Engineering heavy load lifting unmanned aerial vehicle

Abstract

This utility model discloses an engineering hoisting heavy-duty drone, including a fuselage frame with a power unit inside, the power unit being a hydraulic power system; the top of the fuselage frame has a folding rotor assembly and a fixed rotor assembly, each with at least one rotor at each end, the power unit driving the rotors to rotate; the fixed rotor assembly is stationary, and the folding rotor assembly and the fixed rotor assembly are in a cross-deployed state during operation; the fuselage frame has a lifting mechanism that lifts the folding rotor assembly upwards; the folding rotor assembly rotates from the top of the fuselage frame to directly above the fixed rotor assembly, forming an overlapping state. The engineering hoisting heavy-duty drone provided by this utility model uses a hydraulic power system, has a strong load-bearing capacity and long range; it features a folding rotor system, reducing its width and meeting the size requirements of road transport.

Description

Technical Field

[0001] This utility model relates to the field of aviation technology, specifically to an engineering hoisting heavy-duty drone. Background Technology

[0002] Using drones for engineering hoisting offers advantages such as flexibility, efficiency, and adaptability to complex environments, leading to their widespread application in various fields. For example, in the geological exploration industry, they are used to move drilling rigs up mountains and across rivers; in the power and telecommunications industry, they are used to transport equipment for the construction and maintenance of towers and base stations; and in the construction industry, they are used to hoist building materials and supplies for high-rise buildings or remote construction sites.

[0003] Existing drones have limited performance, with drawbacks such as insufficient payload, short range, and inconvenient transportation. In scenarios such as the construction of power transmission towers in mountainous areas and the hoisting of geological exploration equipment, the payload capacity of existing drones cannot meet the transportation needs of heavy materials or equipment.

[0004] Therefore, it is necessary to develop a dedicated heavy-duty engineering hoisting drone to further improve its load capacity, range, and flight time, so as to meet the needs of engineering hoisting on a larger scale; and the drone should be easy to transport by ground vehicles by road, so as to quickly reach the hoisting site. Utility Model Content

[0005] This utility model addresses the above-mentioned technical problems by providing an engineering hoisting heavy-duty drone, which adopts a hydraulic power system, has a strong load-bearing capacity and a long range; it also features a foldable rotor system, making it easy to load onto ground vehicles and meeting the size requirements for road transport.

[0006] To achieve the above objectives, the technical solution of this utility model is as follows:

[0007] A heavy-duty unmanned aerial vehicle for engineering hoisting includes a fuselage frame with a power unit inside, the power unit being a hydraulic power system;

[0008] The top of the fuselage frame is provided with a folding rotor assembly and a fixed rotor assembly, with at least one rotor at each end. The power unit drives the rotor to rotate. The fixed rotor assembly is stationary. The folding rotor assembly and the fixed rotor assembly are in a cross-deployment state when working.

[0009] The fuselage frame is equipped with a lifting mechanism that lifts the folding rotor assembly upwards; the folding rotor assembly rotates at the top of the fuselage frame to be directly above the fixed rotor assembly, forming an overlapping state.

[0010] The heavy-duty UAVs used in this project are powered by a hydraulic system with a fuel engine as the prime mover, resulting in a strong load-bearing capacity. Refueling is convenient, and by adding external fuel, they can travel long distances for extended periods, thus achieving a long range. The folding rotor assembly is lifted by a lifting mechanism and then rotated to be directly above the fixed rotor assembly, forming an overlapping state. This significantly reduces the width, facilitating the transport of the UAVs to the lifting site by ground vehicles via road.

[0011] In a further optimized design, the folding rotor assembly includes a continuous folding plate frame, while the fixed rotor assembly includes a fixed plate frame that is broken in the middle.

[0012] The rotors at both ends of the folding rotor assembly are connected as a whole by a folding plate frame, which facilitates the lifting mechanism to lift the entire assembly to a suitable height before rotating and folding it in place. The fixed plate frame of the fixed rotor assembly is broken in the middle, which makes room for the installation of the folding plate frame, allowing the fixed rotor assembly and the folding rotor assembly to be installed on the same plane, which is beneficial to flight stability and controllability.

