A folding wing drone

Abstract

The application provides a folding wing unmanned plane, and relates to the technical field of unmanned planes, which comprises a plane body, wherein the plane body comprises a plane body shell, a folding wing support base is longitudinally slidably arranged in the plane body shell, a pair of folding wing second supports are longitudinally slidably arranged on the top of the front end of the folding wing support base, folding wing first supports are longitudinally rotatably arranged on the folding wing second supports, unmanned plane folding wings are transversely rotatably arranged on the folding wing first supports, and adjusting keys are transversively slidably arranged on the front end of the folding wing first supports. The unmanned plane folding wings are staggered and stored in the plane body shell through the folding wing second supports with different heights, the unmanned plane folding wings are protected by the plane body shell, and the unmanned plane folding wings are prevented from being damaged due to impacts or shaking when being outside. The unmanned plane folding wings are loaded on the folding wing first supports, so that the folding wings can be freely adjusted in angle when flying, and the flight state of the unmanned plane is adjusted.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a folding-wing UAV. Background Technology

[0002] Compared to traditional drones, folding-wing drones, with their unique wing-folding design, can fold their wings away when not in use, significantly reducing the overall size of the drone and greatly improving transportation convenience and portability.

[0003] However, existing folding-wing drones typically fold their wings to the outside of the fuselage when folding and storing them, making the wings susceptible to damage from bumps or shaking.

[0004] Based on this, the present invention provides a folding-wing drone. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a folding-wing drone, comprising a drone body, a drone head fixedly mounted at the front end of the drone body, and a drone tail fixedly mounted at the rear end of the drone body. The drone body includes a fuselage shell, within which a folding-wing bracket base is longitudinally slidably mounted. A pair of second folding-wing brackets are longitudinally slidably mounted at the top front end of the folding-wing bracket base. A first folding-wing bracket is longitudinally rotatably mounted on the second folding-wing brackets, and a drone folding wing is laterally rotatably mounted on the first folding-wing bracket. An adjustment key is laterally slidably mounted at the front end of the first folding-wing bracket. A pair of support push rods are laterally rotatably mounted within the fuselage shell, and a connecting rod is fixedly mounted at the bottom of each support push rod. The connecting rod at the bottom of the support push rod is hinged to the adjustment key on the first folding-wing bracket at a corresponding position on the support push rod.

[0006] Furthermore, a bracket adjustment plate is slidably installed in the base of the folding wing bracket in the front-back direction, and an adjustment push block is slidably installed in 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.

[0007] Furthermore, the two folding wing second supports slide against each other, with one of the folding wing second supports separated from the folding wing support base by a certain distance. A compression spring is fixedly installed between the folding wing second support separated from the folding wing support base to control the height difference between the two folding wing second supports. A torsion spring is fixedly installed between the folding wing first support and the folding wing second support.

[0008] Furthermore, a first adjusting motor is fixedly installed at the front end of the housing, and a threaded rod is fixedly installed on the first adjusting motor. The threaded rod on the first adjusting motor cooperates with the adjusting push block screw.

[0009] Furthermore, the folding wing of the drone is rotatably mounted on the outside of the corresponding first bracket of the folding wing. A second adjustment motor is fixedly mounted on the other side of the first bracket of the folding wing, and a gear is fixedly mounted on the second adjustment motor. A limit key is fixedly mounted on the other end of the first bracket of the folding wing. An adjustment limit block is fixedly mounted on the folding wing of the drone. A rack is fixedly mounted on the inner side of the adjustment limit block. The rack on the inner side of the adjustment limit block meshes with the gear on the second adjustment motor. A limit groove is provided on the outer side of the adjustment limit block. The limit groove on the outer side of the adjustment limit block slides in cooperation with the limit key on the first bracket of the folding wing.

