Coaxial multi-rotor folding arm heavy-load transportation unmanned aerial vehicle

Abstract

The utility model is applicable to the technical field of unmanned aerial vehicles, and provides a coaxial multi-rotor folding arm heavy-load transportation unmanned aerial vehicle which comprises an unmanned aerial vehicle body, and the unmanned aerial vehicle body is composed of a carbon fiber frame fuselage, a multifunctional undercarriage, a set of double-tube carbon fiber arms, a coaxial double-paddle power assembly and a double-tube integrated metal folding piece. The multifunctional undercarriage is installed at the bottom of the carbon fiber frame fuselage, the double-tube carbon fiber vehicle arms are arranged on one side of the carbon fiber frame fuselage, and the double-tube integrated metal folding piece is assembled on the double-tube carbon fiber vehicle arms. According to the coaxial multi-rotor folding arm heavy-load transportation unmanned aerial vehicle provided by the scheme, through a double-tube integrated arm folding structure, the strength is high, contact is free of clearance, swing is effectively restrained, storage is rapid, the size is reduced, and meanwhile the problems that other types of equipment are small in lift force, small in load, low in strength and large in vibration can be solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a coaxial multi-rotor folding-arm large-load transport UAV. Background Art

[0002] With the development of economic construction, infrastructure projects, agriculture, forestry, animal husbandry and fishery industries in various places, the transportation of materials has always been difficult in mountainous areas, hills, deserts, forests, scenic areas and other areas with inconvenient transportation. The material transportation work is time-consuming and labor-intensive. With the development of the UAV industry and the liberalization of the low-altitude economy, transport UAVs have been widely used in various industries, playing a great role in improving labor efficiency, reducing labor costs and ensuring material safety.

[0003] At present, the traditional boom is a single-axis, single-tube, single-motor boom that cannot be folded, is bulky, and inconvenient to transport and transfer. Moreover, the single axis can only exert the lifting force provided by one motor, and the boom can only withstand the vertical pull of a single motor. The improved boom is a foldable boom, but still uses a single-tube, single-motor. Although it solves the problem of folding and storage, the folding parts have a large clearance and large vibration, which can easily cause the boom to explode due to vibration. The single-tube boom and single-motor power still cannot meet the needs of large loads. Utility Model Content

[0004] The utility model provides a coaxial multi-rotor folding-arm large-load transport drone, which aims to solve the problem of the current traditional arm structure proposed in the above background technology, that the arm cannot be folded, occupies too much space, increases transportation costs, and the foldable arm vibrates greatly, which can easily cause the drone to explode due to vibration.

[0005] To solve the above problems, the utility model is implemented as follows: a coaxial multi-rotor folding arm large-load transport drone, comprising: a drone body, the drone body is composed of a carbon fiber frame fuselage, a multi-functional landing gear, a group of double-tube carbon fiber arms, a coaxial double-propeller powertrain and a double-tube integrated metal folding part, the multi-functional landing gear is installed at the bottom of the carbon fiber frame fuselage, a group of double-tube carbon fiber arms are arranged on one side of the carbon fiber frame fuselage, the double-tube integrated metal folding part is assembled on a group of double-tube carbon fiber arms, and the coaxial double-propeller powertrain is installed at one end of the double-tube carbon fiber arm away from the carbon fiber frame fuselage.

[0006] Preferably, a threaded hole is provided on the multifunctional landing gear, a stainless steel bolt is threadedly installed on the multifunctional landing gear, the stainless steel bolt is threadedly connected to the bottom of the carbon fiber frame fuselage, and a locking bolt and a through bolt are threadedly installed on the double-tube integrated metal folding part, and the locking bolt and the through bolt are both used to connect a set of double-tube carbon fiber arms.

