Folding wing unmanned aerial vehicle

Abstract

The invention provides a folding wing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the folding wing unmanned aerial vehicle comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a fuselage shell, a folding wing bracket base is longitudinally and slidably mounted in the fuselage shell, and a pair of folding wing second brackets is longitudinally and slidably mounted at the top of the front end of the folding wing bracket base; the folding wing second supports with different heights are longitudinally and rotatably provided with folding wing first supports, the folding wing first supports are transversely and rotatably provided with unmanned aerial vehicle folding wings, and the front ends of the folding wing first supports are transversely and slidably provided with adjusting keys. The folding wings of the unmanned aerial vehicle are protected through the fuselage shell, and the folding wings are prevented from being damaged due to collision or shaking when located outside; the folding wings of the unmanned aerial vehicle are loaded through the folding wing first supports, so that the folding wings can freely adjust the angle during flight, and the flight state of the unmanned aerial vehicle is adjusted.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a folding-wing UAV. Background Art

[0002] Compared to traditional drones, folding-wing drones have a unique wing-folding design that allows the wings to be folded up when not in use, significantly reducing the overall size of the drone and greatly improving its transport convenience and portability. However, when existing folding-wing drones are folded and stored, the wings are usually folded outside the fuselage, making the wings vulnerable to bumps or shaking, resulting in damage.

[0003] Based on this, the present invention provides a folding-wing UAV. Summary of the Invention

[0004] In response to the above technical problems, the present invention provides a folding-wing UAV, comprising a UAV body, a UAV head is fixedly installed at the front end of the UAV body, a UAV tail is fixedly installed at the rear end of the UAV body, the UAV body comprises a fuselage shell, a folding wing bracket base is longitudinally slidably installed in the fuselage shell, a pair of folding wing second brackets are longitudinally slidably installed on the front end top of the folding wing bracket base, a folding wing first bracket is longitudinally rotatably installed on the folding wing second bracket, a UAV folding wing is transversely rotatably installed on the folding wing first bracket, an adjustment key is transversely slidably installed at the front end of the folding wing first bracket, a pair of support push rods are transversely rotatably installed in the fuselage shell, a connecting rod is fixedly installed at the bottom of the support push rod, and the connecting rod at the bottom of the support push rod is hinged to the adjustment key on the folding wing first bracket at the corresponding position of the support push rod.

[0005] Furthermore, a bracket adjustment plate is installed in the base of the folding wing bracket for horizontal sliding in the front and rear directions, an adjustment push block is installed for longitudinal sliding on the top front end of the bracket adjustment plate, push rods are fixedly installed on both sides of the top of the adjustment push block, and the push rods on the adjustment push block are in contact with the support push rods.

[0006] Furthermore, the two folding wing second brackets slide with each other, one of the folding wing second brackets is separated from the folding wing bracket base by a certain distance, a compression spring is fixedly installed between the separated folding wing second bracket and the folding wing bracket base to control the height difference between the two folding wing second brackets, and a torsion spring is fixedly installed between the folding wing first bracket and the folding wing second bracket.

[0007] Furthermore, a first adjusting motor is fixedly mounted on the front end of the body shell, a threaded rod is fixedly mounted on the first adjusting motor, and the threaded rod on the first adjusting motor cooperates with the adjusting push block screw.

[0008] Furthermore, the folding wing of the drone is rotatably mounted on the outside of the corresponding folding wing first bracket, a second adjusting motor is fixedly mounted on the other side of the first folding wing bracket, a gear is fixedly mounted on the second adjusting motor, a limit key is fixedly mounted on the other end of the first folding wing bracket, an adjustment limit block is fixedly mounted on the folding wing of the drone, a rack is fixedly mounted on the inside of the adjustment limit block, the rack on the inside of the adjustment limit block is engaged with the gear on the second adjusting motor, a limit groove is provided on the outside of the adjustment limit block, and the limit groove on the outside of the adjustment limit block slides with the limit key on the first folding wing bracket.

