Cylinder type ejection folding multi-rotor unmanned aerial vehicle

Abstract

The invention discloses a cylindrical ejection folding multi-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. Comprising a machine head, a machine body, a machine arm folding assembly and a folding foot stool, and the machine head comprises a nose cone and an upper-layer bottom plate connected to the lower portion of the nose cone; the fuselage is a shell connected to the lower portion of the upper-layer bottom plate, the arm folding assembly comprises multiple arms and arm mounting assemblies, the tail ends of the arms are rotationally connected with the fuselage in a folded mode through the arm mounting assemblies, and the folding foot stools are rotationally connected with the fuselage in a folded mode through foot stool mounting assemblies. In a non-operation state, the vehicle arms can be folded and put into the launch canister, the space occupancy rate of storage and transportation is reduced, after the unmanned aerial vehicle is launched through the launch canister, the vehicle arms are rapidly and automatically unfolded under the action of the torsional springs and are limited, the attitude of the unmanned aerial vehicle is adjusted, stable flight, rapid response and specific task execution are achieved, and the unmanned aerial vehicle is convenient to use. The method has the advantages that the low-altitude field can be quickly deployed to preempt the low-altitude air control right; and the requirements of ejection launching in a specific environment are met.

Description

Technical Field

[0001] The invention relates to a multi-rotor unmanned aerial vehicle, in particular to a barrel-type ejection folding multi-rotor unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles. Background Art

[0002] Modern warfare is transforming into a comprehensive drone war. Especially in the context of the rapid development of drone technology, more and more drone products are coming into people's view. Among them, drones are developing the fastest due to their advantages of low cost and wide application range. They can be seen from civilian to military fields. In recent years, multi-rotor drones have been widely developed and applied in various fields of society because of their advantages such as environmental protection, low noise, small size, light weight, low cost, easy to carry, suitable for multi-platform and multi-space use, and vertical take-off and landing. However, the fixed-wing drones usually used by conventional multi-rotor drones currently occupy a relatively large space, which is not only inconvenient to store and carry, but also cannot meet the needs of ejection launch in specific environments. Summary of the invention

[0003] The technical problem to be solved by the present invention is to overcome the defects of the prior art and provide a catapult-folding multi-rotor UAV whose wings are easy to store and carry and can be launched by catapult.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is: a barrel-type catapult folding multi-rotor UAV, including a nose, a fuselage, an arm folding assembly 3 and a folding tripod 6, the nose includes: a nose cone 1 and an upper bottom plate 2 connected thereto; the fuselage 5 is a shell connected to the bottom of the upper bottom plate 2, and the fuselage 5 is hollowed out from top to bottom into an upper plate 501, a middle plate 502, and a lower plate 503, the arm folding assembly 3 includes: an arm 4 and an arm mounting assembly, there are multiple arms 4 and the ends of the arms 4 are rotatably connected to the upper plate 501 through the arm mounting assembly, a propeller is installed at the outer end of the arm 4, and corresponding positions on the upper plate 501, the middle plate 502, and the lower plate 503 are all provided with through grooves for accommodating the arms 4, and there are multiple folding tripods 6 and they are rotatably connected to the lower plate 501 through the tripod mounting assembly.

[0005] Specifically, the arm mounting assembly includes an arm torsion spring 303, a left fixing member 301, a right fixing member 302, a bare rod bolt I 305 and a lock nut 306. The arm 4 is hinged with the bare rod bolt I 305. A through hole is arranged at the end of the arm 4. Fixing member through holes are arranged on the left fixing member 301 and the right fixing member 302. Two arm torsion springs 303 are respectively arranged on both sides of the arm 4. The bare rod bolt I 305 passes through the fixing member through hole on the left fixing member 301, the arm torsion spring 303 on one side, the through hole at the end of the arm 4, the arm torsion spring 303 on the other side and the fixing member through hole on the right fixing member 302 in sequence, and is fixed by the lock nut 306. The bottoms of the left fixing member 301 and the right fixing member 302 are respectively fixedly connected to the two ends of the through groove on the upper plate 501, and the tops are fixedly connected to the upper bottom plate 2.