[0013] In a further optimized design, the folding plate frame includes two parallel folding beams, which are fixedly connected in the middle by several connecting plates; hydraulic oil pipes are provided on the inner side of the folding beams along the length direction, and radiators are provided on the outer sides of both ends;

[0014] The fixed frame includes two sets of two parallel fixed straight beams, which are fixedly connected in the middle by a connecting plate; hydraulic oil pipes are provided on the inner side of the fixed straight beams along the length direction, and a radiator is provided on the outer side of the outer end of each fixed straight beam.

[0015] The radiator is located at the head of the retractable straight beam and the fixed straight beam, which can quickly transfer the heat in the hydraulic oil pipe to the radiator, and then conduct it to the air through the radiator's heat dissipation fins.

[0016] In a further optimized design, the radiator is located at the lower part of the rotor. The radiator dissipates heat rapidly through the exhaust gas from the rotor.

[0017] The scheme is further optimized so that the lifting mechanism includes a lift, a lifting turntable, several support rods and several tie rods;

[0018] A number of the aforementioned support rods are disposed between the lifting turntable and the folding rotor assembly, and a number of the aforementioned tie rods are disposed between the top of the fuselage frame and the folding rotor assembly;

[0019] The elevator lifts the folding rotor assembly to a preset height, and several support rods support the folding rotor assembly; the lifting turntable rotates, causing the folding rotor assembly to rotate directly above the fixed rotor assembly, and several pull rods tighten and lock the folding rotor assembly.

[0020] In a further optimized design, a turntable support plate is provided on the top of the fuselage frame, and the lifting turntable is supported by several rotating rollers on the turntable support plate. The turntable support plate is provided with several limiting wheels to position the rotation of the lifting turntable.

[0021] In a further optimized design, the top of the fuselage frame is provided with several plate frame fasteners to connect and fix the folding rotor assembly and the fixed rotor assembly;

[0022] The plate frame fastener includes a lower fastener and an upper fastener. The lower fastener is fixedly connected to the top of the machine frame, and the upper fastener is connected to the lower fastener.

[0023] The lower fastener and the upper fastener form a limiting and fitting part on one side and a clamping part on the other side, and the clamping part clamps the folding rotor assembly and the fixed rotor assembly.

[0024] When the connection between the upper and lower fasteners is loosened, the upper fastener can be separated from the lower fastener, allowing the folding rotor assembly to be lifted and rotated to achieve folding. The folding rotor assembly or the fixed rotor assembly can also be disassembled for easy maintenance and replacement.

[0025] In a further optimized design, the lower fastener has an L-shaped cross-section with a hook on the horizontal side and a limiting groove on its vertical surface.

[0026] The upper fastener has an F-shaped cross-section with a horizontal side and a hook, and the protrusion on its vertical surface is a limiting protrusion that fits into the limiting groove.

[0027] The limiting protrusion is located in the limiting groove to form the limiting fitting part, and the horizontal side with the upper hook on the lower fastener and the horizontal side with the lower hook on the upper fastener form the clamping part.

[0028] A further optimization involves enclosing each rotor blade with a duct. The duct concentrates the exhaust gas from the rotor blades and directs it backward, improving the rotor's aerodynamic performance and increasing lift. Simultaneously, the duct protects the rotor blades, reducing the risk of blade flapping.

[0029] A further optimized design places the folding rotor assembly and the fixed rotor assembly on the same plane when in the cross-deployed state. Having the fixed rotor assembly and the folding rotor assembly on the same plane improves flight stability and maneuverability.

[0030] The further optimized design includes a rotor comprising blades, a hub, a gearbox, and a hydraulic motor.

[0031] The blades are mounted on the hub, the gearbox is connected to the hub via the blade shaft, and the hydraulic motor is shaft-connected to the gearbox.

[0032] The power unit outputs high-pressure hydraulic oil, which is then fed into the hydraulic motor via pipeline to drive its rotation. After being changed speed by the speed changer, the hydraulic motor drives the propeller shaft to rotate, thereby causing the propeller blades to rotate and generating thrust.

[0033] In a further optimized design, the rotor also includes a flow rectifier cap, which is mounted on the rotor hub. The flow rectifier cap, mounted on the rotor hub, helps improve airflow and reduce drag.

[0034] In a further optimized design, the fuselage frame is a polygonal frame structure, consisting of several round rods and elbow plates connected together.

