M-shaped synchronous unfolding device for wings of barrel-launched unmanned aerial vehicle

Abstract

The invention discloses a novel M-shaped synchronous unfolding device for wings of a barrel-shot unmanned aerial vehicle. A wing bearing plate comprises a gunpowder barrel positioning device, a boss, an arc groove, an inner wing shaft, a transmission gear shaft, an inner wing spring pin hole and a rectangular block; the folding wing group comprises an inner wing, an outer wing, teeth, a stepped shaft, a torsional spring and an outer wing spring pin, the stepped shaft serves as a rotating shaft, and the torsional spring is arranged on the stepped shaft; one end, with teeth, of the inner wing is a root and is fixed on the inner wing shaft, an inner wing spring pin is arranged at the horizontal center line, the lower end of the inner wing spring pin is embedded into the arc groove, and an inner wing torsion spring hole is formed in the horizontal center line of one end without teeth and is matched with the lower end of the torsion spring; an outer wing spring pin is arranged at one point of the outer wing horizontal center line, the lower end of the outer wing spring pin is in plane contact with the stepped shaft, and an outer wing torsion spring hole is formed in the outer wing horizontal center line farther from the outer wing rotating shaft than the outer wing spring pin and matched with the upper end of a torsion spring; the gear unfolding mechanism comprises two transmission gears, a rack, a rack transmission rod and a gunpowder barrel. According to the invention, miniaturization of the barrel-launched unmanned aerial vehicle is realized, and transportation and launching in various environments are facilitated.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, in particular to the technical field of unmanned aerial vehicle wing rotation, and specifically to a folding wing unfolding shaft mechanism. Background Art

[0002] Folding-wing UAVs have the advantage of being small and easy to carry after folding. In addition, cluster UAVs have become a hot topic. Most cluster UAVs are launched by catapult, cannon launch, aerial projection, etc. To meet the needs of cannon launch, most cannon-launched cluster UAVs use folding wings. The synchronous unfolding mechanism of folding wings is the key technology of this type of aircraft.

[0003] The design of the folding wing pivot mechanism is a technical difficulty. The mechanism requires that the folded size of the wing be small enough for transportation and launch, and that the pivot mechanism be able to quickly and reliably complete the synchronous unfolding of the left and right wings in a very short time, and also that the position locking of the wings be achieved when they are unfolded. Summary of the invention

[0004] The purpose of the present invention is to provide an M-shaped synchronous unfolding device for the wings of a tube-launched UAV.

[0005] The technical solution to achieve the purpose of the present invention is: a tube-launched UAV wing M-shaped synchronous deployment device, including a wing bearing plate, a pair of folding wing groups, and a gear deployment mechanism, wherein: The wing bearing plate comprises a powder cartridge positioning device, a boss, an arc groove, an inner wing shaft, a transmission gear shaft, an inner wing spring pin hole and a rectangular block; the powder cartridge positioning device and the boss are arranged at the axis of the wing bearing plate; the transmission gear shaft, the inner wing shaft and the rectangular block are symmetrically arranged on both sides of the boss from inside to outside, and the axes of the transmission gear shaft and the inner wing shaft are located on the same plane; an arc groove coaxial with the inner wing shaft is arranged on the outer side of the inner wing shaft; The folding wing group includes an inner wing, an outer wing, teeth, a stepped shaft, a torsion spring and an outer wing spring pin. The stepped shaft serves as a rotation axis, on which a torsion spring is arranged; teeth are arranged at one end of the inner wing, and the other end is without teeth. The toothed end of the inner wing is the root, which is fixed on the inner wing shaft. An inner wing spring pin is arranged at the horizontal center line, and the lower end of the inner wing spring pin is embedded in the arc groove. An inner wing torsion spring hole is arranged at the horizontal center line of the end without teeth to cooperate with the lower end of the torsion spring, and the upper surface of the inner wing shaft is in close contact with the stepped shaft and does not rotate relative to each other; an outer wing spring pin is arranged at a point at the horizontal center line of the outer wing, and its lower end is in plane contact with the stepped shaft. An outer wing torsion spring hole is arranged on the horizontal center line of the outer wing, which is farther away from the outer wing rotation axis than the outer wing spring pin, and cooperates with the upper end of the torsion spring. The lower surface of the outer wing shaft is in close contact with the stepped shaft and can rotate relative to each other. The gear deployment mechanism includes two transmission gears, a rack, a rack transmission rod and a powder cartridge. There are transmission gear bearings on the upper and lower sides of the transmission gear to ensure the normal rotation of the transmission gear. The rack is placed on the boss of the wing bearing plate. There are teeth on both sides of the rack that mesh with the transmission gear. The other side of the transmission gear meshes with the teeth on the outer peripheral surface of the inner wing. There is a rack transmission rod at the tail of the rack that is inserted into the powder cartridge fixed on the bearing plate. The powder cartridge is fixed to the wing bearing plate through a powder cartridge positioning device.

