Dismounting and connecting device for wing locking of composite wing unmanned aerial vehicle

Abstract

The utility model discloses a composite wing unmanned aerial vehicle wing locking dismounting connecting device which comprises a front wing and a rear wing, a fuselage is arranged between the front wing and the rear wing, first undercarriages are symmetrically installed on the two sides of the front wing, and undercarriage connecting pieces are fixedly installed on one sides of the two first undercarriages. A second undercarriage is fixedly installed on one side of the bottom of the undercarriage connecting piece, longitudinal connecting assemblies and vertical shaft connecting assemblies are arranged at the connecting positions of the fuselage and the front wings and the connecting positions of the fuselage and the rear wings, and the longitudinal connecting assemblies comprise fixed shells symmetrically installed on the sides, close to the fuselage, of the front wings and the rear wings; the connecting stability and reliability of the wings are improved, better vibration and impact absorption capacity is provided, the wing connecting device adapts to complex flight environments, the dismounting and mounting processes are simplified, the operation efficiency is improved, additional safety guarantee is provided, and accidental unlocking or loosening is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engineering, in particular to a detachable connection device for locking the wings of a composite-wing unmanned aerial vehicle. Background Art

[0002] In the field of aeronautical engineering, wing locking and assembly / disassembly devices are crucial components in drone construction. Traditional wing attachment methods typically rely on mechanical locking, employing a design where a locking pin and a movable pin interact with each other. This design ensures the wing's position remains stable when connected to the fuselage, but requires the operator to release the locking pin when removing the wing.

[0003] There are currently some problems with the wing locking assembly and disassembly connection device. First, the traditional bite design may have the risk of loose connection or accidental unlocking, especially when the drone is subjected to large vibrations or impacts. Second, the operation during the disassembly process is cumbersome and requires the use of specific tools and auxiliary equipment, which increases the disassembly time and difficulty of operation. In addition, the existing technology has poor vibration and impact absorption capacity between the wing and the fuselage, which may cause fatigue and damage to the connection parts.

[0004] A detachable connection device for locking the wings of a composite-wing UAV is proposed to solve the above-mentioned problems. Utility Model Content

[0005] The purpose of the present utility model is to provide a wing locking disassembly and assembly connection device for a composite wing UAV, so as to solve the problem proposed in the above background technology that the current wing locking disassembly and assembly connection device may have the risk of loose connection or accidental unlocking through the traditional bite design, especially when the UAV is subjected to large vibration or impact. Secondly, the operation during the disassembly process is cumbersome and requires the use of specific tools and auxiliary equipment, which increases the disassembly time and operation difficulty. In addition, the existing technology has poor vibration and impact absorption capacity between the wing and the fuselage, which may cause fatigue and damage to the connection parts.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a detachable and assembling connecting device for locking the wings of a composite-wing UAV, comprising a front wing and a rear wing;

[0007] A fuselage is provided between the front wing and the rear wing, and first landing gears are symmetrically mounted on both sides of the front wing, and landing gear connectors are fixedly mounted on one side of the two first landing gears, and second landing gears are fixedly mounted on one side of the bottom of the landing gear connectors;

[0008] Also includes:

[0009] The connection between the fuselage and the front wing and the rear wing is provided with a longitudinal connection assembly and a vertical axis connection assembly;

[0010] The longitudinal connection assembly includes a fixed shell symmetrically mounted on the front wing and the rear wing near the fuselage, with a connection groove extending through the top of the fixed shell and a through hole extending through the lower side of one side of the fixed shell, and an internal steel sleeve adapted to be connected to the interior of the through hole;

[0011] Among them, the internal adaptor connection of the internal steel sleeve is provided with a locking steel sleeve, and the internal adaptor connection of the locking steel sleeve is provided with a locking rod, and locking holes are provided on one side of the top of the locking steel sleeve and the locking rod, and the internal adaptor connection of the connecting groove is provided with a fixing pin, and a positioning hole is provided on one side of the locking rod of the fuselage, and the locking rod is adapted to be connected with the positioning hole.

[0012] Preferably, the fixing member pin is adapted to be connected with the two locking holes, and a waist-shaped hole is provided through the top of the inner steel sleeve, and the fixing member pin is adapted to be connected with the waist-shaped hole.

[0013] Preferably, a retaining spring is detachably connected to the lower portion of the fixing member latch, and a telescopic spring is sleeved on the lower portion of the outer portion of the fixing member latch.