[0035] The fuselage frame has several detachable cross-shaped railings on its sides and several omnidirectional casters on its bottom. The detachable cross-shaped railings facilitate the installation and maintenance of the power unit, while the omnidirectional casters allow for easy movement of the drone on the ground.

[0036] In a further optimized design, the power unit includes an engine and a hydraulic pump, with the engine driving the hydraulic pump to output high-pressure hydraulic oil.

[0037] Further optimization of the design involves using one, two, or four power units to drive the rotor and generate thrust. Using multiple power units operating in parallel can further enhance the carrying capacity of the heavy-duty engineering drone.

[0038] Compared with existing technologies, the engineering hoisting heavy-load drone of this utility model has the following technical advantages:

[0039] 1. The power unit adopts a hydraulic power system with a fuel engine as the prime mover, which has a stronger load capacity than electric drones; refueling is convenient, and the external fuel capacity can be increased to enable long-distance and long-term flight.

[0040] 2. The use of hydraulic oil pipe transmission is equivalent to mechanical transmission. The oil pipe can be flexibly arranged and can transmit in any direction, which greatly simplifies the structure of the aircraft and improves its reliability.

[0041] 3. The folding rotor assembly is lifted and then rotated to be directly above the fixed rotor assembly, forming an overlapping arrangement. This significantly reduces the width, making it easier to transport the UAV to the hoisting project site by ground vehicles via road transport.

[0042] 4. The radiator is integrated into the folding plate frame and the fixing plate frame, which effectively solves the problem of hydraulic oil heat dissipation in high-power hydraulic systems.

[0043] 5. The radiator is installed inside the duct and uses the rotor exhaust to dissipate heat, which significantly improves the heat dissipation speed. Attached Figure Description

[0044] Figure 1This is a perspective view of the unfolded folding rotor assembly of a specific embodiment of the heavy-duty engineering hoisting drone of this utility model;

[0045] Figure 2 yes Figure 1 A three-dimensional view of the retractable rotor assembly;

[0046] Figure 3 yes Figure 1 A three-dimensional view of the folding plate frame in the folding rotor assembly;

[0047] Figure 4 yes Figure 1 A three-dimensional view of the folding rotor assembly in the middle;

[0048] Figure 5 yes Figure 4 Rotor assembly diagram;

[0049] Figure 6 yes Figure 1 A three-dimensional diagram of the duct in the middle;

[0050] Figure 7 yes Figure 6 3D view of the support rod of the culvert;

[0051] Figure 8 yes Figure 6 A stereoscopic view from another perspective;

[0052] Figure 9 yes Figure 8 A perspective view of the culvert connector on one side;

[0053] Figure 10 yes Figure 8 A perspective view of the connecting component of the culvert on the other side;

[0054] Figure 11 yes Figure 1 A three-dimensional view of the fixed plate frame in the fixed rotor assembly;

[0055] Figure 12 yes Figure 1 A three-dimensional view of the fixed rotor assembly in the image;

[0056] Figure 13 yes Figure 1 A three-dimensional view of the fuselage frame;

[0057] Figure 14 yes Figure 13 A three-dimensional view of the fasteners on the plate frame;

[0058] Figure 15 yes Figure 13 The main view;

[0059] Figure 16 yes Figure 1A perspective view showing the connection between the center-folding rotor assembly, the fixed rotor assembly, and the fuselage frame;

[0060] Figure 17 yes Figure 1 A 3D view of the central lifting mechanism;

[0061] Figure 18 yes Figure 17 Top view;

[0062] Figure 19 yes Figure 17 A 3D view of the center loop ear;

[0063] Figure 20 yes Figure 17 A three-dimensional view of the central strut;

[0064] Figure 21 yes Figure 17 A 3D view of the tie rod;

[0065] Figure 22 yes Figure 16 Partial 3D view of the central lifting turntable;

[0066] Figure 23 yes Figure 16 Front view of the folding rotor assembly and lifting mechanism;

[0067] Figure 24 yes Figure 23 A view of the folding rotor assembly in its raised state;

[0068] Figure 25 yes Figure 24 A three-dimensional image;

[0069] Figure 26 yes Figure 25 Front view of the retractable rotor assembly in its retracted state after rotation;

[0070] Figure 27 yes Figure 26 A three-dimensional image;

[0071] Figure 28 yes Figure 1 A three-dimensional view of the power unit.