[0009] Furthermore, the tail of the drone includes a tail bracket, which is fixedly mounted on the rear end of the fuselage shell, and tail adjustment rods are rotatably mounted on both sides of the tail bracket, and a movable tail is rotatably mounted on the tail adjustment rod, and a fourth adjustment motor is fixedly mounted on the tail adjustment rod, and the fourth adjustment motor is fixedly connected to the tail adjustment rod, and a third adjustment motor is fixedly mounted in the tail bracket, and a threaded rod is fixedly mounted on the third adjustment motor, and an adjustment sliding plate is slidably mounted in the tail adjustment rod, and the adjustment sliding plate cooperates with the threaded rod and screw on the third adjustment motor, and adjustment bevels are provided on both sides of the tail adjustment rod, and adjustment support blocks are longitudinally slidably mounted on both sides of the adjustment sliding plate, and the adjustment support block slidably cooperates with the adjustment bevel, and a transverse cylindrical key is fixedly mounted on the adjustment support block, and a slide groove is provided on the tail adjustment rod, and the cylindrical key on the adjustment support block slidably cooperates with the slide groove on the tail adjustment rod.

[0010] Furthermore, a tail protection plate is fixedly mounted on the outer side of the tail bracket.

[0011] Furthermore, a slide groove is provided at the bottom inner side of the fuselage shell, an adjustment inclined plate is installed in the slide groove, an adjustment protrusion is fixedly installed at the bottom of the bracket adjustment plate, and the protrusion at the bottom of the bracket adjustment plate slides with the inclined plate at the bottom of the fuselage shell.

[0012] Furthermore, a curved windshield is slidably installed inside the bottom of the fuselage shell, and a compression spring is fixedly installed between the curved windshield and the fuselage shell.

[0013] Furthermore, protective baffles are fixedly installed on both sides of the outer wall of the fuselage shell, and the first folding wing bracket contacts and cooperates with the protective baffles.

[0014] Compared with the prior art, the present invention has the following advantages: (1) the present invention staggers the folding wings of the drone into the interior of the fuselage shell through two folding wing second brackets of different heights, and protects the folding wings of the drone through the fuselage shell to prevent the folding wings from being easily damaged by impact or shaking when they are outside; (2) the present invention seals the storage compartment on the fuselage shell through an arc-shaped windshield plate, which can ensure the stability of the drone during flight; (3) the present invention loads the folding wings of the drone through the folding wing first bracket, so that the folding wings can freely adjust the angle during flight, thereby adjusting the flight state of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the top structure of the present invention.

[0016] Figure 2 It is a side structural schematic diagram of the present invention.

[0017] Figure 3 It is a schematic diagram of the overall structure of the present invention.

[0018] Figure 4 This is a schematic diagram of the structure of the present invention.

[0019] Figure 5 It is a schematic diagram of the half-section structure of the present invention.

[0020] Figure 6 It is a schematic diagram of the partial cross-section structure of the drone fuselage of the present invention.

[0021] Figure 7 It is a schematic diagram of the half-section structure of the drone fuselage of the present invention.

[0022] Figure 8 This is a schematic diagram of the assembly structure of the second bracket of the folding wing of the present invention.

[0023] Figure 9 This is a schematic diagram of the partial cross-section structure of the tail of the UAV of the present invention.

[0024] Figure 10 This is a schematic diagram of the half-section structure of the tail of the UAV of the present invention.

[0025] Figure 11 This is a schematic diagram of the assembly structure of the movable tail wing of the present invention.

[0026] Figure 12 It is a schematic diagram of the bottom structure of the fuselage shell of the present invention.

[0027] Figure 13 This is a schematic diagram of the overall structure of the folding wings of the UAV of the present invention.

[0028] Figure 14 for Figure 7 A1 is an enlarged schematic diagram of the structure.

[0029] Figure 15 for Figure 11 Enlarged structural diagram at B1 in the middle.

[0030] Figure 16 for Figure 13 Enlarged structural diagram of C1 in the middle.