[0010] Furthermore, the tail section of the UAV includes a tail fin support bracket, which is fixedly installed at the rear end of the fuselage shell. Tail fin adjustment rods are laterally rotatably mounted on both sides of the tail fin support bracket. A movable tail fin is rotatably mounted on the tail fin adjustment rods. A fourth adjustment motor is fixedly mounted on the tail fin adjustment rods and is fixedly connected to the tail fin adjustment rods. A third adjustment motor is fixedly mounted inside the tail fin support bracket, and a threaded rod is fixedly mounted on the third adjustment motor. An adjustment sliding plate is laterally slidably mounted inside the tail fin adjustment rods, and the adjustment sliding plate engages with the threaded rod on the third adjustment motor. Adjustment grooves are provided on both sides of the tail fin adjustment rods. Adjustment support blocks are longitudinally slidably mounted on both sides of the adjustment sliding plate, and the adjustment support blocks engage with the adjustment grooves. A transverse cylindrical key is fixedly mounted on the adjustment support block. A sliding groove is provided on the tail fin adjustment rod, and the cylindrical key on the adjustment support block engages with the sliding groove on the tail fin adjustment rod.

[0011] Furthermore, a tail wing protection plate is fixedly installed on the outer side of the tail wing bracket.

[0012] Furthermore, a sliding groove is provided on the bottom inner side of the housing, and an adjusting ramp is installed in the sliding groove. An adjusting protrusion is fixedly installed on the bottom of the bracket adjusting plate, and the protrusion on the bottom of the bracket adjusting plate slides in cooperation with the ramp at the bottom of the housing.

[0013] Furthermore, an arc-shaped wind deflector is slidably installed inside the bottom of the casing, and a compression spring is fixedly installed between the arc-shaped wind deflector and the casing.

[0014] Furthermore, protective baffles are fixedly installed on both sides of the outer wall of the fuselage shell, and the first bracket of the folding wing contacts and cooperates with the protective baffles.

[0015] The beneficial effects of this invention compared with the prior art are: (1) This invention uses two folding wing second brackets of different heights to stagger the folding wings of the drone into the fuselage shell, and protects the folding wings of the drone by the fuselage shell, so as to avoid the folding wings being easily damaged by impact or shaking when they are outside; (2) This invention uses an arc-shaped wind deflector to seal the storage compartment on the fuselage shell, which can ensure the stability of the drone during flight; (3) This invention uses the folding wing first bracket to load the folding wings of the drone, so that the folding wings can freely adjust the angle during flight and adjust the flight state of the drone. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the top structure of the present invention.

[0017] Figure 2 This is a side view of the present invention.

[0018] Figure 3 This is a schematic diagram of the overall structure of the present invention.

[0019] Figure 4 This is a schematic diagram of the unfolded structure of the present invention.

[0020] Figure 5 This is a schematic diagram of the half-section structure of the present invention.

[0021] Figure 6 This is a schematic diagram of a partial cross-sectional structure of the unmanned aerial vehicle (UAV) of the present invention.

[0022] Figure 7 This is a schematic diagram of the half-section structure of the unmanned aerial vehicle (UAV) of the present invention.

[0023] Figure 8 This is a schematic diagram of the assembly structure of the second bracket of the folding wing of the present invention.

[0024] Figure 9 This is a schematic diagram of a partial cross-sectional structure of the tail section of the UAV of the present invention.

[0025] Figure 10 This is a schematic diagram of the half-section structure of the tail section of the UAV of the present invention.

[0026] Figure 11 This is a schematic diagram of the assembly structure of the movable tail fin of the present invention.

[0027] Figure 12 This is a schematic diagram of the bottom structure of the outer casing of the present invention.

[0028] Figure 13 This is a schematic diagram of the overall structure of the folding wing of the UAV of the present invention.

[0029] Figure 14 for Figure 7 Enlarged structural diagram at point A1.

[0030] Figure 15 for Figure 11 Enlarged structural diagram at point B1.

[0031] Figure 16 for Figure 13 Enlarged structural diagram at point C1.

[0032] Reference numerals: 1-UAV head; 2-UAV body; 3-UAV tail; 201-Fuselage shell; 202-Protective baffle; 203-Support push rod; 204-First folding wing bracket; 205-Adjustment key; 206-Second folding wing 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-shaped windshield; 214-Adjustment limit block; 301-Tail wing bracket; 302-Tail wing adjustment rod; 303-Movable tail wing; 304-Adjustment support block; 305-Third adjustment motor; 306-Adjustment sliding plate; 307-Adjustment sloping groove; 308-Fourth adjustment motor; 309-Tail wing protection plate. Detailed Implementation