[0006] Preferably, the rear end of the arm 4 is provided with a limiting groove, and the inner sides of the left fixing member 301 and the right fixing member 302 are respectively provided with raised limiting blocks, and limiting holes are cut on the limiting blocks. One end of the arm torsion spring 303 is clamped in the limiting groove at the rear end of the arm 4, and the other end is clamped in the limiting hole of the left fixing member 301 or the right fixing member 302.

[0007] Specifically, the tripod mounting assembly includes a tripod torsion spring 601, a bare rod bolt II 602 and fixed plates fixed on both sides of the inner wall of the tripod mounting groove on the lower plate 503. The folding tripod 6 is hinged with the bare rod bolt II 602. A through hole is arranged at the end of the folding tripod 6, and fixed plate through holes are arranged on the fixed plates on both sides. Two tripod torsion springs 601 are respectively arranged on both sides of the folding tripod 6. The bare rod bolt II 602 passes through the fixed plate through hole on the left fixed plate, the tripod torsion spring 601 on one side, the through hole at the end of the folding tripod 6, the tripod torsion spring 601 on the other side and the fixed plate through hole on the right fixed plate in sequence, and is fixed by a tripod anti-loosening nut.

[0008] Preferably, the head cone 1 is conical, an inner thread is cut on the inner wall of the bottom of the head cone 1, a raised rib is provided on the edge of the upper bottom plate 2, and an outer thread is cut on the outer side of the rib, and the head cone 1 and the upper bottom plate 2 are connected by threads.

[0009] Preferably, a battery compartment 201 for placing a power module is arranged at the center of the upper base plate 2, and the battery compartment 201 is located inside the head cone 1. The upper base plate 2 and the battery compartment 201 are an integrated structure.

[0010] Preferably, guide grooves are provided on both sides of the top of the battery compartment 201, and the removable battery compartment cover 202 is installed in the guide grooves.

[0011] Preferably, the fuselage 5 is an integrated fuselage, which is cylindrical as a whole, and there are four arms 4 and four folding tripods 6, which are evenly and symmetrically distributed along the circumference of the fuselage 5.

[0012] Preferably, a wire hiding groove is arranged at the bottom of the arm 4, and the wire hiding plate 401 covers the wire hiding groove.

[0013] Preferably, a central connecting piece 304 is fixed at the center of the upper end surface of the upper plate 501 , and the upper end of the central connecting piece 304 is fixedly connected to the upper bottom plate 2 .

[0014] The beneficial effects of the present invention are: When not in operation, the arms can be folded into the fuselage, greatly reducing the space occupied by the drone and facilitating normal storage and carrying; the arms of the drone rotors can be automatically unfolded after being ejected from the tube, allowing the drone to be quickly deployed in the air with a fast response, meeting the needs of ejection launch in specific environments;.

[0015] 2. The nose cone is connected to the fuselage with threads; the battery compartment is arranged inside the nose cone, which not only facilitates the disassembly and replacement of batteries of the drone, but also prevents the battery from falling during flight.

[0016] 3. The design of the arm not only meets the needs of folding and launching the drone, but also can store wires to prevent them from being damaged during flight.

[0017] 4. The present invention adopts an integrated fuselage, which avoids the problem of insufficient rigidity caused by too many connecting parts of other drones, and greatly improves the stability of the drone.

[0018] 5. The UAV adopts a cylindrical symmetrical design. Its center of gravity is distributed at the central axis of the UAV and the center of gravity is located below the lift surface. The torque generated by the center of gravity relative to the lift surface is opposite to the torque generated by external interference, which will suppress the interference vibration and make the UAV have better stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 is a general schematic diagram of the UAV of the present invention; Figure 2 It is a schematic diagram of the cooperation between the nose cone and the upper bottom plate; Figure 3 It is a schematic diagram of the upper bottom plate battery compartment structure; Figure 4 This is a schematic diagram of the arm folding assembly structure Figure I ; Figure 5This is a schematic diagram of the arm folding assembly structure Figure II ; Figure 6 It is a schematic diagram of the arm wire-retrieving structure; Figure 7 It is a schematic diagram of the integrated fuselage structure; Figure 8 It is a schematic diagram of the folding structure of the folding tripod.