[0006] Furthermore, the rectangular block is on the side edge of the inner wing shaft, and an elastic rubber block is provided on the rectangular block as an energy absorbing buffer. When the wing rotates to a limited position, the wing abuts against the energy absorbing buffer.

[0007] Furthermore, the starting point of the arc groove is located on the wing bearing plate below the center line of the inner wing, and the outward rotation angle is 90°. There is an inner wing spring pin hole at the end point of the arc groove. When the inner wing is unfolded to 90°, the inner wing hits the rectangular block to stop moving, and the inner wing spring pin slides into the inner wing spring pin hole at the end point of the arc groove, thereby achieving the limiting of the inner wing.

[0008] Furthermore, the inner wing is also arranged with an inner wing bearing, an inner wing cover plate, and an inner wing bolt from bottom to top with the rotation axis of the inner wing as the axis. The inner wing is fixed to the inner wing shaft through the inner wing cover plate and the inner wing bolts, and inner wing bearings are arranged above and below to ensure that the inner wing can rotate normally when subjected to lift.

[0009] Furthermore, the outer wing is arranged with an outer wing bearing, an outer wing cover plate, and an outer wing bolt from bottom to top with the outer wing's rotation axis as the axis. The outer wing bolt and the outer wing cover plate connect the outer wing and the stepped shaft. An outer wing bearing is arranged between the outer wing cover plate and the outer wing to ensure that the outer wing can rotate normally when subjected to lift.

[0010] Furthermore, an outer wing spring pin pit is provided on the stepped shaft. When the outer wing is unfolded to 180°, the torsion spring stops pulling the outer wing, and the outer wing spring pin slides into the outer wing spring pin pit in the stepped shaft, thereby achieving the limitation of the outer wing.

[0011] Furthermore, the wing bearing plate is provided with a weight-reducing groove between the boss and the powder cartridge positioning device.

[0012] Furthermore, the transmission gear bearing (5), the transmission gear (3), the transmission gear bearing (5), the transmission gear cover plate (31), and the transmission gear screw (24) are arranged from bottom to top with the transmission gear shaft (26) as the axis, so as to achieve stable transmission during the deployment of the transmission gear (3).

[0013] Furthermore, the UAV is in a folded state when launched with the outer shell, and the unfolding of the inner wing and the outer wing is limited by the shell wall. After launching, the UAV separates from the projectile body and the gunpowder in the gunpowder cartridge is detonated to unfold the inner wing. At the same time, the torsion spring causes the inner wing and the outer wing to move relative to each other, so that the wing group unfolds in an M shape; when the four wings are unfolded, the four wings are in the same straight line.

[0014] Compared with the prior art, the present invention has the following significant advantages: The two-stage deployment can shorten the length of the wing when folded to half of that of the single-stage deployment. Compared with the one-stage deployment, the wing mechanism is shorter, which is conducive to the optimization of the internal structure of the launcher. After the restraint of the external shell disappears, the inner wing deployment part uses the gunpowder in the gunpowder cartridge to provide driving force, pushing the rack to move, driving the transmission gears on both sides to rotate, and the rotation of the transmission gears drives the teeth on the outer peripheral surfaces of the left and right inner wings to rotate synchronously, so that the left and right wings can be deployed at the same time. The left and right wings use independent rotation axes. Compared with the coaxial deployment mechanism, the connection method is simple, ensuring reliable connection at the root of the wing. The transmission is through the meshing of gears and racks. Compared with the use of torsion springs at the root to provide driving force, the structure is more compact and the rotation is smoother; the outer wing deployment part uses a torsion spring to provide driving force, driving the outer wing to deploy in the opposite direction of the inner wing's rotation, so that the inner and outer wings are deployed in an M shape, so that the left and right wings do not interfere with each other. Except for the electronic devices required to detonate the gunpowder, the rest are purely mechanical mechanisms. In the invention, except for the electromagnet, other purely mechanical parts have a simple structure, low failure rate, high reliability and easy use. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the wing folding state of the present invention.