[0033] The technical solution provided by the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0034] like Figures 1 to 16As shown, a folding-wing drone includes a drone body 2, a drone head 1 fixedly mounted at the front end of the drone body 2, and a drone tail 3 fixedly mounted at the rear end of the drone body 2. The drone body 2 includes a fuselage shell 201, and a folding wing support base 207 is longitudinally slidably mounted inside the fuselage shell 201. A pair of folding wing second supports 206 are longitudinally slidably mounted on the top front end of the folding wing support base 207. The two folding wing second supports 206 slide and cooperate with each other, with one of the folding wing second supports 206 spaced apart from the folding wing support base 207 by a certain distance. The spaced-apart folding wing second supports 206 and the folding wing support base 207 are connected by a certain distance. A compression spring is fixedly installed between the bases 207 to control the height difference between the two second folding wing brackets 206, allowing the wings to fold alternately during storage, facilitating their insertion into the drone's cabin. A first folding wing bracket 204 is longitudinally rotatably mounted on the second folding wing bracket 206. A torsion spring is fixedly installed between the first folding wing bracket 204 and the second folding wing bracket 206 to control the automatic storage of the drone's folding wings. A drone folding wing 212 is laterally rotatably mounted on the first folding wing bracket 204. An adjustment key 205 is laterally slidably mounted on the front end of the first folding wing bracket 204. A pair of support push rods 203 are horizontally rotatably installed inside the outer shell 201. 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 to 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 horizontally slidably installed in the front-rear direction inside the bracket base 207. An adjustment push block 209 is vertically slidably installed at the top 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 contact and cooperate with the support push rods 203. The first adjustment key 205 is fixedly installed at the front end of the outer shell 201. The first adjusting motor 210 has a threaded rod fixedly installed on it. The threaded rod on the first adjusting motor 210 cooperates with the lead screw 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 adjusting plate 208 to slide inside the folding wing bracket base 207. The push rod on the adjusting push block 209 pushes the support push rod 203 to rotate inside the fuselage shell 201. When the support 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, thus unfolding the folding wing 212 of the UAV.

[0035] like Figures 1 to 16As shown, protective baffles 202 are fixedly installed on both sides of the outer wall of the fuselage shell 201. The first folding wing bracket 204 is in contact with the protective baffles 202 to protect the first folding wing bracket 204 when the folding wing is deployed, preventing damage to the first folding wing bracket 204 from foreign objects during flight. A sliding groove is provided on the bottom inner side of the fuselage shell 201, and an adjusting ramp is installed in the sliding groove. An adjusting protrusion is fixedly installed on the bottom of the bracket adjusting plate 208. The protrusion at the bottom of the bracket adjusting plate 208 slides in contact with the ramp at the bottom of the fuselage shell 201. When the first adjusting motor 210 pushes the adjusting push block 209, the bracket is adjusted. When plate 208 slides inside folding wing bracket base 207, the cooperation between the protrusion at the bottom of bracket adjustment plate 208 and the inclined plate drives folding wing bracket base 207 to slide upward inside fuselage shell 201, driving folding wing second bracket 206 to slide upward. When folding wing second bracket 206 slides to the top of the fuselage shell 201, folding wing second bracket 206 contacts the top of the inner compartment of fuselage shell 201, compressing the folding wing second bracket 206 that was separated by a distance 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 and can be used normally.

[0036] like Figures 1 to 16 As shown, the folding wing 212 of the drone is rotatably mounted on the outside of the corresponding first folding wing bracket 204. A second adjustment motor 211 is fixedly mounted on the other side of the first folding wing bracket 204. A gear is fixedly mounted on the second adjustment motor 211. A limit key is fixedly mounted on the other end of the first folding wing bracket 204. An adjustment limit block 214 is fixedly mounted on the folding wing 212 of the drone. 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 meshes with the gear on the second adjustment 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 and engages with the limit key on the first folding wing bracket 204 to limit the rotation range of the folding wing 212 of the drone on the first folding wing bracket 204. During the flight of the drone, by starting the second adjustment motor 211 to drive the folding wing 212 of the drone to rotate on the first folding wing bracket 204, the angle of the folding wing can be adjusted, thereby adjusting the direction and altitude of the drone during flight.

