Automatic folding arm multi-rotor unmanned aerial vehicle capable of putting small unmanned aerial vehicles

Abstract

The invention discloses an automatic folding arm multi-rotor unmanned aerial vehicle capable of putting a small unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, in particular to the automatic folding arm multi-rotor unmanned aerial vehicle capable of putting the small unmanned aerial vehicle, which comprises a fuselage assembly, four arm assemblies and at least two undercarriage assemblies, automatic folding and unfolding of the unmanned aerial vehicle arms are achieved through the electric folding vehicle arm assemblies; the gear motor drives the lead screw to rotate, the lead screw drives the sliding nut to move in the length direction, the sliding nut pushes the crank connecting rod to locally rotate around the shaft rod, and therefore folding and unfolding of the machine arm are achieved. Meanwhile, the unmanned aerial vehicle occupies a smaller space in the storage and transportation processes due to the automatic vehicle arm folding function, the unmanned aerial vehicle can be stored in an automatic airport conveniently, and the problems that in the prior art, manual vehicle arm folding is inconvenient to operate, and the size of the automatic airport is too large are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of drones, and specifically to an automatic folding arm multi-rotor drone capable of deploying small drones. Background Art

[0002] With the continuous development of drone technology, its applications in fields such as detection, aerial photography, mapping, power line inspection, and plant protection are becoming increasingly widespread. As a special unmanned helicopter with three or more rotor shafts, a multi-rotor drone generates lift thrust by the rotation of motors on each shaft, and has received extensive attention due to its flexibility and high efficiency. However, there are still some problems to be solved urgently in the practical application of existing multi-rotor drones.

[0003] The existing patented technology (CN109018297B) discloses an automatic retractable drone arm folding member, which realizes the automatic retraction and extension of the drone arm by driving a lead screw to rotate with a motor, expanding the flight area of the drone. However, this technology is limited to the automatic retraction and extension function of the arm and does not involve other function expansions of the drone, such as the functions of mounting and deploying small drones. In practical applications, the automation level and function expandability of drones are crucial for improving operation efficiency and adapting to complex environments.

[0004] Currently, the common storage methods of multi-rotor drones are mostly manual folding of the arms or disassembly of the arms. This manual operation method is not only time-consuming and laborious, but also not conducive to the realization of drone automation. In addition, with the introduction and wide promotion of automatic drone airports, higher requirements are put forward for the automation level of drones. However, the existing automatic airports have the problem of overly large airport sizes due to catering to the large wheelbases of drones, which to a certain extent limits the storage and transportation efficiency of drones. At the same time, when drones perform specific tasks, they often need to carry additional equipment or small drones, but the existing methods of mounting and deploying small drones on drones are relatively complex and have a low automation level, unable to meet the requirements of efficient operation.

[0005] Therefore, the present invention aims to provide an automatic folding arm multi-rotor drone capable of deploying small drones, which improves the automation level and function expandability of the drone through the functions of automatic folding of the arms and mounting and deploying small drones, and solves the problems of inconvenient manual folding of the arms, overly large sizes of automatic airports, and complex methods of deploying small drones existing in the prior art. Summary of the Invention

[0006] (I) Technical Problems to be Solved In view of the deficiencies of the prior art, the present invention provides an automatic folding arm multi-rotor drone capable of deploying small drones, which solves the problems raised in the above background art.

[0007] (2) Technical solution To achieve the above objectives, the present invention is implemented through the following technical solutions: an automatic folding arm multi-rotor drone capable of launching a small drone, comprising a fuselage assembly, four arm assemblies, and at least two landing gear assemblies, each of which is equipped with a small drone assembly; the fuselage assembly comprises a fuselage; the four arm assemblies are respectively mounted on the four corner rods of the fuselage, and each of the landing gear assemblies is mounted below the fuselage; the small drone assembly is slidably mounted on the landing gear assembly; the small drone assembly is detached from the landing gear assembly by sliding. The assembly is then deployed; the arm assembly includes an electric folding hinge housing, a reduction motor, a crank connecting rod, and a shaft rod; one end of the electric folding hinge housing is detachably mounted on a rod body at a corner of the fuselage; the reduction motor is mounted inside the electric folding hinge housing; one end of the crank connecting rod is inserted into the electric folding hinge housing; the shaft rod longitudinally penetrates the end of the crank connecting rod, and the upper and lower ends of the shaft rod are rotatably connected to the electric folding hinge housing; the reduction motor is transmission-connected to the crank connecting rod; the reduction motor drives the crank connecting rod to rotate locally around the shaft rod.