[0031] Figure markings: 1-UAV head; 2-UAV body; 3-UAV tail; 201-fuselage shell; 202-protective baffle; 203-support push rod; 204-folding wing first bracket; 205-adjustment key; 206-folding wing second bracket; 207-folding wing bracket base; 208-bracket adjustment plate; 209-adjustment push block; 210-first adjustment motor; 211-second adjustment motor; 212-UAV folding wing; 213-arc windshield; 214-adjustment limit block; 301-tail bracket; 302-tail adjustment rod; 303-movable tail; 304-adjustment support block; 305-third adjustment motor; 306-adjustment sliding plate; 307-adjustment chute; 308-fourth adjustment motor; 309-tail protection plate. DETAILED DESCRIPTION

[0032] The technical solution provided by the present invention will be further described below with reference to the accompanying drawings and according to specific implementation methods.

[0033] like Figures 1 to 16As shown, a folding-wing UAV includes a UAV body 2, a UAV head 1 is fixedly mounted on the front end of the UAV body 2, a UAV tail 3 is fixedly mounted on the rear end of the UAV body 2, the UAV body 2 includes a fuselage shell 201, a folding-wing bracket base 207 is longitudinally slidably mounted in the fuselage shell 201, a pair of folding-wing second brackets 206 are longitudinally slidably mounted on the top of the front end of the folding-wing bracket base 207, the two folding-wing second brackets 206 slide in cooperation with each other, one of the folding-wing second brackets 206 is spaced a certain distance from the folding-wing bracket base 207, and the folding-wing second brackets 206 separated by the distance are in contact with the folding-wing bracket base 207. A compression spring is fixedly installed between the frame base 207 to control the height difference between the two folding wing second brackets 206, which is used to make the wings staggered when folded and stored, so that the folding wings can be stored inside the drone cabin. The folding wing first bracket 204 is longitudinally rotated and installed on the folding wing second bracket 206. A torsion spring is fixedly installed between the folding wing first bracket 204 and the folding wing second bracket 206 to control the automatic storage of the drone folding wings. The drone folding wings 212 are installed on the folding wing first bracket 204 for transverse rotation. The front end of the folding wing first bracket 204 is laterally slidably installed with an adjustment key 205. A pair of support push rods 203 are installed in the fuselage shell 201 for horizontal rotation. A connecting rod is fixedly installed at the bottom of the support push rod 203. The connecting rod at the bottom of the support push rod 203 is hinged with the adjustment key 205 on the first bracket 204 of the folding wing at the corresponding position of the support push rod 203. A bracket adjustment plate 208 is installed in the folding wing bracket base 207 for horizontal sliding in the front and back directions. An adjustment push block 209 is installed for longitudinal sliding on the top of the front end of the bracket adjustment plate 208. Push rods are fixedly installed on both sides of the top of the adjustment push block 209. The push rods on the adjustment push block 209 are in contact with the support push rod 203. The first adjustment plate 208 is fixedly installed at the front end of the fuselage shell 201. The energy-saving motor 210 and the first adjusting motor 210 are fixedly installed with a threaded rod. The threaded rod on the first adjusting motor 210 cooperates with the screw rod of the adjusting push block 209. By starting the first adjusting motor 210, the threaded rod is driven to rotate. The rotation of the threaded rod drives the adjusting push block 209 to push the bracket adjustment plate 208 to slide in the folding-wing bracket base 207. The push rod on the adjusting push block 209 pushes the supporting push rod 203 to rotate in the fuselage shell 201. When the supporting push rod 203 rotates, it drives the first folding-wing bracket 204 to flip outward on the second folding-wing bracket 206 through the connecting rod at the bottom, thereby unfolding the folding wing 212 of the drone.

