspan wings a routine practice.

[0003] The docking structure of the inner and outer wings generally uses two pairs of docking joints connected front and rear, and is fixed by bolts and nuts. Because the docking structure needs to transfer the load requirements of the outer wing, the docking bolts and bolt holes of the joints generally adopt a high-precision small-clearance fit method. During installation, the outer wing joint is docked with the inner wing joint, and after the docking bolt holes are aligned, the bolts are inserted and tightened. However, this method makes the docking of the inner and outer wings difficult and time-consuming. Utility Model Content

[0004] The purpose of this utility model is to overcome the shortcomings of the prior art. This utility model provides a quick-release wing mechanism and aircraft. By setting a docking tenon and a snap-fit ​​groove, the difficulty of docking the inner and outer wings is reduced and the docking time is reduced through the precise cooperation of the docking tenon and the snap-fit ​​groove.

[0005] Accordingly, this utility model proposes a quick-release wing mechanism, which includes: an inner wing mounting base and an outer wing mounting base; The inner wing mounting base is provided with tenons at both ends, and a first connecting hole is provided on the tenon, the first connecting hole passing through the tenon; The outer wing mounting base is provided with mating grooves at both ends that mate with the mating tenon, and a first fixing boss and a second fixing boss are provided on both sides of the mating groove. The mating tenon and the mating groove fix the inner wing mounting base and the outer wing mounting base together based on the first bolt and the second bolt; When the tenon is engaged with the groove, the first bolt is inserted into the first fixing boss and inserted at one end of the first connecting hole, and the second bolt is inserted into the second fixing boss and inserted at the other end of the first connecting hole.

[0006] Preferably, the tenon has a first positioning pin hole on its engagement surface, into which a positioning pin is inserted, and the groove has a second positioning pin hole that mates with the positioning pin on its engagement surface, with the other end of the positioning pin inserted into the second positioning pin hole.

[0007] Preferably, the first bolt is an externally threaded bolt, and the second bolt is an internally threaded bolt, with the first bolt and the second bolt engaging with each other based on their threads.

[0008] Preferably, the mating tenon has a limiting groove on its snap-fit ​​surface that mates with the first fixing boss or the second fixing boss. The inner walls of the limiting grooves form arc surfaces at their joints.

[0009] Preferably, a plurality of first fixing holes that mate with the first connecting hole are provided on one side of the outer wing mounting base; The first fixing hole extends inward to form a first limiting boss.

[0010] Preferably, a plurality of second fixing holes that mate with the first connecting hole are provided on the other side of the outer wing mounting base; The second fixing hole extends inward to form a second limiting boss.

[0011] Preferably, the inner wing mounting base is provided with a plurality of first mounting shells, and the plurality of first mounting shells are distributed symmetrically based on the center of the inner wing mounting base.

[0012] Preferably, the outer wing mounting base is provided with a plurality of second mounting shells, which are distributed symmetrically about the center of the outer wing mounting base.

[0013] Preferably, the inner wing mounting base is provided with a plurality of first reinforcing ribs arranged in a crisscross pattern.

[0014] This utility model also proposes an aircraft, which includes the above-mentioned wing quick-release mechanism, multiple outer wings and multiple inner wings, wherein one of the multiple outer wings and one of the multiple inner wings are detachably connected based on one of the wing quick-release mechanisms.

[0015] The beneficial effects of this utility model are: This invention features a tenon and a groove for docking. The precise fit between the tenon and the groove ensures that when the tenon is subjected to external force, its rotation is blocked by the outer wing mounting seat, effectively limiting the rotation of the tenon and consequently restricting the relative rotation between the outer and inner wing mounting seats. Furthermore, this invention incorporates locating pins in the inner and outer wing mounting seats. The precise fit between the locating pins and their holes allows for adjustment of the outer wing position only along the axial direction of the locating pins, reducing the difficulty and time required for docking the inner and outer wings. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a front view of the quick-release wing mechanism in this utility model; Figure 2 This is a cross-sectional view of the quick-release wing mechanism in this utility model; Figure 3 This is the first exploded view of the quick-release wing mechanism in this utility model; Figure 4 This is the second exploded view of the quick-release wing mechanism in this utility model.