[0021] The numbers in the figure are: 1-head cone, 2-upper bottom plate, 3-arm folding assembly, 4-arm, 5-fuselage, 6-folding tripod, 201-battery compartment, 202-battery compartment cover, 301-left fixing part, 302-right fixing part, 303-arm torsion spring, 304-center connecting part, 305-light rod bolt I, 306-locking nut, 307-motor, 401-wire hiding plate, 402-wire hiding plate screw, 501-upper plate, 502-middle plate, 503-bottom plate, 601-tripod torsion spring, 602-light rod bolt II. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0023] Embodiment 1: A barrel-type ejection folding multi-rotor UAV comprises a nose, a fuselage, an arm folding assembly 3 and a folding tripod 6, wherein the nose comprises: a nose cone 1 and an upper bottom plate 2 connected thereto; the fuselage 5 is a shell connected to the bottom of the upper bottom plate 2, and the fuselage 5 is hollowed out from top to bottom into an upper plate 501, a middle plate 502, and a lower plate 503, the arm folding assembly 3 comprises: an arm 4 and an arm mounting assembly, wherein the arm 4 is multiple and the ends thereof are rotatably connected to the upper plate 501 through the arm mounting assembly, a propeller is mounted on the outer end of the arm 4, a motor 307 is mounted on the propeller, the motor 307 is connected to a flight controller, and the flight controller is connected to an external remote control, and corresponding positions on the upper plate 501, the middle plate 502, and the lower plate 503 are all provided with through grooves for accommodating the arm 4, so as to facilitate the folding of the arm 4 into the fuselage 5, and the folding tripod 6 is multiple and rotatably connected to the lower plate 501 through the tripod mounting assembly.

[0024] Furthermore, the arm mounting assembly includes an arm torsion spring 303, a left fixing member 301, a right fixing member 302, a bare rod bolt I 305 and a lock nut 306. The arm 4 is hinged with the bare rod bolt I 305. A through hole is arranged at the end of the arm 4. Fixing member through holes are arranged on the left fixing member 301 and the right fixing member 302. Two arm torsion springs 303 are respectively arranged on both sides of the arm 4. The bare rod bolt I 305 passes through the fixing member through hole on the left fixing member 301, the arm torsion spring 303 on one side, the through hole at the end of the arm 4, the arm torsion spring 303 on the other side and the fixing member through hole on the right fixing member 302 in sequence, and is fixed by the lock nut 306. The bottoms of the left fixing member 301 and the right fixing member 302 are respectively fixedly connected to the upper plate 501 of the fuselage 5 by screws, and the tops are also fixedly connected to the upper bottom plate 2 by screws. The left fixing member 301 and the right fixing member 302 not only fix the machine arm 4, but also serve as connecting members between the upper bottom plate 2 and the fuselage 5, thereby increasing the connection strength between the fuselage 4 and the head part.

[0025] Furthermore, the rear end of the arm 4 is provided with a limiting groove, and the inner sides of the left fixing member 301 and the right fixing member 302 are respectively provided with raised limiting blocks, and limiting holes are cut on the limiting blocks. One end of the arm torsion spring 303 is clamped on the limiting groove at the rear end of the arm 4, and the other end is clamped on the limiting hole of the left fixing member 301 or the right fixing member 302. The limiting groove and the limiting hole are used to limit the arm torsion spring 303.

[0026] Furthermore, the tripod mounting assembly includes a tripod torsion spring 601, a bare bolt II 602, and fixing plates fixed on both sides of the inner wall of the tripod mounting groove on the lower plate 503. The folding tripod 6 is hinged with the bare bolt II 602. A through hole is arranged at the end of the folding tripod 6. The fixing plates on both sides are provided with fixing plate through holes. Two tripod torsion springs 601 are arranged on both sides of the folding tripod 6. The bare bolt II 602 passes through the fixing plate through hole on the left fixing plate, the tripod torsion spring 601 on one side, the through hole at the end of the folding tripod 6, the tripod torsion spring 601 on the other side, and the fixing plate through hole on the right fixing plate, and is fixed by the tripod anti-loosening nut. The tripod torsion spring 601 drives the folding tripod 6 to rotate, and the fuselage 5 limits the folding tripod 6.