[0034] like Figures 1 to 16As shown, protective baffles 202 are fixedly installed on both sides of the outer wall of the fuselage shell 201, and the first folding wing bracket 204 contacts and cooperates with the protective baffle 202 to protect the first folding wing bracket 204 when the folding wing is unfolded to prevent the first folding wing bracket 204 from being damaged by foreign objects during flight. A slide groove is provided at the bottom inside the fuselage shell 201, and an adjustment inclined plate is installed in the slide groove. An adjustment protrusion is fixedly installed at the bottom of the bracket adjustment plate 208, and the protrusion at the bottom of the bracket adjustment plate 208 slides with the inclined plate at the bottom of the fuselage shell 201. When the first adjustment motor 210 pushes the adjustment push block 209 to drive the bracket to adjust When the plate 208 slides in the folding-wing bracket base 207, the convex block at the bottom of the bracket adjustment plate 208 cooperates with the inclined plate to drive the folding-wing bracket base 207 to slide upward in the fuselage shell 201, driving the folding-wing second bracket 206 to slide upward. When the folding-wing second bracket 206 slides to the top of the fuselage shell 201, the folding-wing second bracket 206 contacts the top of the inner compartment of the fuselage shell 201, compressing the separated folding-wing second bracket 206 to the same height as the other folding-wing second bracket 206, so that the two drone folding wings 212 are in the same horizontal position so that they can be used normally.

[0035] like Figures 1 to 16 As shown, the folding wing 212 of the drone is rotatably mounted on the outside of the corresponding folding wing first bracket 204, and a second adjusting motor 211 is fixedly mounted on the other side of the folding wing first bracket 204. A gear is fixedly mounted on the second adjusting motor 211, and a limit key is fixedly mounted on the other end of the folding wing first bracket 204. An adjustment limit block 214 is fixedly mounted on the folding wing 212 of the drone, and a rack is fixedly mounted on the inner side of the adjustment limit block 214. The rack on the inner side of the adjustment limit block 214 engages with the gear on the second adjusting motor 211. A limit groove is provided on the outer side of the adjustment limit block 214. The limit groove on the outer side of the adjustment limit block 214 slides with the limit key on the folding wing first bracket 204 to limit the rotation range of the drone folding wing 212 on the folding wing first bracket 204. During the flight of the drone, the second adjusting motor 211 is started to drive the drone folding wing 212 to rotate on the folding wing first bracket 204, so as to adjust the angle of the folding wing, thereby adjusting the direction and height of the drone during flight.

[0036] like Figures 1 to 16 As shown, an arc-shaped windshield 213 is slidably installed inside the bottom of the fuselage shell 201, and a compression spring is fixedly installed between the arc-shaped windshield 213 and the fuselage shell 201, which is used to seal the cavity left on the fuselage shell 201 after the folding wings are unfolded through the arc-shaped windshield 213 to prevent the cavity from affecting the stability of the drone during flight.

[0037] like Figures 1 to 16As shown, the tail 3 of the drone includes a tail bracket 301, which is fixedly mounted on the rear end of the fuselage shell 201, and tail adjustment rods 302 are installed on both sides of the tail bracket 301 for transverse rotation. A movable tail 303 is rotatably installed on the tail adjustment rod 302, and a fourth adjustment motor 308 is fixedly installed on the tail adjustment rod 302. The fourth adjustment motor 308 is fixedly connected to the tail adjustment rod 302, and a tail protection plate 309 is fixedly mounted on the outside of the tail bracket 301. The tail protection plate 309 is used to protect the movable tail 303 to prevent the movable tail 303 from being damaged by impact and shaking during transportation. A third adjustment motor 305 is fixedly mounted in the tail bracket 301, and a threaded rod is fixedly mounted on the third adjustment motor 305. An adjustment sliding plate 306 is installed in the tail adjustment rod 302 for transverse sliding movement, and the adjustment sliding plate 306 is aligned with the third adjustment motor 305. The screw rod and the lead screw cooperate, and adjustment bevel grooves 307 are provided on both sides of the tail adjustment rod 302. Adjustment support blocks 304 are longitudinally slidably installed on both sides of the adjustment sliding plate 306. The adjustment support blocks 304 slide and cooperate with the adjustment bevel grooves 307. A transverse cylindrical key is fixedly installed on the adjustment support block 304. The tail adjustment rod 302 is provided with a slide groove. The cylindrical key on the adjustment support block 304 slides and cooperates with the slide groove on the tail adjustment rod 302. By starting the third adjustment motor 305, the adjustment sliding plate 306 is driven to slide horizontally in the tail bracket 301. At the same time, the adjustment support block 304 is driven to slide upward on the adjustment sliding plate 306 through the adjustment bevel groove 307. The tail adjustment rod 302 is driven to flip upward on the tail bracket 301 through the adjustment support block 304, and the movable tail 303 is unfolded. Then, the angle of the movable tail 303 during flight can be adjusted by starting the fourth adjustment motor 308.