[0016] Figure 2 It is a schematic diagram of the M-shaped expansion process of the present invention.

[0017] Figure 3 It is a schematic diagram of the fully expanded state of the present invention.

[0018] Figure 4 This is a schematic diagram of the outer wing deployment device without a torsion spring of the present invention.

[0019] Figure 5 It is a schematic diagram of the installation of the torsion spring of the present invention.

[0020] Figure 6 Schematic diagram of the installation of the inner wing spring pin of the present invention.

[0021] Figure 7 It is a schematic diagram of the wing bearing plate of the present invention.

[0022] In the figure: 1, rectangular block 2, inner wing teeth 3, transmission gear 4, boss 5, transmission gear bearing 51, inner wing bearing 6, inner wing cover plate 7, arc groove 8, wing bearing plate 9, inner wing 10, outer wing 11, torsion spring 12, inner wing torsion spring hole 13, outer wing bearing 14, gunpowder cartridge 15, gunpowder cartridge positioning device 16, rack 17, outer wing cover plate 18, inner wing bolt 19, inner wing shaft 20, inner wing spring pin hole 21, outer wing torsion spring hole 22, outer wing spring pin pit 23, outer wing spring pin 24, transmission gear screw 25, stepped shaft 26, transmission gear shaft 27, weight reduction groove 28, inner wing spring pin 29, outer wing bolt 30, rack transmission rod 31, transmission gear cover plate DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0024] See also Figure 1-7 A novel tube-launched UAV wing M-shaped synchronous unfolding device comprises a wing bearing plate 8, a folding wing group, and a gear unfolding mechanism; Figure 7 The wing bearing plate 8 includes a powder cartridge positioning device 15, a boss 4, an arc groove 7, an inner wing shaft 19, a transmission gear shaft 26, an inner wing spring pin hole 20 and a rectangular block 1; the wing bearing plate 8 has an inner wing shaft 19 and a transmission gear shaft 26 on one side as the front side, and the powder cartridge positioning device 15 and the boss 4 are symmetrically arranged along the axis of the wing bearing plate 8, and the transmission gear shaft 26 and the inner wing shaft 19 are symmetrically arranged on both sides of the boss 4 along the axis of the wing bearing plate 8, and the axes of the transmission gear shaft 26 and the inner wing shaft 19 are located on the same plane, and a rectangular block 1 is arranged next to the inner wing shaft with an arc groove 7 coaxial with the inner wing shaft, and an inner wing spring pin hole 20 is arranged at the end of the arc groove 7.

[0025] Preferably, the wing bearing plate 8 is provided with a weight-reducing groove 27 between the boss 4 and the powder cartridge positioning device 15 .

[0026] Combination Figure 4-5The folding wing assembly includes an inner wing 9, an outer wing 10, teeth 2, a stepped shaft 25, a torsion spring 11, an inner wing bearing 51, an inner wing cover plate 6, an inner wing bolt 18, an outer wing bearing 13, an outer wing cover plate 17, an outer wing bolt 29 and an outer wing spring pin 23. The stepped shaft 25 cooperates with the toothless side of the inner wing 9, the torsion spring 11 and the outer wing 10 from bottom to top. The inner wing 9 is arranged with the inner wing bearing 51, the inner wing cover plate 6 and the outer wing bearing 13 as the axis. Plate 6, inner wing bolt 18; the outer wing 10 is arranged with the outer wing bearing 13, outer wing cover plate 17, and outer wing bolt 29 from bottom to top with the rotation axis of the outer wing 10 as the axis, and an outer wing spring pin 23 is arranged on the horizontal center line of the outer wing beside the outer wing rotation axis, and the lower end of the outer wing spring pin 23 is in contact with the stepped shaft 25; the upper surface of the shaft of the inner wing 9 is in close contact with the stepped shaft 25 and no relative rotation occurs, and the lower surface of the shaft of the outer wing 10 is in close contact with the stepped shaft 25.