[0072] In the diagram: Rotor 1, Blade 11, Hub 12, Radiator Cap 13, Ductwork 14, Gearbox 15, Shaft 151, Hydraulic Motor 16, Fuselage Frame 2, Round Rod 21, Elbow Plate 22, Plate Frame Fastener 23, Lower Fastener 231, Upper Fastener 232, Connecting Hole 233, Limiting Fitting Part 234, Clamping Part 235, Limiting Groove 236, Limiting Protrusion 237, Railing 24, Elevator Mounting Base 25, Tie Rod Base 26, Universal Caster 27, Turntable Support Plate 28, Power Unit 3, Engine 31, Hydraulic Pump 32, Hydraulic Oil Pipe 33, Mounting Bracket 34, Engine Radiator 35, Folding Rotor Assembly 4, Folding Plate 5, Radiator 51, Folding Straight Beam 52, Connecting Plate 53, Gearbox Mounting Plate 54, Duct Support Rod 55, Duct Connector 56, Fixed Rotor Assembly 6, Fixed Plate 7, Fixed Straight Beam 71, Lifting Mechanism 8, Elevator 81, Lifting Turntable 82, Rotating Roller 821, Limiting Wheel 822, Hanging Lug 823, Support Rod 83, Tie Rod 84. Detailed Implementation

[0073] The present invention will now be described in further detail with reference to the embodiments shown in the accompanying drawings.

[0074] like Figures 1 to 28 As shown, this utility model relates to a specific embodiment of a heavy-duty unmanned aerial vehicle (UAV) for engineering hoisting.

[0075] like Figure 1 and Figure 2 As shown, the engineering hoisting heavy-duty drone of this embodiment includes a fuselage frame 2, which houses a power unit 3. Figure 1 and 2 Not shown in the image, such as Figure 28 As shown), power unit 3 is a hydraulic power system with a fuel-powered aircraft engine as the prime mover.

[0076] The top of the fuselage frame 2 is provided with a folding rotor assembly 4 and a fixed rotor assembly 6, with a rotor 1 at each end. That is, the engineering hoisting heavy-duty UAV in this embodiment adopts a quadcopter drive. The quadcopter is only a preferred technical solution of this utility model, and the number of rotors is not limited to this. Two smaller rotors can also be set at each end, or one rotor at one end and two rotors at the other end. The specific number and size of the rotors are determined according to the design requirements.

[0077] Power unit 3 drives rotor 1 to rotate; fixed rotor assembly 6 remains stationary, and folding rotor assembly 4 and fixed rotor assembly 6 are in a cross-deployment state during operation.

[0078] The fuselage frame 2 is provided with a lifting mechanism 8. Preferably, the lifting mechanism 8 is located on the side of the fuselage frame 2, which lifts the folding rotor assembly 4 upward. The folding rotor assembly 4 rotates at the top of the fuselage frame 2 to be directly above the fixed rotor assembly 6, forming an overlapping state.

[0079] The heavy-duty UAV being lifted in this project utilizes a hydraulic power system 3 powered by a fuel-powered aircraft engine, resulting in a strong load-bearing capacity. Refueling is convenient, and the ability to carry additional fuel externally allows for extended, long-distance flight, thus extending the range. The folding rotor assembly 4 is lifted by the lifting mechanism 8 and then rotated to directly above the fixed rotor assembly 6, forming an overlapping state. This significantly reduces the width, facilitating the transport of the UAV to the lifting site via ground vehicles and road transport.

[0080] like Figure 1 As shown, the folding rotor assembly 4 and the fixed rotor assembly 6 are located on the same plane when in the cross-deployed state. Having the fixed rotor assembly 6 and the folding rotor assembly 4 on the same plane is beneficial for flight stability and controllability.

[0081] like Figure 3 and Figure 11 As shown, the folding rotor assembly 4 includes an integrally continuous folding plate frame 5, and the fixed rotor assembly 6 includes a fixed plate frame 7 that is disconnected in the middle.

[0082] The rotors 1 at both ends of the folding rotor assembly 4 are connected as a whole by the folding plate frame 5, which facilitates the lifting mechanism 8 to lift the entire assembly to a suitable height before rotating and folding it in place. The fixing plate frame 7 of the fixed rotor assembly 6 is broken in the middle, which makes room for the installation of the folding plate frame 5, allowing the fixed rotor assembly 6 and the folding rotor assembly 4 to be installed on the same plane, which is beneficial to flight stability and controllability.