[0018] In the attached diagram: 1. Inner wing mounting base; 11. Docking tenon; 111. First locating pin hole; 112. First connecting hole; 113. Limiting groove; 12. Mounting shell; 13. First reinforcing rib; 2. Outer wing mounting base; 21. Docking groove; 211. Second locating pin hole; 212. Limiting boss; 22. First fixing hole; 221. First fixing boss; 23. Second fixing hole; 231. Second fixing boss; 24. Second mounting shell; 25. Second reinforcing rib; 3. Locating pin; 4. First bolt; 5. Second bolt. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0020] Figure 1The front view of the wing quick-release mechanism of this utility model is shown. Figure 2 A cross-sectional view of the wing quick-release mechanism of this invention is shown. Figure 3 The first exploded view of the wing quick-release mechanism of this utility model is shown. Figure 4 The second exploded view of the wing quick-release mechanism of this utility model is shown. The wing quick-release mechanism includes: an inner wing mounting base 1 and an outer wing mounting base 2; the inner wing mounting base 1 is provided with tenons 11 at both ends, and a first connecting hole 112 is provided on the tenon 11, the first connecting hole 112 penetrating the tenon 11; the outer wing mounting base 2 is provided with grooves 21 at both ends that mate with the tenons 11, and a first fixing boss 221 and a second fixing boss 231 are provided on both sides of the grooves 21; the tenons 11 and the grooves 21 are fixed together by a first bolt 4 and a second bolt 5; when the tenons 11 are engaged with the grooves 21, the first bolt 4 is inserted into the first fixing boss 221 and inserted into one end of the first connecting hole 112, and the second bolt 5 is inserted into the second fixing boss 231 and inserted into the other end of the first connecting hole 112. In this embodiment, the inner wing mounting base 1 is provided with two tenons 11, which are respectively located at both ends of the inner wing mounting base 1. The outer wing mounting base 2 has two corresponding mating grooves 21. The first connecting hole 112 passes through the tenon 11 along its first axis. This first axis is parallel to the first fixing boss 221 and the second fixing boss 231, and is located at the center of the mounting surface of the tenon 11. When the tenon 11 is engaged in the locking groove, the first bolt 4 passes through the first fixing boss 221 and is inserted into the first connecting hole 112, and the second bolt 5 passes through the second fixing boss 231 and is inserted into the first connecting hole 112. This means that the outer wing mounting base 2 and the inner wing mounting base 1 are locked from two directions, avoiding the risk of the outer wing mounting base 2 detaching from the inner wing mounting base 1 during use. This reduces the difficulty of mating the inner wing mounting base 1 and the outer wing mounting base 2, and also reduces the mating time.

[0021] It should be noted that the mating groove 21 has a first fixing hole 22 at the location of the first fixing boss 221. The first fixing hole 22 penetrates one side wall of the mating groove 21, ensuring that the first bolt 4 can pass through the first fixing hole 22, pass through the first fixing boss 221, and finally be inserted into the first connecting hole 112. Similarly, the mating groove 21 has a second fixing hole 23 at the location of the second fixing boss 231. The second fixing hole 23 penetrates one side wall of the mating groove 21, ensuring that the second bolt 5 can pass through the second fixing hole 23, pass through the second fixing boss 231, and finally be inserted into the first connecting hole 112.