[0027] Furthermore, the head cone 1 is conical in shape, an internal thread is cut on the inner wall of the bottom of the head cone 1, a raised rib is provided on the edge of the upper base plate 2, and an external thread is cut on the outer side of the rib, and the head cone 1 and the upper base plate 2 are connected by threads for easy disassembly and installation.

[0028] Furthermore, a battery compartment 201 for placing a power module is arranged at the center of the upper base plate 2, and the battery compartment 201 is located inside the head cone 1. The upper base plate 2 and the battery compartment 201 are an integrated structure.

[0029] Furthermore, guide grooves are provided on both sides of the top of the battery compartment 201, and a pull-out battery compartment cover 202 is installed in the guide grooves. The battery compartment 201 can be closed by pushing the battery compartment cover 202 in, so as to prevent the power module from falling when the drone is launched.

[0030] Furthermore, the fuselage 5 is an integrated fuselage, which is cylindrical in shape as a whole, and there are four arms 4 and four folding tripods 6 , which are evenly and symmetrically distributed along the circumference of the fuselage 5 .

[0031] Furthermore, a wire storage groove is arranged at the bottom of the arm 4 for storing wires, and a wire storage plate 401 covers the wire storage groove. At the same time, the wire storage plate 401 is fixed to the wire storage groove of the arm 4 by screws 402 to prevent the wires from being damaged by the propeller after the drone takes off.

[0032] Furthermore, a central connecting piece 304 is fixed at the center of the upper end surface of the upper plate 501 , and the upper end of the central connecting piece 304 is fixedly connected to the upper bottom plate 2 .

[0033] The working principle of the present invention is: when not in operation, the machine arm 4 is manually rotated along the polished rod bolt Ⅰ305 until the machine arm 4 is folded and stored in the through groove on the circumference of the fuselage 5, and the folding tripod 6 is rotated along the polished rod bolt Ⅱ602 until it is folded and stored in the vertical direction below the fuselage 5, and then the folded UAV is stored in the launching tube in advance, which reduces the space occupancy rate of storage and transportation. When arriving at a specific work location, an external remote control is used to unlock the UAV flight controller, and the pneumatic switch of the launching tube is turned on to launch the UAV. After the UAV is out of the tube, the machine arm 4 of the UAV rotates along the polished rod bolt Ⅰ305 under the elastic force of the machine arm torsion spring 303, so as to realize automatic outward expansion and be limited by the fuselage 5. The folding tripod 6 rotates along the polished rod bolt Ⅱ602 under the elastic force of the tripod torsion spring 601, so as to realize automatic outward expansion and be limited by the fuselage 5. When the GPS detects that the UAV reaches a certain height, the flight controller turns on the motor 307, and the UAV starts to fly to complete a specific task. During the flight, the remote control is used to adjust the drone's attitude to achieve stable flight, rapid response, and the execution of specific tasks. The advantage is that it can be quickly deployed in low-altitude areas and seize low-altitude air supremacy; it can meet the needs of catapult launch in specific environments.

[0034] In this embodiment, the fuselage 5 of the ejection folding multi-rotor UAV is of streamlined design, and a nose cone 1 with a rectifying effect is provided at the head of the fuselage. The center of gravity of the entire ejection folding multi-rotor UAV is distributed at the central axis of the UAV and the center of gravity is located below the lift surface. The torque generated by the center of gravity relative to the lift surface is opposite to the torque generated by external interference, which will have a suppressive effect on interfering vibrations, thereby ensuring that the UAV has good stability during flight.

[0035] The present invention provides a method for ejecting a folding multi-rotor drone. There are many methods and ways to implement the technical solution. The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the protection scope of the present invention. All components not specified in this embodiment can be implemented by existing technologies.