[0083] like Figure 3 As shown, the folding plate frame 5 includes two parallel folding straight beams 52, which are fixedly connected in the middle by multiple connecting plates 53; hydraulic oil pipes 33 are provided on the inner side of the folding straight beams 52 along the length direction, and radiators 51 are provided on the outer sides of both ends, that is, there are a total of four radiators 51 on the folding plate frame 5.

[0084] Specifically, the retractable straight beam 52 is made of aluminum square tube with a cross-sectional dimension of 40mm*80mm and a length dimension of 4220mm. Two retractable straight beams 52 are placed parallel to each other on the same plane with their end faces aligned, and are connected by multiple connecting plates 53 to form the main body of the retractable plate frame 5.

[0085] like Figure 11 As shown, the fixed plate frame 7 includes two sets of two parallel fixed straight beams 71, which are fixedly connected in the middle by a connecting plate 53; hydraulic oil pipes 33 are respectively provided on the inner side of the fixed straight beams 71 along the length direction, and a radiator 51 is provided on the outer side of the outer end of each fixed straight beam 71, that is, there are a total of four radiators 51 on the fixed plate frame 7.

[0086] Specifically, the fixed straight beam 71 is an aluminum square tube with a cross-sectional dimension of 40mm*80mm and a length dimension of 1515mm.

[0087] The hydraulic oil pipe 33 is made of metal and is tightly connected to the retractable straight beam 52 and the fixed straight beam 71 by welding or clamping.

[0088] The radiator 51 is located at the head of the retractable straight beam 52 and the fixed straight beam 71. The radiator 51 is an aluminum shovel-tooth radiator 51, which is connected to the retractable straight beam 52 and the fixed straight beam 71 by welding. It can quickly transfer the heat in the hydraulic oil pipe 33 to the radiator 51, and then conduct it to the air through the heat sink of the radiator 51.

[0089] Furthermore, such as Figure 6 As shown, the radiator 51 is located inside the head duct 14 of the folding straight beam 52 and the fixed straight beam 71, so that part of the exhaust of the rotor 1 passes through the surface of the radiator 51, which will significantly improve the heat dissipation speed.

[0090] like Figures 17 to 21 As shown, the lifting mechanism 8 includes a lift 81, a lifting turntable 82, four support rods 83 and four tie rods 84; the four support rods 83 are located between the lifting turntable 82 and the folding rotor assembly 4, and the four tie rods 84 are located between the top of the fuselage frame 2 and the folding rotor assembly 4.

[0091] like Figure 17 , Figure 19 and Figure 20 As described above, four hanging ears 823 are welded onto the lifting turntable 82, the bottom of the support rod 83 is connected to the hanging ears 823, and the upper part has a fork that supports the folding plate frame 5.

[0092] The elevator 81 lifts the folding rotor assembly 4 to a preset height, which needs to be greater than the overall height of the fixed rotor assembly 6. Four support rods 83 support the folding rotor assembly 4. The lifting turntable 82 rotates, causing the folding rotor assembly 4 to rotate directly above the fixed rotor assembly 6. Four tie rods 84 tighten and lock the folding rotor assembly 4.

[0093] like Figure 17 As shown, the lifting platform 81 is a screw jack positioned opposite to the lifting platform. Figure 13 and Figure 23 As shown, the machine frame 2 has lifting platform mounting seats 25 on both sides opposite to each other to fix the screw jack 81.

[0094] like Figures 23 to 27 As shown, the working process of the lifting mechanism 8 is as follows:

[0095] like Figure 24 and Figure 25As shown, first use the screw jack 81 to raise the folding rotor assembly 4 to a preset height (greater than the overall height of the fixed rotor assembly 6), then use four support rods 83 to support the folding rotor assembly 4 on the lifting turntable 82, and then lower the push rod of the screw jack 81; as shown Figure 26 and Figure 27 As shown, the folding rotor assembly 4 is rotated until it overlaps and aligns with the fixed rotor assembly 6 vertically, and then the folding rotor assembly 4 is tightened and locked at the four corners by four telescopic levers 84.