[0027] Combination Figure 1-3 The gear deployment mechanism includes two transmission gears 3, a rack 16, a rack transmission rod 30 and a powder cartridge 14. The transmission gear 3 has transmission gear bearings 5 ​​on the upper and lower sides to ensure the normal rotation of the transmission gear 3. The rack 16 is placed on the boss 4 of the wing bearing plate 8. Both sides of the rack 16 have teeth that mesh with the transmission gear 3. The rear end of the rack 16 has a rack transmission rod 30 that is inserted into the powder cartridge 14 fixed on the wing bearing plate 8. The powder cartridge 14 is fixed on the wing bearing plate 8 through a powder cartridge positioning device 15.

[0028] Preferably, the transmission gear bearing (5), the transmission gear (3), the transmission gear bearing (5), the transmission gear cover plate (31), and the transmission gear screw (24) are arranged from bottom to top with the transmission gear shaft (26) as the axis, so as to achieve stable transmission during the deployment of the transmission gear (3).

[0029] To drive the powder cartridge 14 to move linearly, the powder cartridge 14 is fixed on the wing bearing plate 8 by a powder cartridge positioning device 15. When deployed, the gunpowder in the powder cartridge 14 explodes and causes the rack 16 to move linearly.

[0030] Combination Figure 1-3 The inner wing 9 is a machined part, including teeth 2, inner wing spring pin 28, and inner wing torsion spring hole 12. The inner wing 9 outer circumference has teeth on one end, and the inner wing spring pin 28 is set at the horizontal center line. The lower end of the inner wing spring pin is embedded in the arc groove 7. The inner wing torsion spring hole 12 is set at the horizontal center line of the other end of the inner wing 9 to match the lower end of the torsion spring 11. The outer circumference of the inner wing 9 has a gear end as the root, which is fixed to the inner wing shaft 19 through the inner wing cover plate 6 and the inner wing bolt 18. The inner wing bearings 51 are arranged above and below to ensure that the inner wing 9 can rotate normally when subjected to lift.

[0031] In order to drive the inner wing 9 to rotate and open, teeth 2 are arranged on a circular arc of more than 1 / 4 of the outer circumference of the left and right inner wings 9. Between the two inner wing rotating shafts, a transmission gear 3 is arranged to mesh with the inner wing teeth 2. The rack 16 is installed on the boss 14 of the wing bearing plate 8 and can slide along the length direction of the boss 14. The linear motion of the rack 16 drives the transmission gear 3 to rotate, and then drives the inner wing 9 to rotate, thereby realizing the opening of the inner wing 9, and the rotation angle is 0-90°.

[0032] like Figure 4-5 As described above, the stepped shaft 25 is used as the rotation axis, a countersunk screw 30 is set to connect the inner wing and the stepped shaft 25, an outer wing bolt 29 and an outer wing cover plate 17 are set to connect the outer wing 10 and the stepped shaft 25, and an outer wing bearing 13 is set between the outer wing cover plate 17 and the outer wing 10 to ensure that the outer wing 10 can rotate normally when subjected to lift.

[0033] In order to drive the outer wing 10 to rotate and open, a torsion spring 11 is arranged in the middle section of the stepped shaft 25 . The upper end of the torsion spring 11 is bent and fixed in the outer wing torsion spring hole 12 , and the lower end of the torsion spring 11 is bent and fixed in the inner wing torsion spring hole 21 .

[0034] like Figure 2-3 As described above, after losing the restriction of the shell, it starts to rotate simultaneously with the inner wing 9, and the matching inner and outer wings rotate in opposite directions, and the outer wing rotates at an angle of 0-180°, thereby realizing the M-shaped wing deployment.

[0035] In order to achieve locking after the wings are unfolded, the inner wing 9 is provided with an inner wing spring pin 28 at the toothed end, and the lower end of the inner wing spring pin 28 is embedded in the circular arc groove 7. The inner wing spring pin 28 rotates with the inner wing 9, and the rotation angle is 0-90°. The circular arc groove 7 is provided with an inner wing spring pin pin hole 20 at the rotation end point. When the inner wing spring pin 28 rotates to the end point, its head falls into the inner wing spring pin pin hole 20 to achieve inner wing locking.

[0036] Combination Figure 4 The middle section of the stepped shaft 25 is parallel to the inner wing 9 and has an outer wing spring pin pit 22 at a point on the axis in the direction away from the inner wing 9; an outer wing spring pin 23 is arranged on the wing side of the outer wing 10; when the outer wing 10 rotates, the outer wing spring pin 23 rotates accordingly, and after rotating 180°, it slides into the outer wing spring pin pit 22 to achieve mutual locking of the inner and outer wings.