[0022] Furthermore, the tenon 11 has a first positioning pin hole 111 on its engagement surface, into which a positioning pin 3 is inserted. The groove 21 has a second positioning pin hole 211 on its engagement surface, which mates with the positioning pin 3. The other end of the positioning pin 3 is inserted into the second positioning pin hole 211. When the components are joined, the tenon is inserted into the groove, making the engagement surfaces of the two parts in close contact. At this time, the positions of the first positioning pin hole 111 and the second positioning pin hole 211 correspond. Then, the positioning pin 3 is inserted into the first positioning pin hole 111 and the second positioning pin hole 211. Due to the tight fit between the positioning pin 3 and the two positioning pin holes, the relative movement between the tenon and the groove is restricted, keeping them relatively stationary. This achieves a precise and stable connection between the components, which helps to make the connection between the inner wing mounting base and the outer wing mounting base more accurate, reduces failures and damage caused by loose connections, and improves the overall structural quality and service life. Furthermore, the first bolt 4 is an externally threaded bolt, and the second bolt 5 is an internally threaded bolt. The first bolt 4 and the second bolt 5 are interlocked based on their threads. In this embodiment, the first bolt 4 and the second bolt 5 are coupled, that is, the externally threaded connecting end of the first bolt 4 is screwed into the internally threaded connecting end of the second bolt 5. The external and internal threads interlock, increasing the friction and stability of the connection, allowing the connection part of the first bolt 4 and the second bolt 5 to withstand greater tensile force and vibration, thus improving the reliability and durability of the connection. At the same time, this connection method facilitates disassembly and installation, enabling quick and convenient operation when maintenance or replacement of parts is required, thereby improving work efficiency.

[0023] Furthermore, the tenon's engagement surface is provided with a limiting groove that mates with the first or second fixed boss; the connecting points of the inner walls of the limiting groove form arc surfaces. In this embodiment, the limiting groove 113 increases the contact area between the tenon 11 and the engaging groove, and the limiting groove 113 can mutually limit the engagement of the engaging groove. When the tenon 11 is inserted into the tenon groove of the outer wing mounting base 2, the precise fit between the tenon 11 and the outer wing mounting base 2 ensures that when the tenon 11 is subjected to external force, its rotation is blocked by the outer wing mounting base 2, thereby effectively limiting the rotation of the tenon 11. The connecting points of the inner walls of the limiting groove 113 form arc surfaces. The arc surface design not only reduces stress concentration and improves the structural strength of the tenon 11, but also makes the outer wing mounting base 2 more smoothly embedded in the limiting groove 113, reducing wear.

[0024] It should be noted that when the outer wing mounting base 2 is installed onto the inner wing mounting base 1, the limiting groove 113 contacts the surface of the limiting boss 212, and the limiting boss 212 contacts the side of the limiting groove, forming a tight mating surface. The precise fit between the tenon 11 and the mating groove 21 in the outer wing mounting base 2 ensures that when the tenon 11 is subjected to external force, its rotation is blocked by the outer wing mounting base 2, thereby effectively limiting the rotation of the tenon 11, and thus limiting the relative rotation between the outer wing mounting base 2 and the inner wing mounting base 1.

[0025] Furthermore, the outer wing mounting base 2 is provided with a plurality of first fixing holes 22 that mate with the first connecting hole 112; the first fixing holes 22 extend inward to form a first fixing boss 221. In this embodiment, the outer wing mounting base 2 is provided with two first fixing holes 22 that mate with the first connecting hole 112. The two first fixing holes 22 are used to insert the external threaded bolt 4, that is, the head of the external threaded bolt 4 can abut against the end face of the first fixing boss 221, increasing the contact area between the two, effectively distributing the load, and reducing local stress concentration. At the same time, the presence of the first fixing boss 221 enhances the structural strength around the first fixing hole 22 and improves the fatigue resistance of the external threaded bolt 4. When subjected to axial tensile force, the threads of the bolt and the threads of the first fixing hole 22 interlock, preventing the outer wing from separating from the mounting base; when subjected to shear force, the abutment between the bolt head and the end face of the first fixing boss 221 and the friction between the bolt shank and the hole wall work together to resist shear deformation and ensure the stability of the connection.

[0026] Furthermore, the outer wing mounting base 2 is provided with a plurality of second fixing holes 23 that mate with the second connecting hole 113; the second fixing holes 23 extend inward to form a second fixing boss 231. In this embodiment, the outer wing mounting base 2 is provided with two second fixing holes 23, which are used to insert the internal threaded bolt 5, that is, the head of the internal threaded bolt 5 can abut against the end face of the second fixing boss 231, increasing the contact area between the two, effectively dispersing the load, and reducing local stress concentration. At the same time, the presence of the first fixing boss 221 enhances the structural strength around the second fixing hole 23 and improves the fatigue resistance of the external threaded bolt 4. When subjected to axial tensile force, the threads of the bolt and the threads of the second fixing hole 23 mesh with each other, preventing the outer wing from separating from the mounting base; when subjected to shear force, the abutment between the bolt head and the end face of the second fixing boss 231 and the friction between the bolt shank and the hole wall work together to resist shear deformation and ensure the stability of the connection.