[0008] Optionally, the landing gear assembly includes a landing gear frame, a mounting bracket, and a delivery rail. The upper end of the landing gear frame is fixedly mounted on the lower surface of the fuselage, the mounting bracket is fixedly mounted on the landing gear frame, and the delivery rail is fixedly mounted on a side wall of the mounting bracket, and the delivery rail is inclined. The small UAV assembly includes a slider, a second slot is provided on the slider, and the slider is slidably mounted on the delivery rail.

[0009] Optionally, the landing gear assembly further includes a servo and a clamping strip, wherein the servo is fixedly mounted on a side wall of the mounting bracket away from the launching guide rail, the mounting bracket is provided with a first clamping slot, and the clamping strip is fixedly mounted on the output shaft end of the servo; the servo drives the clamping strip to rotate partially, and the clamping strip is clamped in the first clamping slot and the second clamping slot after partial rotation.

[0010] Optionally, the landing gear frame is U-shaped as a whole, the upper end of the mounting bracket is fixedly installed on the lower surface of the fuselage, and the lower end of the mounting bracket is fixedly installed on the lower part of the landing gear frame; charging contacts are installed on the landing gear frame.

[0011] Optionally, the small drone assembly further includes a small drone, and the lower surface of the casing of the small drone is fixedly mounted to the slider.

[0012] Optionally, the arm assembly further includes a lead screw, a sliding nut, and a bearing. The bearing is fixedly installed inside the electric folding hinge housing. One end of the lead screw is coaxially and fixedly connected to the output shaft end of the reduction motor. The other end of the lead screw is inserted into the central hole of the bearing, and the lead screw is rotatably connected to the electric folding hinge housing through the bearing. The sliding nut is sleeved on the outer sidewall of the lead screw and is threadedly connected thereto. A sliding groove is formed at one end of the crank connecting rod close to the reduction motor. The end of the sliding nut is inserted into the sliding groove of the crank connecting rod, and the sliding nut is slidably connected to the crank connecting rod through the sliding groove. When the sliding nut moves along the length direction of the lead screw, the sliding nut pushes the crank connecting rod to rotate partially around the shaft rod.

[0013] Optionally, the electric folding hinge housing includes an upper electric folding hinge shell and a lower electric folding hinge shell. The upper electric folding hinge shell and the lower electric folding hinge shell are fixedly installed through a plurality of bolts. The upper and lower ends of the shaft rod are respectively rotatably connected to the upper electric folding hinge shell and the lower electric folding hinge shell.

[0014] Optionally, the arm assembly further includes a propeller, a rotor motor, and a motor mount. The motor mount is fixedly installed at the end of the crank connecting rod far from the electric folding hinge housing. The rotor motor is fixedly installed on the motor mount. The propeller is fixedly installed at the output shaft end of the rotor motor.

[0015] Optionally, the fuselage assembly further includes a positioning antenna and an optoelectronic pod. The positioning antenna is fixedly installed on the fuselage. The optoelectronic pod is suspended and installed below the fuselage.

[0016] Optionally, a support rod is fixedly installed on the landing gear assembly. A downward-looking camera and a ground radar are respectively fixedly installed on the support rod.

[0017] (III) Beneficial effects The present invention provides an automatically foldable arm multi-rotor unmanned aerial vehicle with a deployable small unmanned aerial vehicle, having the following beneficial effects: 1. The present invention realizes the automatic folding and unfolding of the unmanned aerial vehicle arm through the electric folding arm assembly. The reduction motor drives the lead screw to rotate. The lead screw drives the sliding nut to move along its length direction. The sliding nut pushes the crank connecting rod to rotate partially around the shaft rod, thereby realizing the folding and unfolding of the arm. This process does not require manual intervention, greatly improving the automation degree of the unmanned aerial vehicle, reducing the workload of the operator, and improving the operation efficiency. At the same time, the function of the automatically foldable arm makes the unmanned aerial vehicle occupy less space during storage and transportation, which is beneficial to storing the unmanned aerial vehicle in the automatic airport, and solves the problems of inconvenient operation of manually folding the arm and the over-large size of the automatic airport in the prior art.