[0037] like Figures 1 to 16 As shown, an arc-shaped wind deflector 213 is slidably installed inside the bottom of the fuselage shell 201. A compression spring is fixedly installed between the arc-shaped wind deflector 213 and the fuselage shell 201. The arc-shaped wind deflector 213 is used to seal the cavity left on the fuselage shell 201 after the folding wings are unfolded, so as to prevent the cavity from affecting the stability of the UAV during flight.

[0038] like Figures 1 to 16As shown, the tail section 3 of the UAV includes a tail fin support 301, which is fixedly installed at the rear end of the fuselage shell 201. Tail fin adjustment rods 302 are laterally rotatably mounted on both sides of the tail fin support 301. A movable tail fin 303 is rotatably mounted on the tail fin adjustment rods 302. A fourth adjustment motor 308 is fixedly mounted on the tail fin adjustment rods 302 and is fixedly connected to the tail fin adjustment rods 302. A tail fin protection plate 309 is fixedly mounted on the outside of the tail fin support 301 to protect the movable tail fin 303 from damage caused by impact and shaking during transportation. A third adjustment motor 305 is fixedly installed inside the tail fin support 301, and a threaded rod is fixedly mounted on the third adjustment motor 305. An adjustment sliding plate 306 is laterally slidably mounted inside the tail fin adjustment rods 302. The adjustment sliding plate 306 is connected to the third adjustment motor 305. The tail fin adjusting rod 302 is fitted with a threaded rod and a lead screw. Adjusting grooves 307 are provided on both sides of the tail fin adjusting rod 302. Adjusting support blocks 304 are longitudinally slidably mounted on both sides of the adjusting sliding plate 306. The adjusting support blocks 304 are slidably engaged with the adjusting grooves 307. A transverse cylindrical key is fixedly mounted on the adjusting support block 304. The tail fin adjusting rod 302 is provided with a sliding groove. The cylindrical key on the adjusting support block 304 is slidably engaged with the sliding groove on the tail fin adjusting rod 302. By activating the third adjusting motor 305, the adjusting sliding plate 306 is driven to slide laterally within the tail fin support 301. Simultaneously, the adjusting grooves 307 drive the adjusting support blocks 304 to slide upwards on the adjusting sliding plate 306. The adjusting support blocks 304 drive the tail fin adjusting rod 302 to flip upwards on the tail fin support 301, unfolding the movable tail fin 303. Then, by activating the fourth adjusting motor 308, the angle of the movable tail fin 303 during flight can be adjusted.

[0039] Working principle: When the drone is activated, the first adjustment motor 210 drives the bracket adjustment plate 208 to slide laterally within the fuselage shell 201. The push rod on the adjustment push block 209 pushes the first folding wing bracket 204 to flip outward, unfolding the drone's folding wings 212. At the same time, the folding wing bracket base 207 and the bracket adjustment plate 208 slide longitudinally within the fuselage shell 201, causing the second folding wing bracket 206 to rise within the fuselage shell 201. This brings the second folding wing bracket 206 into contact with the top of the inner compartment of the fuselage shell 201, placing both second folding wing brackets 206 at the same height. This controls the two drone folding wings 212 to be in the same horizontal position. Simultaneously, the first folding wing bracket 204 slides into the protective baffle 202 for protection.

[0040] After the folding wings are deployed, the arc-shaped wind deflector 213 pops out through a compression spring to seal the cavities on both sides of the fuselage shell 201, preventing the cavities from affecting the flight stability of the UAV during flight.

[0041] By activating the third adjustment motor 305, the adjustment sliding plate 306 is driven to slide, and the adjustment support block 304 is driven to slide upward by the adjustment sliding plate 306 to unfold the movable tail fin 303. At the same time, the angle between the two movable tail fins 303 during the flight of the drone can be adjusted by activating the fourth adjustment motor 308, thereby adjusting the flight status.

[0042] When storing the drone, by storing the drone's folding wing 212 inside the fuselage shell 201 and protecting the movable tail wing 303 with the tail wing protection plate 309, the folding wing of the drone can be effectively prevented from being damaged by impact and shaking during transportation.

