Engineering hoisting heavy-load unmanned aerial vehicle

Abstract

The engineering hoisting heavy-load unmanned aerial vehicle comprises a vehicle body frame, a power unit is arranged in the vehicle body frame, and the power unit is a hydraulic power system; a folding rotor wing group and a fixed rotor wing group are arranged at the top of the fuselage frame, at least one rotor wing is arranged at each of the two ends of the fuselage frame, and the power unit drives the rotor wings to rotate; the fixed rotor group is fixed, and the folding rotor group and the fixed rotor group are in a crossed unfolding state during working; the fuselage frame is provided with a jacking mechanism which is used for jacking the folding rotor wing group upwards; the folding rotor wing set rotates to the position over the fixed rotor wing set at the top of the fuselage frame, and an up-down overlapping state is formed. And the flight control system is used for adjusting the rotating speed of the rotor wings to control the course and the navigational speed of the engineering hoisting heavy-load unmanned aerial vehicle. According to the engineering hoisting heavy-load unmanned aerial vehicle, a hydraulic power system is adopted, the loading capacity is high, and the voyage is long; a foldable rotor wing system is arranged, the width size is reduced, and the size requirement of road transportation is met.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, in particular to an engineering lifting heavy-load UAV. Background Art

[0002] Drones are widely used in various fields for engineering lifting operations due to their flexibility, efficiency, and adaptability to complex environments. Examples include the geological exploration industry, which uses drilling rigs to move up mountains and across rivers; the power and telecommunications industry, which uses equipment for tower and base station construction and maintenance; and the construction industry, which uses drones to lift building materials and supplies for high-rise buildings or remote construction sites.

[0003] Existing drones have limited performance, including insufficient payload, short range, and inconvenient transportation. In scenarios like power transmission tower construction in mountainous areas and lifting geological survey equipment, the payload capacity of existing drones cannot meet the needs of transporting heavy materials or equipment.

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

[0005] In response to the above technical problems, the present invention provides a heavy-load UAV for engineering lifting, which adopts a hydraulic power system, has a strong load-bearing capacity and a long range; it has a foldable rotor system, which is convenient for loading on ground vehicles and meets the size requirements of road transportation.

[0006] To achieve the above object, the technical solution of the present invention is:

[0007] An engineering lifting heavy-load drone comprises a fuselage frame, wherein a power unit is provided inside the fuselage frame, and the power unit is a hydraulic power system;

[0008] The top of the fuselage frame is provided with a foldable rotor group and a fixed rotor group, each of which has at least one rotor, and the power unit drives the rotor to rotate; the fixed rotor group is fixed and stationary, and the foldable rotor group and the fixed rotor group are in a cross-expanded state when working;

[0009] The fuselage frame is provided with a lifting mechanism, which lifts the folding rotor assembly upward; the folding rotor assembly rotates on the top of the fuselage frame to be directly above the fixed rotor assembly, forming an upper and lower overlapping state;

[0010] It also includes a flight control system, which adjusts the rotation speed of the rotor to control the heading and speed of the engineering lifting heavy-load drone.

[0011] The heavy-load lifting drone used in this project utilizes a hydraulic power system powered by a fuel engine, resulting in a strong load capacity. Refueling is convenient, and by increasing the external fuel capacity, it can travel long distances for extended periods, resulting in a long range. The retractable rotor assembly is lifted by a lifting mechanism and then rotated directly above the fixed rotor assembly, forming an overlapping position. This significantly reduces the width of the drone, making it easier to transport the drone to the lifting project site via road transport using ground vehicles.

[0012] According to a further optimized solution, the folding rotor assembly includes an integrally continuous folding plate frame, and the fixed rotor assembly includes a fixed plate frame that is disconnected in the middle.

[0013] The rotors at both ends of the retractable rotor assembly are connected as a single unit via a retractable plate, facilitating their overall lifting to an appropriate height via a lifting mechanism, followed by rotational retraction. The fixed plate for the fixed rotor assembly is disconnected in the middle, freeing up space for the retractable plate, allowing the fixed and retractable rotor assemblies to be mounted on the same surface, enhancing flight stability and controllability.

[0014] Further optimized, the foldable plate frame includes two parallel foldable straight beams, which are fixedly connected in the middle by a plurality of connecting plates; hydraulic oil pipes are respectively provided on the inner side of the foldable straight beams along the length direction, and radiators are respectively provided on the outer sides of both ends;

[0015] The fixed plate frame includes two groups of two parallel fixed straight beams, and the two parallel fixed straight beams are fixedly connected in the middle by a connecting plate; hydraulic oil pipes are respectively 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.

[0016] The radiator is arranged at the head of the folding straight beam and the fixed straight beam, which can quickly transfer the heat in the hydraulic oil pipe to the radiator and then transfer it to the air through the radiator's cooling fins.

[0017] In a further optimized solution, the radiator is arranged at the lower part of the rotor and quickly dissipates heat through the exhaust of the rotor.