[0027] Furthermore, the inner wing mounting base 1 is provided with a plurality of first mounting shells 12, which are symmetrically distributed around the center of the inner wing mounting base 1. In this embodiment, the inner wing mounting base 1 is provided with two first mounting shells 12, which are C-shaped, with their openings facing each other. The C-shaped openings can better conform to the specific contours of the wing. The symmetrical arrangement of the two first mounting shells 12 not only ensures the balance of the outer wing mounting base 2 under stress, but also makes the contact between the two first mounting shells 12 and the wing more uniform. With the symmetrical distribution, the force from the outer wing mounting base 2 on the wing can be evenly distributed to the two first mounting shells 12, thereby transferring the force to the wing through a larger contact area, avoiding the problem of loosening or damage caused by excessive local stress. At the same time, the symmetrical distribution also helps to improve the installation accuracy and stability, making the connection between the outer wing mounting base 2 and the wing more reliable.

[0028] Furthermore, the outer wing mounting base 2 is provided with a plurality of second mounting shells 24, which are symmetrically distributed around the center of the outer wing mounting base 2. In this embodiment, the outer wing mounting base 2 is provided with two second mounting shells 24, which are C-shaped, and the opening of the C-shape can better fit the specific contour of the wing. The symmetrical layout of the two second mounting shells 24 not only ensures the balance of the outer wing mounting base 2 under force, but also makes the contact between the two second mounting shells 24 and the wing more uniform. With the symmetrical distribution, the force from the outer wing mounting base 2 on the wing can be evenly distributed to the two second mounting shells 24, thereby transferring the force to the wing through a larger contact area, avoiding the problem of loosening or damage caused by excessive local stress. At the same time, the symmetrical distribution also helps to improve the installation accuracy and stability, making the connection between the outer wing mounting base 2 and the wing more reliable.

[0029] Furthermore, the inner wing mounting base 1 is provided with a plurality of crisscrossing first reinforcing ribs 13. In this embodiment, the inner wing mounting base 1 is provided with four first reinforcing ribs 13, two of which are arranged in parallel, and the other two are arranged perpendicular to the other two. The four crisscrossing first reinforcing ribs 13 and the inner wing mounting base 1 form nine rectangular grooves. When the inner wing mounting base 1 is subjected to external mechanical loads, the crisscrossing first reinforcing ribs 13 can effectively disperse the stress in various directions. When the mounting base is subjected to vertical pressure, the vertical first reinforcing ribs 13 will bear part of the pressure and transfer it to the horizontal first reinforcing ribs 13, which then disperse the pressure to other parts of the mounting base, thereby avoiding stress concentration in local areas. The nine rectangular grooves help increase the path and area for stress dispersion, allowing the stress to be more evenly distributed throughout the mounting base, reducing the risk of structural damage caused by stress concentration.

[0030] Similarly, the outer wing mounting base 2 is provided with a plurality of intersecting second reinforcing ribs 25. In this embodiment, the outer wing mounting base 2 is provided with four second reinforcing ribs 25, two of which are arranged in parallel, and the other two are arranged perpendicular to the other two. The four intersecting second reinforcing ribs 25 and the outer wing mounting base 2 form nine rectangular grooves. When the outer wing mounting base 2 is subjected to external mechanical loads, the intersecting second reinforcing ribs 25 can effectively disperse the stress in various directions. When the mounting base is subjected to vertical pressure, the vertical second reinforcing ribs 25 will bear part of the pressure and transfer it to the horizontal second reinforcing ribs 25, which then disperse the pressure to other parts of the mounting base, thereby avoiding stress concentration in local areas. The nine rectangular grooves help increase the path and area for stress dispersion, allowing the stress to be more evenly distributed throughout the mounting base, reducing the risk of structural damage caused by stress concentration.