[0007] Preferably, the multifunctional landing gear consists of a landing gear, a gimbal camera, a group of obstacle avoidance radars and a rubber shock-absorbing sleeve. The gimbal camera is installed on the top of the landing gear, a group of obstacle avoidance radars are installed on both sides of the landing gear, the gimbal camera is located directly above any of the obstacle avoidance radars, and the rubber shock-absorbing sleeve is mounted on the bottom rod of the landing gear.

[0008] Preferably, the double-tube integrated metal folding part consists of an inner folding part, an outer folding part, a fixing pin, a quick-release pin, an anti-swing pin and a group of anti-swing holes. The inner folding part and the outer folding part are respectively installed on a group of double-tube carbon fiber arms. The fixing pin is installed at the corner connection of the inner folding part and the outer folding part, and the quick-release pin is installed at the other corner connection of the inner folding part and the outer folding part. The fixing pin and the quick-release pin are arranged at the same level. A group of anti-swing holes are opened on one side of the inner folding part and the outer folding part, and are arranged correspondingly. The anti-swing pin slides through a group of anti-swing holes.

[0009] Preferably, the fixing pin, quick-release pin and anti-sway pin are arranged in a triangular structure.

[0010] Compared with related technologies, the coaxial multi-rotor folding-arm large-load transport drone provided by the present invention has the following beneficial effects:

[0011] Compared with the existing technology, the coaxial multi-rotor folding arm large-load transport drone provided by this solution provides stronger structural strength and power output than the traditional single-tube single-motor design through the configuration of double-tube carbon fiber arms and coaxial double-propeller powertrain, meeting the needs of large load capacity. The design of double-tube integrated metal folding parts reduces the clearance and vibration compared with previous folding parts, and improves the stability and safety of the drone. At the same time, the setting of the drone body can also greatly reduce the cost of material transportation, overcome the problems of low efficiency and high risk of previous human and livestock transportation, and at the same time, it has high structural strength, large load capacity, and strong mounting capacity, solving the problems of large-load material transportation and multi-point delivery that similar equipment cannot complete.

[0012] To sum up, the coaxial multi-rotor folding arm large-load transport drone of the utility model has a double-tube integrated arm folding structure, which has high strength, no dead space in contact, effectively suppresses swing, can be quickly stored, and reduces volume. At the same time, it can also solve the problems of low lift, small load, low strength and large vibration of other types of equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the overall three-dimensional structure of a coaxial multi-rotor folding-arm heavy-load transport drone provided by the utility model;

[0014] Figure 2This is a schematic diagram of the main structure of a coaxial multi-rotor folding-arm heavy-load transport drone provided by the present invention, with its double-tube carbon fiber arms in a folded state;

[0015] Figure 3 This is an assembly diagram of the carbon fiber frame fuselage and the multifunctional landing gear provided by the utility model.

[0016] Figure 4 This is an assembly diagram of the double-tube carbon fiber machine arm and the double-tube integrated metal folding part provided by the utility model;

[0017] Figure numerals: 1-1, UAV body; 1, carbon fiber frame fuselage; 2, multi-function landing gear; 3, double-tube carbon fiber arm; 4, coaxial double-propeller power assembly; 5, double-tube integrated metal folding part; 6, inner folding; 7, outer folding; 8, fixing pin; 9, quick release pin; 10, anti-sway pin; 11, anti-sway hole; 12, gimbal camera; 13, obstacle avoidance radar; 14, rubber shock-absorbing sleeve. DETAILED DESCRIPTION

[0018] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application belongs; the terms used herein in the specification of the application are for the purpose of describing specific embodiments only and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the description of the above-mentioned drawings, as well as any variations thereof, are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification and claims of this application or the above-mentioned drawings are used to distinguish different objects, rather than to describe a specific order; the terms "inside", "outside", "left", and "right" indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention.