[0018] According to a further optimized solution, the lifting mechanism includes a lift, a lifting turntable, a plurality of support rods and a plurality of pull rods;

[0019] A plurality of the support rods are arranged between the lifting turntable and the folding rotor assembly, and a plurality of the pull rods are arranged between the top of the fuselage frame and the folding rotor assembly;

[0020] The elevator lifts the folding rotor assembly to a preset height, and a plurality of the support rods support the folding rotor assembly; the rotation of the lifting turntable drives the folding rotor assembly to rotate to just above the fixed rotor assembly, and a plurality of the pull rods tighten and lock the folding rotor assembly.

[0021] A further optimized solution is that a turntable support plate is provided on the top of the fuselage frame, the lifting turntable is provided with a plurality of rotating rollers supported on the turntable support plate, and the turntable support plate is provided with a plurality of limiting wheels to position the lifting turntable for rotation.

[0022] In a further optimized solution, a plurality of plate fasteners are provided on the top of the fuselage frame to connect and fix the foldable rotor assembly and the fixed rotor assembly;

[0023] The plate frame fastener includes a lower fastener and an upper fastener, the lower fastener is fixedly connected to the top of the fuselage frame, and the upper fastener is connected to the lower fastener;

[0024] The lower fastener and the upper fastener form a limiting fitting portion on one side and a clamping portion on the other side, and the clamping portion clamps the folding rotor assembly and the fixed rotor assembly.

[0025] When the connection between the upper fastener and the lower fastener is loosened, the upper fastener can be separated from the lower fastener, and the folding rotor assembly can 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.

[0026] In a further optimized solution, the cross section of the lower fastener is L-shaped with a hook on the horizontal side, and a limiting groove is provided on its vertical surface;

[0027] The cross section of the upper fastener is an F-shaped one with a horizontal side and a lower hook, and the raised structure on its vertical surface is a limiting protrusion that fits into the limiting groove;

[0028] The limiting protrusion is located in the limiting groove to form the limiting fitting portion, and the horizontal edge of the lower fastener with the upper hook and the horizontal edge of the upper fastener with the lower hook form the clamping portion.

[0029] In a further optimization, each rotor blade is enclosed by a duct. This duct concentrates the exhaust from the rotor blades and sprays it backward, improving the rotor's aerodynamic performance and increasing lift. Furthermore, the duct protects the rotor blades, reducing the risk of blade strikes.

[0030] In a further optimized solution, the retractable rotor group and the fixed rotor group are located on the same plane when in the cross-expanded state. The fixed rotor group and the retractable rotor group being located on the same plane is beneficial to flight stability and controllability.

[0031] According to a further optimized solution, the rotor includes blades, a hub, a speed changer and a hydraulic motor;

[0032] The blades are mounted on the hub, the speed changer is connected to the hub via a propeller shaft, and the hydraulic motor shaft is connected to the speed changer;

[0033] The power unit outputs high-pressure hydraulic oil which is input into the hydraulic motor through a pipeline to drive the hydraulic motor to rotate. After the speed is changed by the speed changer, the propeller shaft is driven to rotate, thereby driving the propeller blades to rotate and generate a thrust force.

[0034] In a further optimized solution, the rotor further includes a fairing cap mounted on the propeller hub. The fairing cap mounted on the propeller hub is beneficial to improving the intake airflow and reducing resistance.

[0035] According to a further optimized solution, the fuselage frame is a polygonal frame structure, which is formed by connecting a number of round rods and brackets;

[0036] The fuselage frame is equipped with several removable cross-shaped railings on the sides and several universal rollers on the bottom. The removable cross-shaped railings facilitate the installation and maintenance of the power unit, and the universal rollers make it easy to move the drone on the ground.

[0037] According to a further optimized solution, the power unit includes an engine and a hydraulic pump, and the engine drives the hydraulic pump to output high-pressure hydraulic oil.

[0038] In a further optimization scheme, the number of power units can be one, two, or four, driving the rotors to rotate and generate thrust. Using multiple power units working in parallel can further enhance the carrying capacity of heavy-load engineering drones.

[0039] Compared with the existing technology, the engineering lifting heavy-load drone of the present invention has the following technical advantages:

[0040] 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. It is easy to refuel, and by increasing the external fuel capacity, it can fly for a long time and long distances.

[0041] 2. It adopts hydraulic oil pipe transmission. Compared with mechanical transmission, the oil pipe can be turned and arranged flexibly, and can transmit in any direction, which greatly simplifies the structure of the aircraft and improves reliability.

[0042] 3. The foldable rotor assembly is lifted and then rotated to the top of the fixed rotor assembly to form an overlapping arrangement, which significantly reduces the width and facilitates the use of ground vehicles to transport the drone to the lifting project site by road.

[0043] 4. The radiator is integrated on the folding plate frame and the fixed plate frame to effectively solve the hydraulic oil heat dissipation problem of the high-power hydraulic system.