[0018] 2. The landing gear assembly of the present invention is cleverly designed and can be used to mount and launch small drones. An inclined launch rail is installed on the landing gear frame, and the small drone assembly is slidably mounted on the launch rail via a slider. The servo drives the card bar to rotate partially to achieve the mounting and launch of the small drone. This design enables the drone to carry small drones with different functions to perform various tasks, such as reconnaissance, observation, and mapping. The small drone is launched from a high altitude, which reduces the power consumption of taking off from a low altitude, retains more power for the small drone, and improves the endurance and operating efficiency of the small drone. It solves the problem of complex small drone launch methods in the existing technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0020] Figure 1 This is a schematic diagram of the three-dimensional structure of the machine arm of the present invention in the unfolded state; Figure 2 This is a schematic diagram of the three-dimensional structure of the machine arm of the present invention in a folded state; Figure 3 This is a schematic diagram of the right side structure of the present invention when the machine arm is in an unfolded state; Figure 4 This is a schematic diagram of the structure of the machine arm of the present invention in a folded state from the right side; Figure 5 This is a front view structural diagram of the present invention with the arms in an unfolded state; Figure 6 This is a front view schematic diagram of the structure of the machine arm in a folded state of the present invention; Figure 7 An exploded view of each component of the present invention; Figure 8 It is a front view structural diagram of the fuselage in the present invention; Figure 9 Schematic diagram of the three-dimensional structure of the electric folding arm assembly of the present invention; Figure 10 This is a schematic diagram of the three-dimensional structure of the electric folding arm assembly of the present invention in a disassembled state; Figure 11 Schematic diagram of the three-dimensional structure (top-down perspective) of the landing gear assembly of the present invention; Figure 12 Schematic diagram of the three-dimensional structure (looking from above) of the landing gear assembly of the present invention; Figure 13Schematic three-dimensional structure diagram of the small and medium-sized unmanned aerial vehicle components of the present invention; Figure 14 Schematic three-dimensional structure diagram of the delivery guide rail of the present invention; Figure 15 Schematic three-dimensional structure diagram of the mounting bracket of the present invention; Figure 16 is Figure 15 Schematic enlarged structure diagram at position A in Figure 17 Schematic three-dimensional structure diagram of the reduction motor of the present invention.

[0021] In the figure: 100, fuselage assembly; 101, fuselage; 102, positioning antenna; 103, optoelectronic pod; 200, arm assembly; 201, propeller; 202, rotor motor; 203, motor base; 204, crank connecting rod; 205, upper shell of electric folding hinge; 206, lower shell of electric folding hinge; 207, reduction motor; 208, lead screw; 209, bearing; 210, sliding nut; 211, shaft rod; 300, landing gear assembly; 301, landing gear frame; 302, mounting bracket; 303, delivery guide rail; 304, charging contact; 305, servo; 306, downward-looking camera; 307, ground radar; 308, clamping strip; 309, first card slot; 400, small unmanned aerial vehicle component; 401, small unmanned aerial vehicle; 402, slider; 403, second card slot. Detailed implementation manners

[0022] Next, the technical solutions of the present invention will be clearly and completely described in conjunction with the accompanying drawings. In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be understood as indicating or implying.

[0023] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "connected", "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments.

[0024] Please refer to Figures 1 to 17 Figures 1 to 17 The present invention provides a technical solution: an automatically foldable arm multi-rotor drone capable of deploying small drones, including a fuselage assembly 100, four arm assemblies 200, and at least two landing gear assemblies 300. A small drone assembly 400 is installed on each landing gear assembly 300.

[0025] The fuselage assembly 100 includes a fuselage 101. The four arm assemblies 200 are respectively installed on the four corner rods of the fuselage 101, and each landing gear assembly 300 is installed below the fuselage 101. The small drone assembly 400 is slidably installed on the landing gear assembly 300. After the small drone assembly 400 slides away from the landing gear assembly 300, it is deployed.

[0026] The fuselage assembly 100 further includes a positioning antenna 102, an optoelectronic pod 103, a battery, an integrated avionics controller, etc. The positioning antenna 102 is fixedly installed on the fuselage 101, and the optoelectronic pod 103 is suspended and installed below the fuselage 101. A support rod is fixedly installed on the landing gear assembly 300. Specifically, the support rod is fixedly installed on the landing gear frame 301, and a downward-looking camera 306 and a ground radar 307 are respectively fixedly installed on the support rod.