[0019] References herein to "embodiments" mean that a particular feature, structure, or characteristic described in connection with the embodiments may be included in at least one embodiment of the present application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor does it constitute an independent or alternative embodiment that is mutually exclusive of other embodiments. It is understood, both explicitly and implicitly, by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0020] The present invention provides a coaxial multi-rotor folding arm large load transport drone, such as Figure 1-4As shown, the coaxial multi-rotor folding arm large-load transport drone includes: a drone body 1-1, the drone body 1-1 is composed of a carbon fiber frame fuselage 1, a multi-functional landing gear 2, a group of double-tube carbon fiber arms 3, a coaxial double-propeller power assembly 4 and a double-tube integrated metal folding part 5, the multi-functional landing gear 2 is installed at the bottom of the carbon fiber frame fuselage 1, a group of the double-tube carbon fiber arms 3 are arranged on one side of the carbon fiber frame fuselage 1, the double-tube integrated metal folding part 5 is assembled on a group of the double-tube carbon fiber arms 3, and the coaxial double-propeller power assembly 4 is installed at one end of the double-tube carbon fiber arm 3 away from the carbon fiber frame fuselage 1.

[0021] In this embodiment, the UAV body 1-1 can be folded by the double-tube integrated metal folding part 5 and the double-tube carbon fiber machine arm 3. When folding is required, the quick release pin 9 and the anti-sway pin 10 are removed, and the machine arm is folded upward and leans against the EVA equipment cabin protective cover above the carbon fiber frame fuselage 1. After the propeller is folded, it is fixed to the outer double-tube carbon fiber machine arm 3 through the EVA propeller support. The main structure is in a folded storage state. After folding, the volume of the whole machine is only 1 / 2 of the unfolded state, which is convenient for transportation and transfer. The setting of the double-tube integrated metal folding part 5 can realize the rapid folding of the machine arm. After folding, the volume of the whole machine is only 1 / 2 of the unfolded state, which greatly reduces the volume of the UAV and is convenient. Transport and transfer, through the configuration of the double-tube carbon fiber arm 3 and the coaxial double-propeller powertrain 4, compared with the traditional single-tube single-motor design, provides stronger structural strength and power output, meeting the needs of large load capacity. Through the design of the double-tube integrated metal folding part 5, compared with the previous folding parts, the clearance is reduced, the vibration is reduced, and the stability and safety of the UAV are improved. At the same time, the setting of the UAV body 1-1 can also greatly reduce the cost of material transportation, overcome the low efficiency and high risk of previous human and livestock transportation, and at the same time, with high structural strength, large load capacity and strong mounting capacity, it solves the problems of large-load material transportation and multi-point delivery that similar equipment cannot complete.

[0022] In a further preferred embodiment of the present invention, a threaded hole is provided on the multifunctional landing gear 2, and a stainless steel bolt is threadedly installed on the multifunctional landing gear 2. The stainless steel bolt is threadedly connected to the bottom of the carbon fiber frame fuselage 1, and a locking bolt and a through bolt are threadedly installed on the double-tube integrated metal folding part 5. The locking bolt and the through bolt are both used to connect a group of double-tube carbon fiber arms 3.

[0023] In this embodiment, it is threadedly connected to the multifunctional landing gear 2 through a threaded hole and further threadedly connected to the bottom of the carbon fiber frame fuselage 1 to achieve a stable installation. The locking bolt is used to connect and lock a group of double-tube carbon fiber arms 3 to ensure the stability and safety of the arms in the deployed state. The through bolts and the locking bolts work together to further enhance the connection strength and stability of the arms. By opening threaded holes on the multifunctional landing gear 2 and using stainless steel bolts to threadably connect to the bottom of the carbon fiber frame fuselage 1, a stable connection between the multifunctional landing gear 2 and the carbon fiber frame fuselage 1 is achieved, and the overall structural strength of the UAV body 1-1 is improved. The locking bolts and the through bolts on the double-tube integrated metal folding part 5 work together to ensure the stable connection of the double-tube carbon fiber arms 3 in the deployed state, reducing the risk of loosening or falling off of the arms due to vibration or external force.