[0096] like Figure 13 and Figure 22 As shown, the top of the fuselage frame 2 is provided with a turntable support plate 28, and the lifting turntable 82 is provided with a number of rotating rollers 821 supported on the turntable support plate 28. The turntable support plate 28 is provided with a number of limiting wheels 822 to position the rotation of the lifting turntable 82.

[0097] Specifically, the lifting turntable 82 has a circular structure, with 16 rotating rollers 821, which are evenly distributed in pairs on the inner and outer sides of the ring of the lifting turntable 82. The turntable support plate 28 also has a circular structure, with 6 limiting wheels 822, which are evenly distributed on the inner side of the ring of the turntable support plate 28 and position the inner ring of the lifting turntable 82.

[0098] like Figure 1 and Figure 13 As shown, the top of the fuselage frame 2 is provided with several plate frame fasteners 23 to connect and fix the folding rotor assembly 4 and the fixed rotor assembly 6; the total number of plate frame fasteners 23 is 16, of which 8 are used for the folding rotor assembly 4 and the fixed rotor assembly 6, respectively, to fix the folding straight beam 52 and the fixed straight beam 71.

[0099] like Figure 14 As shown, the plate frame fastener 23 includes a lower fastener 231 and an upper fastener 232. The lower fastener 231 is fixedly connected to the top of the body frame 2, and the upper fastener 232 is connected to the lower fastener 231.

[0100] The lower fastener 231 and the upper fastener 232 form a limiting and fitting part 234 on one side and a clamping part 235 on the other side. The clamping part 235 clamps the folding straight beam 52 of the folding rotor assembly 4 and the fixing straight beam 71 of the fixing rotor assembly 6. The upper fastener 232 has a connecting hole 233 on the side where the limiting and fitting part 234 is located to fix it to the lower fastener 231.

[0101] When the connection between the upper fastener 232 and the lower fastener 231 is loosened, the upper fastener 232 can slide off and separate from the lower fastener 231, thereby allowing the folding rotor assembly 4 to be lifted and rotated to achieve folding. The folding rotor assembly 4 or the fixed rotor assembly 6 can also be disassembled for easy maintenance and replacement.

[0102] like Figure 14 As shown, the lower fastener 231 has an L-shaped cross-section with an upward hook on the horizontal side, and a limiting groove 236 is provided on its vertical surface; the upper fastener 232 has an F-shaped cross-section with a downward hook on the horizontal side, and a protruding structure on its vertical surface is a limiting protrusion 237 that fits into the limiting groove 236; the limiting protrusion 237 is located in the limiting groove 236 to form a limiting fitting part 234, and the horizontal side with the upward hook on the lower fastener 231 and the horizontal side with the downward hook on the upper fastener 232 form a clamping part 235.

[0103] like Figure 4 and Figure 5 As shown, the rotor 1 includes blades 11, hub 12, gearbox 15 and hydraulic motor 16; blades 11 are mounted on hub 12, gearbox 15 is connected to hub 12 through rotor shaft 151, and hydraulic motor 16 is shaft-connected to gearbox 15.

[0104] like Figure 3 and Figure 11 As shown, the folding plate frame 5 and the fixing plate frame 7 are respectively provided with a gearbox mounting plate 54 at both ends to connect and fix the gearbox 15.

[0105] The high-pressure hydraulic oil output by the power unit 3 is input into the hydraulic motor 16 through the hydraulic oil pipe 33 to drive it to rotate. After being changed by the speed changer 15, it drives the propeller shaft 151 to rotate, thereby driving the propeller hub 12 and the propeller blade 11 to rotate and generate thrust.

[0106] like Figure 4 and Figure 5 As shown, the rotor 1 also includes a fairing cap 13, which is mounted on the rotor hub 12. The fairing cap 13 is mounted on the rotor hub 12, which helps to improve the intake airflow, reduce drag, and also improves the appearance.

[0107] like Figure 1 and Figure 4 As shown, each rotor 1 is surrounded by a duct 14. The duct 14 can concentrate the exhaust gas of the rotor 1 and spray it backward, improving the aerodynamic performance of the rotor 1 and increasing the thrust. At the same time, the duct 14 surrounds and protects the blades 11, which helps to reduce the risk of flapping and improve safety performance.