[0038] Working principle: When the drone is activated, the first adjustment motor 210 is started to drive the bracket adjustment plate 208 to slide horizontally in the fuselage shell 201, and the push rod on the adjustment push block 209 is used to push the folding wing first bracket 204 to flip outward to unfold the drone folding wings 212. At the same time, the folding wing bracket base 207 and the bracket adjustment plate 208 are driven to slide longitudinally in the fuselage shell 201, and the folding wing second bracket 206 is driven to rise in the fuselage shell 201, so that the folding wing second bracket 206 contacts the top of the inner compartment of the fuselage shell 201, so that the two folding wing second brackets 206 are at the same height, and the two drone folding wings 212 are controlled to be in the same horizontal position. At the same time, the folding wing first bracket 204 is slid to the inside of the protective baffle 202 to protect the folding wing first bracket 204.

[0039] After the folding wings are unfolded, the arc-shaped windshield plate 213 is ejected by the compression spring to seal the cavities on both sides of the fuselage shell 201, thereby preventing the cavities from affecting the flight stability of the UAV during flight.

[0040] By starting the third adjustment motor 305 to drive the adjustment sliding plate 306 to slide, and by adjusting the sliding plate 306 to drive the adjustment support block 304 to slide upward to unfold the movable tail 303, the angle between the two movable tails 303 during the flight of the drone can be adjusted by starting the fourth adjustment motor 308 to adjust the flight state.

[0041] When the drone is stored, the folding wings 212 of the drone are stored inside the fuselage shell 201, and the movable tail 303 is protected by the tail protection plate 309, which can effectively prevent the folding wings from being damaged due to collision and shaking during transportation.

Claims

1. A folding-wing drone, comprising a drone body (2), a drone head (1) fixedly mounted on the front end of the drone body (2), a drone tail (3) fixedly mounted on the rear end of the drone body (2), the drone body (2) comprising a body shell (201), characterized in that: A folding wing bracket base (207) is longitudinally slidably installed in the fuselage shell (201), a pair of folding wing second brackets (206) are longitudinally slidably installed on the front end top of the folding wing bracket base (207), a folding wing first bracket (204) is longitudinally rotatably installed on the folding wing second bracket (206), a drone folding wing (212) is transversely rotatably installed on the folding wing first bracket (204), an adjustment key (205) is transversely slidably installed on the front end of the folding wing first bracket (204), a pair of support push rods (203) are transversely rotatably installed in the fuselage shell (201), a connecting rod is fixedly installed at the bottom of the support push rod (203), and the connecting rod at the bottom of the support push rod (203) is hinged to the adjustment key (205) on the folding wing first bracket (204) at a corresponding position of the support push rod (203); A bracket adjustment plate (208) is installed in the folding wing bracket base (207) in a transversely sliding manner in the front and rear directions. An adjustment push block (209) is installed in a longitudinally sliding manner on the top of the front end of the bracket adjustment plate (208). Push rods are fixedly installed on both sides of the top of the adjustment push block (209). The push rods on the adjustment push block (209) are in contact with the support push rod (203).