[0037] When the four wings are unfolded, the four wings are in the same straight line.

[0038] Combination Figure 7 The wing bearing plate 8 is characterized in that there is a rectangular block 1 on the edge of the inner wing shaft side, and an elastic rubber block of suitable thickness is provided on the rectangular block 1 as an energy absorbing buffer. When the wing rotates to a limited position, the wing and the energy absorbing buffer are abutted to achieve energy absorption and buffering when the wing is fully unfolded.

[0039] The present invention uses a two-stage unfolding method, so that the length of the wing when folded is shortened to half of that of a single-stage unfolding method. Compared with a one-stage unfolding wing mechanism, the length is shorter, which is conducive to the optimization of the internal structure of the launching projectile; the left and right wings use independent rotating shafts, and compared with a coaxial unfolding mechanism, the connection method is simple, ensuring that the root of the wing is connected reliably. Transmission is carried out by gear rack meshing, and the structure is more compact and the rotation is more stable compared with the root using a torsion spring to provide driving force; the outer wing unfolding part provides driving force through a torsion spring, driving the outer wing to unfold in the opposite direction of the inner wing rotation direction, so that the inner and outer wings unfold in an M shape, so that the left and right wings do not interfere with each other; except for the electronic devices required to detonate gunpowder, the rest of the present invention is a pure mechanical mechanism. In the invention, except for the electromagnet, other pure mechanical parts have a simple structure, a low failure rate, high reliability, and convenient use, and the wing unfolding mechanism of the unmanned aerial vehicle is optimized and improved.

[0040] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Those skilled in the art can still make modifications to the above technical solutions, or make equivalent replacements for some of the technical features therein, and any modifications made without departing from the spirit and scope of the present invention should fall within the protection scope of the present invention.

Claims

1. A tube-launched UAV wing M-shaped synchronous deployment device, characterized in that: It comprises a wing bearing plate (8), a pair of folding wing groups, and a gear unfolding mechanism, wherein: The wing bearing plate (8) comprises a powder cartridge positioning device (15), a boss (4), an arc groove (7), an inner wing shaft (19), a transmission gear shaft (26), an inner wing spring pin hole (20) and a rectangular block (1); the powder cartridge positioning device (15) and the boss (4) are arranged at the axis of the wing bearing plate; the transmission gear shaft (26), the inner wing shaft (19) and the rectangular block (1) are symmetrically arranged on both sides of the boss (4); the axes of the transmission gear shaft (26) and the inner wing shaft (19) are located on the same plane, the transmission gear shaft (26) and the boss (4) are closest to each other, the inner wing shaft (19) and the boss (4) are centered, and the rectangular block (1) and the boss (4) are farthest apart; and an arc groove (7) coaxial with the inner wing shaft is arranged on the outer side of the inner wing shaft (19); The folding wing assembly comprises an inner wing (9), an outer wing (10), teeth (2), a stepped shaft (25), a torsion spring (11) and an outer wing spring pin (23); the stepped shaft (25) serves as a rotation axis, on which a torsion spring (11) is arranged; one end of the inner wing (9) is provided with teeth (2), and the other end is free of teeth (2); the end of the inner wing (9) with teeth (2) is a root portion and is fixed to the inner wing shaft (19); an inner wing spring pin (28) is arranged at a horizontal midline, and the lower end of the inner wing spring pin (28) is embedded in a circular arc groove (7); the end of the inner wing (9) without teeth (2) is provided at a horizontal midline An inner wing torsion spring hole (12) is arranged to cooperate with the lower end of the torsion spring (11), and the upper surface of the shaft of the inner wing (9) is in close contact with the lower surface of the middle section of the stepped shaft (25) and does not rotate relative to each other; an outer wing spring pin (23) is arranged at a point on the horizontal midline of the outer wing (10), and its lower end is in plane contact with the stepped shaft (25); an outer wing torsion spring hole (21) is arranged on the horizontal midline of the outer wing (10) at a distance from the outer wing rotation axis farther than the outer wing spring pin (23) and cooperates with the upper end of the torsion spring (11), and the lower surface of the shaft of the outer wing (10) is in close contact with the upper surface of the middle section of the stepped shaft (25) and can rotate relative to each other; The gear deployment mechanism comprises two transmission gears (3), a rack (16), a rack transmission rod (30) and a powder cartridge (14). Transmission gear bearings (5) are arranged above and below the transmission gear (3) to ensure the normal rotation of the transmission gear (3). The rack (16) is placed on a boss (4) of a wing bearing plate (8). Both sides of the rack (16) are provided with teeth meshing with the transmission gear (3). The other side of the transmission gear (3) is meshing with teeth (2) on the outer peripheral surface of the inner wing (9). The rear end of the rack is provided with a rack transmission rod (30) inserted into a powder cartridge (14) fixed on the bearing plate. The powder cartridge (14) is fixed on the wing bearing plate (8) through a powder cartridge positioning device (15).