[0027] Among them, the fuselage 101 serves as the support structure of the entire drone, carrying other components. The positioning antenna 102 is installed at the front and rear ends of the fuselage 101, used to receive satellite signals, provide accurate position and heading information for the drone, and ensure the navigation accuracy of the drone during flight. The optoelectronic pod 103 is installed below the fuselage 101, mainly used for tasks such as reconnaissance and observation, can obtain image information of ground targets in real time, and provide data support for operations. The battery and the integrated avionics controller are installed inside the fuselage 101. The integrated avionics controller is the "brain" of the drone, responsible for processing various sensor signals, controlling parameters such as the flight attitude and speed of the drone, and realizing the autonomous flight function of the drone. The positioning antenna 102, the optoelectronic pod 103, the downward-looking camera 306, the ground radar 307, etc. all adopt common spare parts or electrical components in the drone market, which belong to the prior art, and their functions, structures, connection methods, etc. will not be elaborated here.

[0028] The arm assembly 200 includes an electric folding hinge housing, a reduction motor 207, a crank connecting rod 204, and a shaft rod 211. One end of the electric folding hinge housing is detachably installed on a corner rod of the fuselage 101, and this detachable design facilitates the installation and maintenance of the arm assembly 200. The reduction motor 207 is installed inside the electric folding hinge housing to provide power for the folding and unfolding of the arm. One end of the crank connecting rod 204 is inserted into the electric folding hinge housing, the shaft rod 211 longitudinally penetrates this end of the crank connecting rod 204, and the upper and lower ends of the shaft rod 211 are rotatably connected to the electric folding hinge housing. The reduction motor 207 is drivingly connected to the crank connecting rod 204. The reduction motor 207 drives the crank connecting rod 204 to partially rotate around the shaft rod 211.

[0029] Among them, the electric folding hinge housing is mainly used to provide stable housing support. When the reduction motor 207 operates, the reduction motor 207 pushes the crank connecting rod 204 to partially rotate around the shaft rod 211, thereby realizing the folding (refer to Figure 2 ) and unfolding (refer to Figure 1 ) of the arm.

[0030] The landing gear assembly 300 includes a landing gear frame 301, a mounting bracket 302, and a launch guide rail 303. The upper end of the landing gear frame 301 is fixedly installed on the lower surface of the fuselage 101. The mounting bracket 302 is fixedly installed on the landing gear frame 301 and is used to install the launch guide rail 303 and the small unmanned aircraft assembly 400. The launch guide rail 303 is fixedly installed on one side wall of the mounting bracket 302, and the launch guide rail 303 is inclined to facilitate the sliding launch of the small unmanned aircraft 401. The small unmanned aircraft assembly 400 includes a slider 402, and a second card slot 403 is provided on the slider 402. The slider 402 is slidably installed on the launch guide rail 303. The small unmanned aircraft assembly 400 further includes a small unmanned aircraft 401, and the lower surface of the housing of the small unmanned aircraft 401 is fixedly installed on the slider 402. The landing gear assembly 300 further includes a servo motor 305 and a card strip 308. The servo motor 305 is fixedly installed on the side wall of the mounting bracket 302 away from the launch guide rail 303. A first card slot 309 is provided on the mounting bracket 302. The card strip 308 is fixedly installed at the output shaft end of the servo motor 305. The servo motor 305 drives the card strip 308 to partially rotate, and after the partial rotation, the card strip 308 is clamped in the first card slot 309 and the second card slot 403.