[0108] like Figures 6 to 10 As shown, duct support rods 55 and duct connectors 56 are respectively installed at both ends of the folding plate frame 5 and the fixing plate frame 7, which are used to install and fix the opposite ends of the duct 14. The duct connectors 56 are connected to the inner wall of the duct 14 and the folding plate frame 5 and the fixing plate frame 7 on the left and right sides respectively.

[0109] like Figure 13 As shown, the fuselage frame 2 is a polygonal frame structure, consisting of several round rods 21 and elbow plates 22 welded together; specifically, the fuselage frame 2 is octagonal.

[0110] like Figure 13 , Figure 15 As shown, the side of the fuselage frame 2 is provided with several detachable cross-shaped railings 24, and the four corners are connected and fixed to the elbow plates 22 welded to the frame by screws.

[0111] The bottom surface of the fuselage frame 2 is provided with several universal casters 27. Specifically, there are 8 universal casters 27 with braking function.

[0112] The detachable cross-shaped railing 24 facilitates the installation and maintenance of the power unit 3, while the omnidirectional casters 27 allow for easy movement of the drone on the ground.

[0113] like Figure 13 and Figure 15 As shown, the top of the fuselage frame 2 is also provided with four tie rod bases 26, which are used to fix the bottom of the tie rod 84. The four tie rods 84 are used to fix the folding rotor assembly 4 in the folded state.

[0114] like Figure 28 As shown, the power unit 3 includes an engine 31 and a hydraulic pump 32 housed within a mounting bracket 34. The engine 31 drives the hydraulic pump 32 to output high-pressure hydraulic oil. The engine 31 is an aviation fuel engine, and an engine radiator 35 is also fixed on the mounting bracket 34 to meet the cooling requirements of the engine 31. The number of power units 3 is at least one, but can also be two or four. The power output from the power unit 3 drives the rotor 1 to rotate. Power is transmitted from the hydraulic pump 32 through hydraulic oil pipes 33 and the hydraulic oil within them. Because the hydraulic oil pipes 33 can be flexibly arranged, the direction of power transmission is unrestricted, and the speed and torque control of the hydraulic transmission system is more precise, which is beneficial to improving flight stability. Using multiple power units working in parallel can further enhance the carrying capacity of the heavy-duty engineering UAV.

[0115] The project involves hoisting heavy-duty drones using a hydraulic power system powered by a fuel engine, which boasts strong load-bearing capacity and long range. It also features a foldable rotor system, whose retractable dimensions meet the requirements for road transport, facilitating the transport of the drone to the hoisting site by ground vehicles.

[0116] In summary, as described in the specification and figures, this utility model has been manufactured into actual samples and subjected to multiple use tests. The test results demonstrate that this utility model achieves its intended purpose, and its practicality is beyond doubt. The embodiments described above are merely for illustrative purposes and are not intended to limit the scope of this utility model. Any equivalent embodiments made by those with common knowledge in the relevant technical field, utilizing the technical content disclosed in this utility model, without departing from the scope of the technical features and similar features disclosed in this utility model, are all within the protection scope of this utility model.

Claims

1. An engineered heavy load lifting drone, characterized by: It includes a fuselage frame (2), which has a power unit (3) inside, and the power unit (3) is a hydraulic power system; The fuselage frame (2) is provided with a folding rotor assembly (4) and a fixed rotor assembly (6) at the top, with at least one rotor (1) at each end. The power unit (3) drives the rotor (1) to rotate. The fixed rotor assembly (6) is fixed and the folding rotor assembly (4) and the fixed rotor assembly (6) are in a cross-deployment state when working. The fuselage frame (2) is provided with a lifting mechanism (8), which lifts the folding rotor assembly (4) upward; the folding rotor assembly (4) rotates to the top of the fuselage frame (2) and is directly above the fixed rotor assembly (6), forming an overlapping state.

2. The engineered crane drone of claim 1, wherein, The folding rotor assembly (4) includes an integrally continuous folding plate frame (5), and the fixed rotor assembly (6) includes a fixed plate frame (7) that is broken in the middle.

3. The engineered crane drone of claim 2, wherein, The folding frame (5) includes two parallel folding beams (52) which are fixedly connected in the middle by several connecting plates (53); the inner side of the folding beams (52) is provided with hydraulic oil pipes (33) along the length direction, and the outer sides of both ends are provided with radiators (51); The fixed frame (7) includes two sets of two parallel fixed straight beams (71), which are fixedly connected in the middle by a connecting plate (53); the inner side of the fixed straight beams (71) is provided with hydraulic oil pipes (33) along the length direction, and the outer side of the outer end of each fixed straight beam (71) is provided with a radiator (51).