Claims

1. A folding-wing unmanned aerial vehicle (UAV), comprising a UAV fuselage (2), a UAV head (1) fixedly mounted at the front end of the UAV fuselage (2), a UAV tail (3) fixedly mounted at the rear end of the UAV fuselage (2), the UAV fuselage (2) comprising a fuselage shell (201), characterized in that, A folding wing bracket base (207) is longitudinally slidably installed inside the fuselage shell (201). A pair of second folding wing brackets (206) are longitudinally slidably installed on the front top of the folding wing bracket base (207). A first folding wing bracket (204) is longitudinally rotatably installed on the second folding wing bracket (206). A drone folding wing (212) is laterally rotatably installed on the first folding wing bracket (204). An adjustment key (205) is laterally slidably installed on the front end of the first folding wing bracket (204). A pair of support push rods (203) are laterally rotatably installed inside the fuselage shell (201). 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 to the adjustment key (205) on the first folding wing bracket (204) at the corresponding position of the support push rod (203). The bracket adjustment plate (208) is slidably installed in the folding wing bracket base (207) in the front-back direction. The adjustment push block (209) is slidably installed in 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 two folding wing second supports (206) slide against each other, and one of the folding wing second supports (206) is spaced apart from the folding wing support base (207) by a certain distance. A compression spring is fixedly installed between the folding wing second support (206) and the folding wing support base (207) at the distance to control the height difference between the two folding wing second supports (206). A torsion spring is fixedly installed between the folding wing first support (204) and the folding wing second support (206). The front end of the outer casing (201) is fixedly installed with a first adjusting motor (210), and a threaded rod is fixedly installed on the first adjusting motor (210). The threaded rod on the first adjusting motor (210) cooperates with the lead screw of the adjusting push block (209). The folding wing (212) of the UAV is rotatably mounted on the outside of the corresponding first bracket (204) of the folding wing. A second adjustment motor (211) is fixedly mounted on the other side of the first bracket (204) of the folding wing. A gear is fixedly mounted on the second adjustment motor (211). A limit key is fixedly mounted on the other end of the first bracket (204) of the folding wing. An adjustment limit block (214) is fixedly mounted on the folding wing (212) of the UAV. 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) meshes with the gear on the second adjustment 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 first bracket (204) of the folding wing. The tail section (3) of the UAV includes a tail fin support (301), which is fixedly installed at the rear end of the fuselage shell (201). Tail fin adjustment rods (302) are rotatably mounted on both sides of the tail fin support (301). A movable tail fin (303) is rotatably mounted on the tail fin adjustment rods (302). A fourth adjustment motor (308) is fixedly mounted on the tail fin adjustment rods (302), and the fourth adjustment motor (308) is fixedly connected to the tail fin adjustment rods (302). A third adjustment motor (305) is fixedly installed inside the tail fin support (301), and a threaded rod is fixedly mounted on the third adjustment motor (305). An adjusting sliding plate (306) is slidably installed inside the section rod (302). The adjusting sliding plate (306) is engaged with the threaded rod on the third adjusting motor (305). Adjusting grooves (307) are provided on both sides of the tail wing adjusting rod (302). Adjusting support blocks (304) are slidably installed on both sides of the adjusting sliding plate (306). The adjusting support blocks (304) are slidably engaged with the adjusting grooves (307). A transverse cylindrical key is fixedly installed on the adjusting support block (304). A sliding groove is provided on the tail wing adjusting rod (302). The cylindrical key on the adjusting support block (304) is slidably engaged with the sliding groove on the tail wing adjusting rod (302). An arc-shaped wind deflector (213) is slidably installed inside the bottom of the fuselage shell (201), and a compression spring is fixedly installed between the arc-shaped wind deflector (213) and the fuselage shell (201).

2. A folding-wing drone according to claim 1, characterized in that, A tail wing protection plate (309) is fixedly installed on the outside of the tail wing bracket (301).

3. A folding-wing drone according to claim 1, characterized in that, The bottom inner side of the housing (201) is provided with a sliding groove, and an adjusting ramp is installed in the sliding groove. An adjusting protrusion is fixedly installed at the bottom of the bracket adjusting plate (208), and the protrusion at the bottom of the bracket adjusting plate (208) slides in cooperation with the ramp at the bottom of the housing (201).

4. A folding-wing drone according to claim 1, characterized in that, Protective baffles (202) are fixedly installed on both sides of the outer wall of the fuselage shell (201), and the first bracket (204) of the folding wing is in contact with the protective baffles (202).

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