[0031] Among them, the landing gear assembly 300 is the support structure of the UAV, which is used to support the UAV for ground parking and realize the takeoff and landing of the UAV. When the small UAV assembly 400 is mounted on the release guide rail 303, the servo 305 drives the partial rotation of the latch 308, and the latch 308 is clamped in the first slot 309 and the second slot 403 to fix the small UAV assembly 400 on the release guide rail 303. When it is necessary to release the small UAV 401, the servo 305 drives the partial rotation of the latch 308 again to disengage the latch 308 from the first slot 309 and the second slot 403, and the small UAV assembly 400 slides down along the release guide rail 303 under the action of gravity to realize the release. In actual implementation, the servo 305 can also be replaced by a small servo motor. The servo 305 is mainly used to drive the latch 308 to rotate a certain angle so that the latch 308 can be clamped in the first slot 309 and the second slot 403. The integrated avionics controller is electrically connected to the servo 305 (including communication connection), and the integrated avionics controller is used to control the start-stop and operation of the servo 305. The small UAV assembly 400 is an important part of the present invention and is used to perform various specific tasks. The small UAV 401 can carry different sensors or devices, such as cameras, surveying instruments, etc. according to different task requirements, so as to realize diversified operation functions. When the small UAV 401 is mounted on the release guide rail 303, the servo 305 drives the latch 308 to cooperate with the second slot 403 on the slider 402 to fix the small UAV 401 on the release guide rail 303. When it is necessary to release the small UAV 401, the servo 305 drives the latch 308 to disengage from the second slot 403, and the small UAV 401 slides down along the release guide rail 303 under the action of gravity to realize the release. This release method is simple, efficient, and highly automated, greatly improving the operation efficiency of the small UAV 401.

[0032] Specifically, the landing gear frame 301 is integrally U-shaped. The upper end of the mounting bracket 302 is fixedly installed on the lower surface of the fuselage 101 and is used to support the weight of the entire UAV. The lower end of the mounting bracket 302 is fixedly installed on the lower part of the landing gear frame 301. A charging contact 304 is installed on the landing gear frame 301 for realizing the automatic charging function of the UAV.

[0033] Among them, when the UAV lands on the automatic airport (referring to the UAV airport equipment used to hold the UAV or for the UAV to land), the charging contact 304 (i.e., the charging terminal) contacts the charging device of the automatic airport to charge the battery of the UAV, improving the convenience of using the UAV. The electrical connection between the charging contact 304 and the battery on the UAV belongs to the prior art and will not be elaborated here in detail.

[0034] Specifically, the arm assembly 200 further includes a lead screw 208, a sliding nut 210, and a bearing 209. The bearing 209 is fixedly installed inside the electric folding hinge housing. One end of the lead screw 208 is coaxially and fixedly connected to the output shaft end of the reduction motor 207. The other end of the lead screw 208 is inserted into the central hole of the bearing 209, and the lead screw 208 is rotationally connected to the electric folding hinge housing through the bearing 209. The sliding nut 210 is sleeved on the outer sidewall of the lead screw 208 and the two are threadedly connected. One end of the crank connecting rod 204 close to the reduction motor 207 is provided with a sliding groove. The end of the sliding nut 210 is inserted into the sliding groove of the crank connecting rod 204, and the sliding nut 210 is slidably connected to the crank connecting rod 204 through the sliding groove. When the sliding nut 210 moves along the length direction of the lead screw 208, the sliding nut 210 pushes the crank connecting rod 204 to partially rotate around the shaft rod 211.

[0035] Among them, the reduction motor 207 is used to drive the rotation of the lead screw 208. The lead screw 208 is used to drive the sliding nut 210 to slide along its length direction. During the displacement process, the sliding nut 210 pushes one end of the crank connecting rod 204 close to the reduction motor 207, causing the crank connecting rod 204 to partially rotate around the shaft rod 211, so that the entire arm folds or unfolds relative to the fuselage 101. When the reduction motor 207 works, it drives the rotation of the lead screw 208. The sliding nut 210 on the lead screw 208 moves along its length direction, pushing the crank connecting rod 204 to partially rotate around the shaft rod 211, thereby realizing the folding (refer to Figure 2 ) and unfolding (refer to Figure 1 ) of the arm.

[0036] Specifically, the electric folding hinge housing includes an upper electric folding hinge shell 205 and a lower electric folding hinge shell 206. The upper electric folding hinge shell 205 and the lower electric folding hinge shell 206 are fixedly installed through a plurality of bolts. The upper and lower ends of the shaft rod 211 are respectively rotationally connected to the upper electric folding hinge shell 205 and the lower electric folding hinge shell 206.

[0037] Among them, the upper electric folding hinge shell 205 and the lower electric folding hinge shell 206 together form the electric folding hinge housing. The upper electric folding hinge shell 205 and the lower electric folding hinge shell 206 are fixedly installed together through a plurality of bolts after being buckled.