4. The engineered crane drone of claim 3, wherein, The radiator (51) is located at the lower part of the rotor (1).

5. The engineered crane drone of claim 1, wherein, The lifting mechanism (8) includes a lift (81), a lifting turntable (82), a number of support rods (83) and a number of tie rods (84). A number of the aforementioned support rods (83) are disposed between the lifting turntable (82) and the folding rotor assembly (4), and a number of the aforementioned tie rods (84) are disposed between the top of the fuselage frame (2) and the folding rotor assembly (4); The elevator (81) lifts the folding rotor assembly (4) to a preset height, and several of the support rods (83) support the folding rotor assembly (4); the lifting turntable (82) rotates and drives the folding rotor assembly (4) to rotate directly above the fixed rotor assembly (6), and several of the pull rods (84) tighten and lock the folding rotor assembly (4).

6. The engineered crane drone of claim 5, wherein, The top of the fuselage frame (2) is provided with a turntable support plate (28), and the lifting turntable (82) is provided with a number of rotating rollers (821) supported on the turntable support plate (28). The turntable support plate (28) is provided with a number of limiting wheels (822) to position the lifting turntable (82) to rotate.

7. The engineered crane drone of claim 1, wherein, The top of the fuselage frame (2) is provided with several plate frame fasteners (23) to connect and fix the folding rotor assembly (4) and the fixed rotor assembly (6). The plate frame fastener (23) includes a lower fastener (231) and an upper fastener (232). The lower fastener (231) is fixedly connected to the top of the body frame (2), and the upper fastener (232) is connected to the lower fastener (231). The lower fastener (231) and the upper fastener (232) form a limiting fitting part (234) on one side and a clamping part (235) on the other side. The clamping part (235) clamps the folding rotor assembly (4) and the fixed rotor assembly (6).

8. The engineered crane drone of claim 7, wherein, The lower fastener (231) has an L-shaped cross section with a horizontal side hook, and its vertical surface is provided with a limiting groove (236). The upper fastener (232) has an F-shaped cross section with a horizontal side hook, and the protrusion structure on its vertical surface is a limiting protrusion (237) that fits into the limiting groove (236). The limiting protrusion (237) is located in the limiting groove (236) to form the limiting fitting part (234), and the horizontal side with an upper hook on the lower fastener (231) and the horizontal side with a lower hook on the upper fastener (232) form the clamping part (235).

9. The engineered crane drone of claim 1, wherein, Each rotor (1) is surrounded by a duct (14).

10. The engineered crane drone of claim 1, wherein, The folding rotor assembly (4) and the fixed rotor assembly (6) are located on the same plane when they are in the cross-deployment state.

11. The engineered crane drone of claim 1, wherein, The rotor (1) includes blades (11), hub (12), gearbox (15) and hydraulic motor (16). The blade (11) is mounted on the hub (12), the gearbox (15) is connected to the hub (12) via the blade shaft (151), and the hydraulic motor (16) is shaft-connected to the gearbox (15). The power unit (3) outputs high-pressure hydraulic oil, which is then fed into the hydraulic motor (16) through a pipeline to drive it to rotate. After being changed by the speed changer (15), the speed changer drives the propeller shaft (151) to rotate, thereby driving the propeller blade (11) to rotate and generate thrust.

12. The engineered crane drone of claim 11, wherein, The rotor (1) also includes a fairing cap (13) which is mounted on the rotor hub (12).

13. The engineered overhead load carrying drone of claim 1, wherein, The fuselage frame (2) is a polygonal frame structure, consisting of several round rods (21) and elbow plates (22) connected together; The fuselage frame (2) has several detachable railings (24) on its side and several universal casters (27) on its bottom.

14. The engineered crane drone of claim 10, wherein, The power unit (3) includes an engine (31) and a hydraulic pump (32), wherein the engine (31) drives the hydraulic pump (32) to output high-pressure hydraulic oil.

15. The engineered overhead load carrying drone of claim 1, wherein, The number of power units (3) is 1, 2 or 4.

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