2. A folding-wing UAV according to claim 1, characterized in that: The two folding-wing second brackets (206) are slidably matched with each other, and a certain distance is separated between one of the folding-wing second brackets (206) and the folding-wing bracket base (207). A compression spring is fixedly installed between the folding-wing second bracket (206) and the folding-wing bracket base (207) at the distance to control the height difference between the two folding-wing second brackets (206). A torsion spring is fixedly installed between the folding-wing first bracket (204) and the folding-wing second bracket (206).

3. The folding-wing UAV according to claim 1, characterized in that: A first adjustment motor (210) is fixedly mounted on the front end of the body shell (201), a threaded rod is fixedly mounted on the first adjustment motor (210), and the threaded rod on the first adjustment motor (210) cooperates with a screw rod of the adjustment push block (209).

4. The folding-wing UAV according to claim 1, characterized in that: The drone folding wing (212) is rotatably mounted on the outer side of the corresponding folding wing first bracket (204); a second regulating motor (211) is fixedly mounted on the other side of the folding wing first bracket (204); a gear is fixedly mounted on the second regulating motor (211); a limit key is fixedly mounted on the other end of the folding wing first bracket (204); an regulating limit block (214) is fixedly mounted on the drone folding wing (212); a rack is fixedly mounted on the inner side of the regulating limit block (214); the rack on the inner side of the regulating limit block (214) is meshed with the gear on the second regulating motor (211); a regulating limit groove is provided on the outer side of the regulating limit block (214); the regulating limit groove on the outer side of the regulating limit block (214) is slidably matched with the limit key on the folding wing first bracket (204).

5. The folding-wing UAV according to claim 1, characterized in that: The tail portion (3) of the UAV includes a tail bracket (301), the tail bracket (301) is fixedly mounted on the rear end of the fuselage shell (201), tail adjustment rods (302) are laterally rotatably mounted on both sides of the tail bracket (301), a movable tail (303) is rotatably mounted on the tail adjustment rod (302), a fourth adjustment motor (308) is fixedly mounted on the tail adjustment rod (302), the fourth adjustment motor (308) is fixedly connected to the tail adjustment rod (302), a third adjustment motor (305) is fixedly mounted in the tail bracket (301), a threaded rod is fixedly mounted on the third adjustment motor (305), and the tail adjustment An adjusting sliding plate (306) is installed in the section rod (302) for transverse sliding. The adjusting sliding plate (306) cooperates with the threaded rod screw on the third adjusting motor (305). Adjusting inclined grooves (307) are provided on both sides of the tail adjusting rod (302). Adjusting support blocks (304) are installed on both sides of the adjusting sliding plate (306) for longitudinal sliding. The adjusting support blocks (304) are slidably engaged with the adjusting inclined grooves (307). A transverse cylindrical key is fixedly installed on the adjusting support block (304). A slide groove is provided on the tail adjusting rod (302). The cylindrical key on the adjusting support block (304) is slidably engaged with the slide groove on the tail adjusting rod (302).

6. The folding-wing UAV according to claim 5, characterized in that: A tail protection plate (309) is fixedly mounted on the outside of the tail bracket (301).

7. The folding-wing UAV according to claim 1, characterized in that: The bottom inner side of the fuselage shell (201) is provided with a slide groove, an adjustment inclined plate is installed in the slide groove, and an adjustment protrusion is fixedly installed on the bottom of the bracket adjustment plate (208), and the protrusion at the bottom of the bracket adjustment plate (208) is slidably matched with the inclined plate at the bottom of the fuselage shell (201).

8. The folding-wing UAV according to claim 1, characterized in that: An arc-shaped windshield plate (213) is slidably mounted inside the bottom of the fuselage shell (201), and a compression spring is fixedly mounted between the arc-shaped windshield plate (213) and the fuselage shell (201).

9. The folding-wing UAV according to claim 1, characterized in that: Protective baffles (202) are fixedly mounted on both sides of the outer wall of the fuselage shell (201), and the first folding wing bracket (204) is in contact with and fits the protective baffles (202).

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