[0014] Preferably, the vertical axis connection assembly includes two sets of wing fixing plates symmetrically installed on the front wing and the rear wing close to the fuselage side, and fuselage fixing plates are symmetrically installed on the side of the fuselage close to the front wing and the rear wing, and a waist-shaped groove is opened through the top of the fuselage fixing plate.

[0015] Preferably, a vertical axis locking seat is fixedly installed on one side of the top of the wing fixing plate, and a vertical axis locking rod is adapted and connected inside the waist-shaped groove, and the vertical axis locking rod is threadedly connected to the vertical axis locking seat.

[0016] Preferably, the bottom of the fuselage fixing plate is symmetrically installed with a fixing block on one side of the waist-shaped groove, and the interior of the two fixing blocks is slidably connected to a movable rod, and the ends of the two movable rods that are close to each other are fixedly connected to a positioning sleeve, and the outer side of the two movable rods is sleeved with a compression spring, and one end of the compression spring is fixedly connected to the fixing block, and the other end of the compression spring is fixedly installed with a connecting block, and the connecting block is fixedly connected to the movable rod.

[0017] Preferably, the bottom of the fuselage fixing plate is located on one side of the two positioning sleeves and is fixedly installed with a mounting block, and the internal thread of the mounting block is connected to a screw, and one end of the screw is rotatably connected to a movable block, and the movable block is slidingly connected to the fuselage fixing plate, and the two ends of the movable block are symmetrically hinged with connecting rods, and the end of the connecting rod away from the movable block is hinged to the connecting block.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows: the detachable connection device for locking the wings of a composite-wing UAV improves the stability and reliability of the wing connection, provides better vibration and shock absorption capabilities, adapts to complex flight environments, simplifies the disassembly and installation process, improves operational efficiency, provides additional safety protection, avoids accidental unlocking or loosening, and provides a convenient and quick locking method for locking the wings of a composite-wing UAV. The specific contents are as follows:

[0019] 1. A longitudinal connection assembly and a vertical axis connection assembly are provided at the connection between the front wing and the rear wing and the fuselage. First, use countersunk screws to fix the wing fixing plate on the front wing or the rear wing, and use countersunk screws to fix the fuselage fixing plate to the fuselage. When installing the wing, first insert the vertical axis locking rod into the waist groove of the fuselage fixing plate, and then push it along the waist groove to the other end. Then use the longitudinal connection assembly to push the fixing pin of the longitudinal connection assembly so that the locking rod of the longitudinal connection assembly is inserted into the positioning hole of the fuselage, so that the wing fixing plate moves along the waist groove of the fuselage fixing plate with the vertical axis locking rod. When it moves to one end of the waist groove, since the column at one end of the vertical axis locking rod is larger than the waist groove width of the fuselage fixing plate, the front wing and the rear wing are locked to the fuselage on the vertical axis. When it moves to the other end of the waist groove, since the column at one end of the vertical axis locking rod is smaller than the waist groove width of the fuselage fixing plate, the front wing and the rear wing are vertically fixed to the fuselage. When the fixing pin moves to the upper step of the fixed shell, the locking rod and the locking steel sleeve move with the fixing pin to the positioning hole inside the front wing or the rear wing, thereby realizing the longitudinal locking of the front wing and the rear wing with the fuselage, and finally use screws to connect the front wing, the first landing gear, the second landing gear, the landing gear connector and the rear wing respectively. This can ensure the stability of the front and rear wings and the fuselage in the horizontal, longitudinal and vertical axis directions, and can also achieve rapid disassembly and assembly of the wings of such canard-wing composite wing drones;

[0020] 2. After the vertical axis locking rod moves, the screw rod can be rotated. The screw rod can be moved through the threaded connection with the mounting block, so that the movable block can be pulled to move. After the movable block moves, the two connecting blocks can be driven closer to each other through the two connecting rods, so that the movable rod slides on the fixed block, so that the positioning sleeve can fit the vertical axis locking rod tightly, preventing the vertical axis locking rod from accidentally rotating and affecting the connection between the fuselage fixing plate and the wing fixing plate, thereby improving the reliability of the connection and preventing accidental unlocking or loosening. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the three-dimensional structure of the utility model;

[0022] Figure 2 This is a schematic diagram of the explosion structure of the utility model;

[0023] Figure 3 This is a schematic diagram of the exploded structure of the longitudinal connection assembly of the utility model;

[0024] Figure 4 This is a schematic diagram of the exploded structure of the local structure of the vertical axis connection assembly of the utility model;

[0025] Figure 5 This is a schematic diagram of the bottom view of the fuselage fixing plate of the present invention.