2. The M-shaped synchronous deployment device for the wing of a tube-launched UAV according to claim 1 is characterized in that: The rectangular block (1) is located at the edge of the inner wing shaft side, and an elastic rubber block is provided on the rectangular block (1) as an energy absorbing buffer. When the wing rotates to a limited position, the wing abuts against the energy absorbing buffer.

3. The M-shaped synchronous deployment device for the wing of a tube-launched UAV according to claim 1 is characterized in that: The starting point of the circular arc groove (7) is located on the wing bearing plate (8) below the center line of the inner wing, and the outward rotation angle is 90 degrees. The end point of the circular arc groove is provided with an inner wing spring pin hole (20). When the inner wing (9) is unfolded to 90 degrees, the inner wing (9) abuts against the rectangular block (1) to stop moving, and the inner wing spring pin (28) slides into the inner wing spring pin hole (20) at the end point of the circular arc groove, thereby achieving the limit of the inner wing (9).

4. The M-shaped synchronous deployment device for the wing of a tube-launched UAV according to claim 1 is characterized in that: The inner wing (9) is also provided with an inner wing bearing (51), an inner wing cover plate (6), and an inner wing bolt (18) from bottom to top, with the rotation axis of the inner wing (9) as the axis. The inner wing (9) is fixed to the inner wing shaft (19) through the inner wing cover plate (6) and the inner wing bolt (18), and the inner wing bearings (51) are arranged above and below to ensure that the inner wing (9) can rotate normally when subjected to lift.

5. The M-shaped synchronous deployment device for the tube-launched UAV wing according to claim 1 is characterized in that: The outer wing (10) is arranged with an outer wing bearing (13), an outer wing cover plate (17), and an outer wing bolt (29) from bottom to top with the rotation axis of the outer wing (10) as the axis. The outer wing bolt (29) and the outer wing cover plate (17) connect the outer wing (10) and the stepped shaft (25). The outer wing bearing (13) is arranged between the outer wing cover plate (17) and the outer wing (10) to ensure that the outer wing (10) can rotate normally when subjected to lift.

6. The M-shaped synchronous deployment device for the tube-launched UAV wing according to claim 1 is characterized in that: An outer wing spring pin pit (22) is also provided on the stepped shaft (25). When the outer wing (10) is unfolded to 180 degrees, the torsion spring (11) stops pulling the outer wing (10), and the outer wing spring pin (23) slides into the outer wing spring pin pit (22) in the stepped shaft, thereby achieving the limiting of the outer wing (10).

7. The M-shaped synchronous deployment device for the tube-launched UAV wing according to claim 1 is characterized in that: The wing bearing plate (8) is provided with a weight-reducing groove (27) between the boss (4) and the powder cartridge positioning device (15).

8. The M-shaped synchronous deployment device for the wing of a tube-launched UAV according to claim 1 is characterized in that: The transmission gear bearing (5), the transmission gear (3), the transmission gear bearing (5), the transmission gear cover plate (31), and the transmission gear screw (24) are arranged from bottom to top with the transmission gear shaft (26) as the axis, so as to achieve stable transmission during the deployment of the transmission gear (3).

9. The M-shaped synchronous deployment device for the tube-launched UAV wing according to claim 1 is characterized in that: The UAV is in a folded state when launched with the shell, and the unfolding of the inner wing (9) and the outer wing (10) is limited by the shell wall. After launching, the UAV is separated from the shell body and the gunpowder in the gunpowder cartridge (14) is detonated to unfold the inner wing (9). At the same time, the torsion spring (11) causes the inner wing (9) and the outer wing (10) to move relative to each other, so that the wing group unfolds in an M shape; when the four wings are unfolded, the four wings are on the same straight line.

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