[0038] More specifically, the arm assembly 200 further includes a propeller 201, a rotor motor 202, and a motor mount 203. The motor mount 203 is fixedly installed on the end head of the crank connecting rod 204 away from the electric folding hinge housing. The rotor motor 202 is fixedly installed on the motor mount 203. The propeller 201 is fixedly installed on the output shaft end of the rotor motor 202.

[0039] Among them, the integrated avionics controller controls the rotation speed of the rotor motor 202 through a control signal, thereby realizing the rotation speed control of the propeller 201 by the rotor motor 202, and thus adjusting the lift of the drone. The rotor motor 202 is used to drive the propeller 201 to rotate. The motor base 203 is used to support and fix the rotor motor 202. During the folding or unfolding process, one end of the crank connecting rod 204 away from the electric folding hinge housing drives the motor base 203 to move, so that the entire arm folds or unfolds relative to the fuselage 101.

[0040] During use, the folding and unfolding of the arm: When the arm needs to be folded, the reduction motor 207 works, and the output shaft of the reduction motor 207 drives the lead screw 208 to rotate. The sliding nut 210 on the lead screw 208 moves along its length direction, pushing the crank connecting rod 204 to rotate locally around the shaft rod 211, causing the arm to fold. When the arm needs to be unfolded, the reduction motor 207 works in the reverse direction, driving the lead screw 208 to rotate in the reverse direction, and the sliding nut 210 moves in the reverse direction along the lead screw 208, pushing the crank connecting rod 204 to rotate in the reverse direction around the shaft rod 211, causing the arm to unfold. This process does not require manual intervention, greatly improving the automation level of the drone, reducing the workload of the operator, and improving the operation efficiency.

[0041] Mounting and dropping of the small drone 401: When the small drone 401 needs to be mounted, the slider 402 of the small drone 401 is installed on the dropping guide rail 303, and the servo 305 drives the latch 308 to rotate locally, so that the latch 308 is clamped in the first card slot 309 and the second card slot 403, fixing the small drone 401 on the dropping guide rail 303. When the small drone 401 needs to be dropped, the servo 305 drives the latch 308 to rotate locally again, so that the latch 308 disengages from the first card slot 309 and the second card slot 403, and the small drone 401 slides down along the dropping guide rail 303 under the action of gravity, realizing the dropping. This dropping method is simple, efficient, and highly automated, greatly improving the operation efficiency of the small drone 401.

[0042] Automatic charging function: Charging contacts 304 are installed on the landing gear frame 301. When the drone lands at the automatic airport, the charging contacts 304 contact the charging equipment of the automatic airport to charge the battery of the drone, improving the convenience of use of the drone.

[0043] Precise landing function: A downward-looking camera 306 and a ground radar 307 are installed at the bottom of the landing gear assembly 300. The downward-looking camera 306 can cooperate with an image recognition program to achieve precise landing, and the ground radar 307 can measure the accurate distance between the drone and the ground or the landing platform of the automatic airport, providing reference data for the downward-looking camera 306, further enhancing the automation level of the drone and its ability to adapt to complex environments.

[0044] In summary, through the mounting and dropping function of the arm assembly 200 and the small unmanned aerial vehicle 401, the present invention improves the automation level and functional expandability of the unmanned aerial vehicle, solves the problems in the prior art such as inconvenient manual folding of the arm, over-large size of the automatic airport, and complex dropping method of the small unmanned aerial vehicle 401, and has broad application prospects.

[0045] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered within the protection scope of the present invention.

Claims

1. An automatic folding arm multi-rotor drone capable of deploying small drones, comprising a fuselage assembly (100), characterized in that: It also includes four arm assemblies (200) and at least two landing gear assemblies (300), each of the landing gear assemblies (300) being equipped with a small drone assembly (400); The fuselage assembly (100) includes a fuselage (101); four arm assemblies (200) are respectively mounted on four corner rods of the fuselage (101); each landing gear assembly (300) is mounted below the fuselage (101); the small drone assembly (400) is slidably mounted on the landing gear assembly (300); and the small drone assembly (400) is deployed after sliding away from the landing gear assembly (300); The arm assembly (200) includes an electric folding hinge housing, a reduction motor (207), a crank connecting rod (204), and an axle (211). One end of the electric folding hinge housing is detachably mounted on a rod body at a corner of the fuselage (101). The reduction motor (207) is mounted inside the electric folding hinge housing. One end of the crank connecting rod (204) is inserted into the electric folding hinge housing. The axle (211) longitudinally penetrates the end of the crank connecting rod (204), and the upper and lower ends of the axle (211) are rotatably connected to the electric folding hinge housing. The reduction motor (207) is transmission-connected to the crank connecting rod (204). The reduction motor (207) drives the crank connecting rod (204) to rotate locally around the axle (211).