[0026] In the figure: 1, front wing; 101, rear wing; 102, fuselage; 103, first landing gear; 104, second landing gear; 105, landing gear connector; 2, longitudinal connecting assembly; 201, fixed shell; 202, connecting groove; 203, through hole; 204, inner steel sleeve; 205, locking steel sleeve; 206, locking rod; 207, locking hole; 208, waist hole; 209, fixing part latch; 21 0. Circlip; 211. Telescopic spring; 3. Vertical axis connecting assembly; 301. Wing fixing plate; 302. Fuselage fixing plate; 303. Vertical axis locking seat; 304. Vertical axis locking rod; 305. Waist-shaped groove; 306. Fixed block; 307. Movable rod; 308. Positioning sleeve; 309. Compression spring; 310. Connecting block; 311. Mounting block; 312. Screw; 313. Movable block; 314. Connecting rod. DETAILED DESCRIPTION

[0027] 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 implementation regulations 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.

[0028] See also Figure 1-5The utility model provides a technical solution: a detachable connection device for locking the wings of a composite wing UAV, comprising a front wing 1 and a rear wing 101, a fuselage 102 is arranged between the front wing 1 and the rear wing 101, and first landing gears 103 are symmetrically installed on both sides of the front wing 1, and a landing gear connector 105 is fixedly installed on one side of the two first landing gears 103, and a second landing gear 104 is fixedly installed on one side of the bottom of the landing gear connector 105, and further comprises: a longitudinal connection assembly 2 and a vertical axis connection assembly 3 are provided at the connection between the fuselage 102 and the front wing 1 and the rear wing 101, wherein the longitudinal connection assembly 2 comprises a fixed shell 201 symmetrically installed on the front wing 1 and the rear wing 101 close to the fuselage 102, and a connection groove is penetrated through the top of the fixed shell 201. 202, and a through hole 203 is opened through the lower side of the fixed shell 201, and the interior of the through hole 203 is adapted to be connected with an internal steel sleeve 204, wherein the interior of the internal steel sleeve 204 is adapted to be connected with a locking steel sleeve 205, and the interior of the locking steel sleeve 205 is adapted to be connected with a locking rod 206, and a locking hole 207 is opened through one side of the top of the locking steel sleeve 205 and the locking rod 206, and the interior of the connecting groove 202 is adapted to be connected with a fixing part pin 209, and a positioning hole is opened on one side of the locking rod 206 of the fuselage 102, and the locking rod 206 is adapted to be connected with the positioning hole, which can ensure the stability of the front wing 1 and the rear wing 101 and the fuselage 102 in the horizontal, longitudinal and vertical axis directions, and can also realize the rapid disassembly and assembly of the wings of such canard-type composite wing UAV.

[0029] The fixing part latch 209 is adapted to be connected with the two locking holes 207, and a waist-shaped hole 208 is opened through the top of the internal steel sleeve 204, and the fixing part latch 209 is adapted to be connected with the waist-shaped hole 208, which can position the locking rod 206. The lower part of the fixing part latch 209 is disassembled and connected with a retaining spring 210, and the outer lower part of the fixing part latch 209 is sleeved with a telescopic spring 211, so that the fixing part latch 209 can be limited. The vertical axis connection assembly 3 includes two sets of wing fixing parts symmetrically installed on the front wing 1 and the rear wing 101 close to the side of the fuselage 102. Plate 301, and the fuselage 102 is symmetrically installed with a fuselage fixing plate 302 on one side close to the front wing 1 and the rear wing 101, and a waist-shaped groove 305 is opened through the top of the fuselage fixing plate 302 to facilitate the installation and disassembly of the front wing 1 and the rear wing 101, and a vertical axis locking seat 303 is fixedly installed on one side of the top of the wing fixing plate 301, and the interior of the waist-shaped groove 305 is adapted to be connected with a vertical axis locking rod 304, and the vertical axis locking rod 304 is threadedly connected to the vertical axis locking seat 303, which can fix the wing fixing plate 301 and the fuselage fixing plate 302.