[0031] This utility model also proposes an aircraft comprising multiple quick-release wing mechanisms, multiple outer wings, and multiple inner wings, wherein one outer wing and one inner wing are detachably connected based on the quick-release wing mechanisms. The aircraft includes two inner and outer wing block mechanisms, two outer wings, and two inner wings, wherein one outer wing and one inner wing are detachably connected based on the quick-release wing mechanisms, the outer wing is mounted on the outer wing mounting base 2, and the inner wing is mounted within the inner wing mounting base 1.

[0032] In summary, this invention features a tenon and a groove for docking. The precise fit between the tenon and the groove ensures that when the tenon is subjected to external force, its rotation is blocked by the outer wing mounting seat, effectively limiting the rotation of the tenon and consequently restricting the relative rotation between the outer and inner wing mounting seats. Furthermore, this invention incorporates locating pins in the inner and outer wing mounting seats. The precise fit between the locating pins and their holes allows for adjustment of the outer wing position only along the axial direction of the locating pins, reducing the difficulty and time required for docking the inner and outer wings.

[0033] Furthermore, the above description provides a detailed account of the quick-release wing mechanism and aircraft provided by the embodiments of this utility model. Specific examples have been used to illustrate the principles and implementation methods of this utility model. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of this utility model. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this utility model. Therefore, the content of this specification should not be construed as a limitation of this utility model.

Claims

1. A quick-release mechanism for an aircraft wing, characterized in that, The quick-release wing mechanism includes: an inner wing mounting base and an outer wing mounting base; The inner wing mounting base is provided with tenons at both ends, and a first connecting hole is provided on the tenon, the first connecting hole passing through the tenon; The outer wing mounting base is provided with mating grooves at both ends that mate with the mating tenon, and a first fixing boss and a second fixing boss are provided on both sides of the mating groove. The mating tenon and the mating groove fix the inner wing mounting base and the outer wing mounting base together based on the first bolt and the second bolt; When the tenon is engaged with the groove, the first bolt is inserted into the first fixing boss and inserted at one end of the first connecting hole, and the second bolt is inserted into the second fixing boss and inserted at the other end of the first connecting hole.

2. The wing quick-release mechanism according to claim 1, characterized in that, The tenon has a first positioning pin hole on its snap-fit ​​surface, into which a positioning pin is inserted. The groove has a second positioning pin hole that mates with the positioning pin, and the other end of the positioning pin is inserted into the second positioning pin hole.

3. The wing quick-release mechanism according to claim 1, characterized in that, The first bolt is an externally threaded bolt, and the second bolt is an internally threaded bolt. The first bolt and the second bolt are interlocked based on their threads.

4. The wing quick-release mechanism according to claim 1, characterized in that, The tenon has a limiting groove on its snap-fit ​​surface that mates with the first fixing boss or the second fixing boss. The inner walls of the limiting grooves form arc surfaces at their joints.

5. The wing quick-release mechanism according to claim 1, characterized in that, The outer wing mounting base has multiple first fixing holes on one side that mate with the first connecting hole; The first fixing hole extends inward to form a first limiting boss.

6. The wing quick-release mechanism according to claim 1, characterized in that, On the other side of the outer wing mounting base, there are multiple second fixing holes that mate with the first connecting hole; The second fixing hole extends inward to form a second limiting boss.

7. The wing quick-release mechanism according to claim 1, characterized in that, The inner wing mounting base is provided with a plurality of first mounting shells, which are distributed symmetrically about the center of the inner wing mounting base.

8. The wing quick-release mechanism according to claim 1, characterized in that, The outer wing mounting base is provided with a plurality of second mounting shells, which are distributed symmetrically about the center of the outer wing mounting base.

9. The wing quick-release mechanism according to claim 1, characterized in that, The inner wing mounting base is provided with multiple intersecting first reinforcing ribs.

10. An aircraft, characterized in that, The aircraft includes: a plurality of wing quick-release mechanisms as described in any one of claims 1 to 9, a plurality of outer wings and a plurality of inner wings, wherein one of the outer wings and one of the inner wings are detachably connected based on one of the wing quick-release mechanisms.

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