Claims

1. A barrel-type ejection folding multi-rotor drone, characterized by: The invention comprises a nose, a fuselage (5), an arm folding assembly (3) and a folding tripod (6), wherein the nose comprises: a nose cone (1) and an upper bottom plate (2) connected thereto; the fuselage (5) is a shell connected to the lower part of the upper bottom plate (2); the fuselage (5) is divided from top to bottom into an upper plate (501), a middle plate (502) and a lower plate (503); the arm folding assembly (3) comprises: an arm (4) and an arm mounting assembly; the arm (4) is plural and the ends of the arms are rotatably connected to the upper plate (501) through the arm mounting assembly; a propeller is mounted on the outer end of the arm (4); corresponding positions on the upper plate (501), the middle plate (502) and the lower plate (503) are all provided with through slots for receiving the arms (4); the folding tripod (6) is plural and rotatably connected to the lower plate (501) through the tripod mounting assembly.

2. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: The arm mounting assembly includes an arm torsion spring (303), a left fixing member (301), a right fixing member (302), a polished rod bolt I (305) and a locking nut (306). The arm (4) is hinged to the polished rod bolt I (305). A through hole is arranged at the end of the arm (4). The left fixing member (301) and the right fixing member (302) are both provided with fixing member through holes. Two arm torsion springs (303) are respectively arranged on both sides of the arm (4). The polished rod bolt I (305) passes through the fixing hole on the left fixing member (301), the torsion spring (303) on one side of the machine arm, the through hole at the end of the machine arm (4), the torsion spring (303) on the other side of the machine arm and the fixing hole on the right fixing member (302) in sequence and is fixed by a locking nut (306). The bottoms of the left fixing member (301) and the right fixing member (302) are respectively fixedly connected to the two ends of the through groove on the upper plate (501), and the tops are fixedly connected to the upper bottom plate (2).

3. The barrel-type ejection folding multi-rotor UAV according to claim 2, characterized in that: The tail end of the machine arm (4) is provided with a limiting groove, and the inner sides of the left fixing member (301) and the right fixing member (302) are respectively provided with raised limiting blocks, and limiting holes are cut into the limiting blocks. One end of the machine arm torsion spring (303) is clamped in the limiting groove at the tail end of the machine arm (4), and the other end is clamped in the limiting holes of the left fixing member (301) and the right fixing member (302).

4. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: The tripod mounting assembly includes a tripod torsion spring (601), a polished rod bolt II (602) and fixed plates fixed on both sides of the inner wall of the tripod mounting groove on the lower plate (503). The folding tripod (6) is hinged with the polished rod bolt II (602). A through hole is arranged at the end of the folding tripod (6). Fixed plate through holes are arranged on the fixed plates on both sides. Two tripod torsion springs (601) are arranged on both sides of the folding tripod (6). The polished rod bolt II (602) passes through the fixed plate through hole on the left fixed plate, the tripod torsion spring (601) on one side, the through hole at the end of the folding tripod (6), the tripod torsion spring (601) on the other side and the fixed plate through hole on the right fixed plate, and is then fixed by a tripod anti-loosening nut.

5. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: The head cone (1) is conical in shape, an inner thread is cut on the inner wall of the bottom of the head cone (1), a raised rib is provided on the edge of the upper bottom plate (2), and an outer thread is cut on the outer side of the rib, and the head cone (1) and the upper bottom plate (2) are connected by threads.

6. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: A battery compartment (201) for accommodating a power module is arranged at the center of the upper base plate (2). The battery compartment (201) is located inside the nose cone (1). The upper base plate (2) and the battery compartment (201) are an integrated structure.

7. The barrel-type ejection folding multi-rotor UAV according to claim 6, characterized in that: Guide grooves are provided on both sides of the top of the battery compartment (201), and a retractable battery compartment cover (202) is installed in the guide grooves.

8. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: The fuselage (5) is an integrated fuselage, and the whole is in the shape of a hollow cylinder. There are four arms (4) and four folding tripods (6), which are evenly distributed along the circumference of the fuselage (5).

9. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: A wire storage groove is arranged at the bottom of the machine arm (4), and a wire storage plate (401) covers the wire storage groove.

10. The barrel-type ejection folding multi-rotor UAV according to claim 1, characterized in that: A central connecting piece (304) is fixed at the center of the upper end surface of the upper plate (501), and the upper end of the central connecting piece (304) is fixedly connected to the upper bottom plate (2).

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