[0030] The bottom of the fuselage fixing plate 302 is symmetrically installed with a fixing block 306 on one side of the waist-shaped groove 305, and the interior of the two fixing blocks 306 are slidably connected to the movable rod 307, and the adjacent ends of the two movable rods 307 are fixedly connected to the positioning sleeve 308, and the outer side of the two movable rods 307 are sleeved with a compression spring 309, and one end of the compression spring 309 is fixedly connected to the fixing block 306, and the other end of the compression spring 309 is fixedly installed with a connecting block 310, and the connecting block 310 is fixedly connected to the movable rod 307, which can be used for The vertical axis locking rod 304 is positioned, and the bottom of the fuselage fixing plate 302 is fixedly installed with a mounting block 311 on one side of the two positioning sleeves 308, and the internal thread of the mounting block 311 is connected to the screw 312, and one end of the screw 312 is rotatably connected to the movable block 313, and the movable block 313 is slidingly connected to the fuselage fixing plate 302, and the two ends of the movable block 313 are symmetrically hinged with connecting rods 314, and the end of the connecting rod 314 away from the movable block 313 is hinged to the connecting block 310, so that the movement of the screw 312 can drive the movable rod 307 to move.

[0031] Working principle: Before using the wing locking and disassembly connection device of the composite wing UAV, it is necessary to check the overall condition of the device to ensure that it can work normally. Figure 1 - Figure 5As shown, a longitudinal connection assembly 2 and a vertical axis connection assembly 3 are provided at the connection between the front wing 1 and the rear wing 101 and the fuselage 102. First, the wing fixing plate 301 is fixed to the front wing 1 or the rear wing 101 using countersunk screws, and the fuselage fixing plate 302 is fixed to the fuselage 102 using countersunk screws. When installing the wing, the vertical axis locking rod 304 is first inserted into the waist groove 305 of the fuselage fixing plate 302, and then pushed along the waist groove 305 to the other end. Then, the longitudinal connection assembly 2 is used to push the fixing part pin 209 of the longitudinal connection assembly 2, so that the locking rod 206 of the longitudinal connection assembly 2 is inserted into the positioning hole of the fuselage 102, so that the wing fixing plate 30 1 moves along the waist-shaped groove 305 of the fuselage fixing plate 302 with the vertical axis locking rod 304. When it moves to one end of the waist-shaped groove 305, the column at one end of the vertical axis locking rod 304 is larger than the width of the waist-shaped groove 305 of the fuselage fixing plate 302, thereby locking the front wing 1 and the rear wing 101 with the fuselage 102 in the vertical axis. When it moves to the other end of the waist-shaped groove 305, the column at one end of the vertical axis locking rod 304 is smaller than the width of the waist-shaped groove 305 of the fuselage fixing plate 302, thereby separating the front wing 1 and the rear wing 101 from the fuselage 102 in the vertical axis. Insert the internal steel sleeve 204 into the fixed shell 201, and align the locking steel sleeve 205 with the locking rod 206. Insert it into the inner steel sleeve 204, then pass the fixing pin 209 through the waist-shaped hole 208 and the locking hole 207 from the connecting groove 202, put the telescopic spring 211 under the outer side of the fixing pin 209, install the retaining spring 210 to position the fixing pin 209, and the fixing pin 209 can move along the waist-shaped hole 208 of the inner steel sleeve 204. The fixing pin 209 drives the locking rod 206 and the locking steel sleeve 205 to move. When the fixing pin 209 moves to the lower step of the fixed shell 201, the fixing pin 209 cannot move in other directions except up and down. At this time, the surface of the locking rod 206 and one end of the locking steel sleeve 205 is fixed to the shell. 201 is flush with the surface. When the fixing pin 209 moves to the upper step of the fixed shell 201, the locking rod 206 and the locking steel sleeve 205 move with the fixing pin 209 to the positioning hole inside the front wing 1 or the rear wing 101, thereby realizing the longitudinal locking of the front wing 1 and the rear wing 101 with the fuselage 102. Finally, the front wing 1, the first landing gear 103, the second landing gear 104, the landing gear connecting piece 105 and the rear wing 101 are connected respectively with screws. In this way, the stability of the front wing 1 and the rear wing 101 and the fuselage 102 in the transverse, longitudinal and vertical axis directions can be ensured, and the wings of such canard-type composite wing UAV can be quickly disassembled and assembled.

[0032] After moving, the vertical axis locking rod 304 can rotate the screw rod 312, and the screw rod 312 can be moved through the threaded connection with the mounting block 311, so that the movable block 313 can be pulled to move. After the movable block 313 moves, the two connecting blocks 310 can be driven to approach each other through the two connecting rods 314, thereby making the movable rod 307 slide on the fixed block 306, so that the positioning sleeve 308 can fit tightly to the vertical axis locking rod 304, thereby preventing the vertical axis locking rod 304 from accidentally rotating and affecting the connection between the fuselage fixing plate 302 and the wing fixing plate 301, thereby improving the reliability of the connection and avoiding accidental unlocking or loosening.