2. The automatically foldable arm multi-rotor drone capable of deploying small drones according to claim 1, wherein: The landing gear assembly (300) includes a landing gear frame (301), a mounting bracket (302), and a delivery guide rail (303); the upper end of the landing gear frame (301) is fixedly mounted on the lower surface of the fuselage (101); the mounting bracket (302) is fixedly mounted on the landing gear frame (301); the delivery guide rail (303) is fixedly mounted on a side wall of the mounting bracket (302), and the delivery guide rail (303) is arranged in an inclined manner; the small UAV assembly (400) includes a slider (402); a second slot (403) is provided on the slider (402); and the slider (402) is slidably mounted on the delivery guide rail (303).

3. The automatically foldable arm multi-rotor drone capable of launching small drones according to claim 2, wherein: The landing gear assembly (300) further comprises a steering gear (305) and a clamping strip (308); the steering gear (305) is fixedly mounted on a side wall of the mounting bracket (302) away from the delivery guide rail (303); a first clamping slot (309) is provided on the mounting bracket (302); and the clamping strip (308) is fixedly mounted on the output shaft end of the steering gear (305); the steering gear (305) drives the clamping strip (308) to partially rotate, and the clamping strip (308) is clamped in the first clamping slot (309) and the second clamping slot (403) after the partial rotation.

4. The automatic folding arm multi-rotor unmanned aerial vehicle capable of deploying small unmanned aerial vehicles according to claim 3, wherein: The landing gear frame (301) is U-shaped as a whole, the upper end of the mounting bracket (302) is fixedly mounted to the lower surface of the fuselage (101), and the lower end of the mounting bracket (302) is fixedly mounted to the lower part of the landing gear frame (301); and a charging contact (304) is installed on the landing gear frame (301).

5. The automatic folding arm multi-rotor drone capable of launching small drones according to claim 2, wherein: The small UAV component (400) further includes a small UAV (401), and the lower surface of the housing of the small UAV (401) is fixedly installed with a slider (402).

6. The automatic folding arm multi-rotor drone capable of deploying small drones according to claim 1, wherein: The arm assembly (200) further includes a lead screw (208), a sliding nut (210), and a bearing (209). The bearing (209) is fixedly installed in the electric folding hinge housing. One end of the lead screw (208) is coaxially and fixedly connected to the output shaft end of the reduction motor (207). The other end of the lead screw (208) is inserted into the middle hole of the bearing (209), and the lead screw (208) is rotationally connected to the electric folding hinge housing through the bearing (209). The sliding nut (210) is sleeved on the outer side wall of the lead screw (208) and is threadedly connected thereto. A sliding groove is provided at one end of the crank connecting rod (204) close to the reduction motor (207). The end of the sliding nut (210) is inserted into the sliding groove of the crank connecting rod (204), and the sliding nut (210) is slidably connected to the crank connecting rod (204) through the sliding groove. When the sliding nut (210) moves along the length direction of the lead screw (208), the sliding nut (210) pushes the crank connecting rod (204) to rotate locally around the shaft rod (211).

7. The automatic folding arm multi-rotor drone capable of deploying small drones according to claim 1, characterized in that: The electric folding hinge housing includes an upper electric folding hinge shell (205) and a lower electric folding hinge shell (206). The upper electric folding hinge shell (205) and the lower electric folding hinge shell (206) are fixedly installed through a plurality of bolts. The upper and lower ends of the shaft rod (211) are respectively rotationally connected to the upper electric folding hinge shell (205) and the lower electric folding hinge shell (206).

8. The automatic folding arm multi-rotor drone capable of deploying small drones according to claim 7, wherein: The arm assembly (200) further includes a propeller (201), a rotor motor (202), and a motor mount (203). The motor mount (203) is fixedly installed at the end of the crank connecting rod (204) away from the electric folding hinge housing. The rotor motor (202) is fixedly installed on the motor mount (203). The propeller (201) is fixedly installed at the output shaft end of the rotor motor (202).

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