[0024] In a further preferred embodiment of the present invention, the multifunctional landing gear 2 is composed of a landing gear, a gimbal camera 12, a group of obstacle avoidance radars 13 and a rubber shock-absorbing sleeve 14. The gimbal camera 12 is installed on the top of the landing gear, and a group of obstacle avoidance radars 13 are respectively installed on both sides of the landing gear. The gimbal camera 12 is located directly above any of the obstacle avoidance radars 13, and the rubber shock-absorbing sleeve 14 is mounted on the bottom rod of the landing gear.

[0025] In this embodiment, the multifunctional landing gear 2 is also provided with a mounting ring. Through the mounting ring, the multifunctional landing gear 2 can mount and transport large-mass materials to meet the material transportation needs of the UAV. Combined with the mounting ring and the flight control system of the UAV body 1-1, the independent throwing function of multiple points can be realized, which is suitable for emergency rescue, material delivery and other scenarios. Through the setting of the gimbal camera 12, and the gimbal camera 12 has a zoom function, it can perform high-precision aerial photography and mapping tasks, and can also obtain accurate distance information from the ground through the laser ranging function. The obstacle avoidance radar 13 can detect obstacles around the UAV body 1-1 in real time to ensure the safety of the UAV body 1-1 during flight. The rubber shock-absorbing sleeve 14 can reduce the impact force of the UAV body 1-1 when landing, protect the UAV body 1-1 and the landing gear from damage, and extend the service life of the UAV body 1-1.

[0026] In a further preferred embodiment of the present invention, the double-tube integrated metal folding part 5 is composed of an inner folding part 6, an outer folding part 7, a fixing pin 8, a quick-release pin 9, an anti-swing pin 10 and a group of anti-swing holes 11. The inner folding part 6 and the outer folding part 7 are respectively installed on a group of double-tube carbon fiber arms 3, the fixing pin 8 is installed at the corner connection of the inner folding part 6 and the outer folding part 7, the quick-release pin 9 is installed at the other corner connection of the inner folding part 6 and the outer folding part 7, the fixing pin 8 and the quick-release pin 9 are arranged at the same level, a group of anti-swing holes 11 are opened on one side of the inner folding part 6 and the outer folding part 7, and are arranged accordingly, and the anti-swing pin 10 slides through a group of anti-swing holes 11.

[0027] In this embodiment, the fixing pin 8 serves as the rotation center of the inner folding part 6 and the outer folding part 7, ensuring that the folding part can maintain a stable rotation trajectory during the folding and unfolding process. The quick-release pin 9 realizes the rapid disassembly and locking of the folding part, and the anti-sway pin 10 realizes the locking and unlocking functions of the folding part. In the locked state, the anti-sway pin 10 passes through the corresponding anti-sway hole 11 to form a triangular structural layout, which effectively suppresses the vertical and lateral swing of the folding part and increases the structural stability of the arm. When the double-tube carbon fiber arm 3 needs to be folded and stored, it is only necessary to pull out the quick-release pin 9 and the anti-sway pin 10 to fold it upward along the fixing pin 8 as the center to realize the quick folding function. By pulling out the quick-release pin 9 and the anti-sway pin 10, the double-tube carbon fiber arm 3 can be folded upward along the fixing pin 8 as the center to realize the quick folding function, which is convenient for the transportation and transfer of the UAV.

[0028] In a further preferred embodiment of the present invention, the fixing pin 8, the quick-release pin 9 and the anti-sway pin 10 are arranged in a triangular structure.

[0029] In this embodiment, the design of the triangular structural layout improves the flight safety of the UAV body 1-1. During flight, even if strong airflow or turbulence is encountered, the folding parts can remain stable, ensuring that the UAV body 1-1 can fly smoothly. The fixing pin 8, the quick-release pin 9 and the anti-sway pin 10 form a triangular structural layout, which effectively suppresses the vertical and lateral swing of the folding parts, increases the structural stability of the arm, and improves the flight safety of the UAV.