[0033] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A detachable connection device for locking the wings of a composite wing UAV, comprising a front wing (1) and a rear wing (101); A fuselage (102) is provided between the front wing (1) and the rear wing (101), and first landing gears (103) are symmetrically mounted on both sides of the front wing (1), and a landing gear connecting member (105) is fixedly mounted on one side of the two first landing gears (103), and a second landing gear (104) is fixedly mounted on one side of the bottom of the landing gear connecting member (105); It is characterized by: Also includes: The connection points between the fuselage (102) and the front wing (1) and the rear wing (101) are all provided with a longitudinal connection component (2) and a vertical axis connection component (3); The longitudinal connection assembly (2) comprises a fixed shell (201) symmetrically mounted on one side of the front wing (1) and the rear wing (101) close to the fuselage (102), and a connection groove (202) is provided through the top of the fixed shell (201), and a through hole (203) is provided through the lower side of one side of the fixed shell (201), and an internal steel sleeve (204) is adapted and connected inside the through hole (203); The inner portion of the inner steel sleeve (204) is adapted to be connected to a locking steel sleeve (205), and the inner portion of the locking steel sleeve (205) is adapted to be connected to a locking rod (206), and a locking hole (207) is provided through one side of the top of each of the locking steel sleeve (205) and the locking rod (206), and a fixing member latch (209) is adapted to be connected to the inner portion of the connecting groove (202), and a positioning hole is provided on one side of the locking rod (206) of the fuselage (102), and the locking rod (206) is adapted to be connected to the positioning hole.

2. The detachable connection device for locking the wing of a composite wing UAV according to claim 1, characterized in that: The fixing member latch (209) is adapted to be connected with the two locking holes (207), and a waist-shaped hole (208) is provided through the top of the internal steel sleeve (204), and the fixing member latch (209) is adapted to be connected with the waist-shaped hole (208).

3. The detachable connection device for locking the wing of a composite wing UAV according to claim 1, characterized in that: A clip spring (210) is detachably connected to the lower portion of the fixing member latch (209), and a telescopic spring (211) is sleeved on the lower portion of the outer portion of the fixing member latch (209).

4. The detachable connection device for locking the wing of a composite wing UAV according to claim 1, characterized in that: The vertical axis connection assembly (3) comprises two groups of wing fixing plates (301) symmetrically mounted on one side of the front wing (1) and the rear wing (101) close to the fuselage (102), and the fuselage fixing plates (302) are symmetrically mounted on one side of the fuselage (102) close to the front wing (1) and the rear wing (101), and waist-shaped grooves (305) are formed through the tops of the fuselage fixing plates (302).

5. The detachable connection device for locking the wing of a composite wing UAV according to claim 4, characterized in that: A vertical axis locking seat (303) is fixedly installed on one side of the top of the wing fixing plate (301), and a vertical axis locking rod (304) is adapted and connected inside the waist-shaped groove (305), and the vertical axis locking rod (304) is threadedly connected to the vertical axis locking seat (303).

6. The detachable connection device for locking the wing of a composite wing UAV according to claim 4, characterized in that: The bottom of the fuselage fixing plate (302) is symmetrically installed with a fixing block (306) on one side of the waist-shaped groove (305), and the interiors of the two fixing blocks (306) are slidably connected with movable rods (307), and the adjacent ends of the two movable rods (307) are fixedly connected with positioning sleeves (308), and the outer sides of the two movable rods (307) are sleeved with compression springs (309), and one end of the compression spring (309) is fixedly connected to the fixing block (306), and the other end of the compression spring (309) is fixedly installed with a connecting block (310), and the connecting block (310) is fixedly connected to the movable rod (307).

7. The detachable connection device for locking the wing of a composite wing UAV according to claim 6, characterized in that: The bottom of the fuselage fixing plate (302) is located on one side of the two positioning sleeves (308) and is fixedly installed with a mounting block (311), and the internal thread of the mounting block (311) is connected to a screw rod (312), and one end of the screw rod (312) is rotatably connected to a movable block (313), and the movable block (313) is slidably connected to the fuselage fixing plate (302), and the two ends of the movable block (313) are symmetrically hinged with connecting rods (314), and the end of the connecting rod (314) away from the movable block (313) is hinged to the connecting block (310).

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