[0030] In summary, compared with related technologies, this drone has a double-tube integrated arm folding structure, which has high strength, no dead space in contact, effectively suppresses swing, allows for quick storage, and reduces size. At the same time, it can also solve the problems of low lift, small load, low strength, and high vibration of other types of equipment.

[0031] In the several embodiments provided in this application, it should be understood that the disclosed device can be implemented in other ways.

[0032] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the scope of protection of the present invention. Obviously, the embodiments described are only some embodiments of the present invention, rather than all embodiments. Based on these embodiments, all other embodiments obtained by ordinary technicians in this field without making any creative work are within the scope to be protected by the present invention. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in this field can still combine, add, delete or make other adjustments to the features in the various embodiments of the present invention according to the circumstances without conflict, without making any creative work, so as to obtain different other technical solutions that do not deviate from the concept of the present invention in essence, and these technical solutions also fall within the scope to be protected by the present invention.

Claims

1. A coaxial multi-rotor folding arm large load transport drone, characterized in that: include: A drone body (1-1) is provided, wherein the drone body (1-1) is composed of a carbon fiber frame fuselage (1), a multifunctional landing gear (2), a set of double-tube carbon fiber arms (3), a coaxial double-propeller power assembly (4) and a double-tube integrated metal folding member (5); the multifunctional landing gear (2) is mounted on the bottom of the carbon fiber frame fuselage (1); a set of double-tube carbon fiber arms (3) is arranged on one side of the carbon fiber frame fuselage (1); the double-tube integrated metal folding member (5) is assembled on a set of double-tube carbon fiber arms (3); and the coaxial double-propeller power assembly (4) is mounted on one end of the double-tube carbon fiber arms (3) away from the carbon fiber frame fuselage (1).

2. The coaxial multi-rotor folding-arm heavy-load transport drone according to claim 1, characterized in that: The multifunctional landing gear (2) is provided with a threaded hole, a stainless steel bolt is threadedly mounted on the multifunctional landing gear (2), and the stainless steel bolt is threadedly connected to the bottom of the carbon fiber frame fuselage (1), and a locking bolt and a through bolt are threadedly mounted on the double-tube integrated metal folding member (5), and the locking bolt and the through bolt are both used to connect a set of double-tube carbon fiber machine arms (3).

3. The coaxial multi-rotor folding-arm heavy-load transport drone according to claim 1, characterized in that: The multifunctional landing gear (2) is composed of a landing gear, a pan-tilt camera (12), a group of obstacle avoidance radars (13) and a rubber shock-absorbing sleeve (14), wherein the pan-tilt camera (12) is mounted on the top of the landing gear, a group of obstacle avoidance radars (13) are mounted on both sides of the landing gear, the pan-tilt camera (12) is located directly above any of the obstacle avoidance radars (13), and the rubber shock-absorbing sleeve (14) is mounted on the bottom rod of the landing gear.

4. The coaxial multi-rotor folding-arm heavy-load transport drone according to claim 1, characterized in that: The double-tube integrated metal folding part (5) consists of an inner folding part (6), an outer folding part (7), a fixing pin (8), a quick-release pin (9), an anti-swing pin (10) and a group of anti-swing holes (11). The inner folding part (6) and the outer folding part (7) are respectively installed on a group of the double-tube carbon fiber machine arms (3). The fixing pin (8) is installed at the corner connection of the inner folding part (6) and the outer folding part (7). The quick-release pin (9) is installed at the other corner connection of the inner folding part (6) and the outer folding part (7). The fixing pin (8) and the quick-release pin (9) are arranged at the same level. A group of anti-swing holes (11) are opened on one side of the inner folding part (6) and the outer folding part (7) and are arranged correspondingly. The anti-swing pin (10) slides through the group of anti-swing holes (11).

5. The coaxial multi-rotor folding-arm heavy-load transport drone according to claim 4, characterized in that: The fixing pin (8), quick-release pin (9) and anti-sway pin (10) are arranged in a triangular structure.

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