[0044] 5. The radiator is set inside the duct and uses the rotor exhaust to dissipate heat, significantly improving the heat dissipation speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1This is a perspective view of a specific embodiment of the engineering lifting heavy-load UAV of the present invention with the foldable rotor assembly unfolded;

[0046] Figure 2 yes Figure 1 A perspective view of the foldable rotor assembly;

[0047] Figure 3 yes Figure 1 A three-dimensional view of a folding plate frame in a folding rotor assembly;

[0048] Figure 4 yes Figure 1 A three-dimensional diagram of the folding rotor assembly;

[0049] Figure 5 yes Figure 4 Rotor assembly diagram in ;

[0050] Figure 6 yes Figure 1 The duct stereogram in

[0051] Figure 7 yes Figure 6 Stereoscopic diagram of the middle duct support rod;

[0052] Figure 8 yes Figure 6 A stereogram from another perspective;

[0053] Figure 9 yes Figure 8 A perspective view of the duct connection piece on one side;

[0054] Figure 10 yes Figure 8 A perspective view of the duct connection piece on the other side;

[0055] Figure 11 yes Figure 1 A perspective view of a fixed plate frame in a fixed rotor assembly;

[0056] Figure 12 yes Figure 1 A three-dimensional view of the fixed rotor group in FIG;

[0057] Figure 13 yes Figure 1 A perspective view of the fuselage frame in FIG;

[0058] Figure 14 yes Figure 13 A perspective view of the plate rack fastener in FIG;

[0059] Figure 15 yes Figure 13 The main view;

[0060] Figure 16 yes Figure 1A three-dimensional diagram showing the connection between the mid-folding rotor assembly, the fixed rotor assembly, and the fuselage frame;

[0061] Figure 17 yes Figure 1 A three-dimensional diagram of the middle lifting mechanism;

[0062] Figure 18 yes Figure 17 A top view of

[0063] Figure 19 yes Figure 17 A three-dimensional image of the middle mounting ear;

[0064] Figure 20 yes Figure 17 A perspective view of the center support rod;

[0065] Figure 21 yes Figure 17 A three-dimensional view of the center tie rod;

[0066] Figure 22 yes Figure 16 Partial perspective view of the middle lifting turntable;

[0067] Figure 23 yes Figure 16 Front view of the mid-folding rotor assembly and the lifting mechanism;

[0068] Figure 24 yes Figure 23 A view of the rotor assembly in the lifted state with the center-folded rotor assembly;

[0069] Figure 25 yes Figure 24 Stereoscopic image of

[0070] Figure 26 yes Figure 25 The main view of the mid-folding rotor assembly in the folded state after rotation;

[0071] Figure 27 yes Figure 26 Stereoscopic image of

[0072] Figure 28 yes Figure 1 A three-dimensional diagram of the power unit.

[0073] In the figure: rotor 1, blade 11, hub 12, fairing cap 13, duct 14, speed changer 15, propeller shaft 151, hydraulic motor 16, fuselage frame 2, round rod 21, toggle 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 seat 25, pull rod base 26, universal roller 27, turntable support plate 28, power Unit 3, engine 31, hydraulic pump 32, hydraulic oil pipe 33, mounting frame 34, engine radiator 35, folding rotor group 4, folding plate frame 5, radiator 51, folding straight beam 52, connecting plate 53, transmission mounting plate 54, duct support rod 55, duct connector 56, fixed rotor group 6, fixed plate frame 7, fixed straight beam 71, jacking mechanism 8, elevator 81, jacking turntable 82, rotating roller 821, limiting wheel 822, hanging ear 823, support rod 83, pull rod 84. DETAILED DESCRIPTION

[0074] The present invention will be described in further detail below with reference to the embodiments in the accompanying drawings.

[0075] like Figures 1 to 28 As shown, a specific embodiment of the engineering lifting heavy-load drone of the present invention.

[0076] like Figure 1 and Figure 2 As shown, the engineering lifting heavy-load UAV of this embodiment includes a fuselage frame 2, inside which a power unit 3 ( Figure 1 and 2 Not shown, such as Figure 28 As shown), the power unit 3 is a hydraulic power system using a fuel aircraft engine as a prime mover.

[0077] A foldable rotor group 4 and a fixed rotor group 6 are provided on the top of the fuselage frame 2, and a rotor 1 is provided at each end. That is, the engineering lifting heavy-load drone of this embodiment adopts a four-rotor drive. The four-rotor is only an optimal technical solution of the present invention, and the number of rotors is not limited to this; two smaller rotors can also be provided at each end, or one rotor at one end and two rotors at the other end. The specific number and size of the rotors depend on the design requirements.

[0078] The power unit 3 drives the rotor 1 to rotate respectively; the fixed rotor group 6 is fixed, and the folding rotor group 4 and the fixed rotor group 6 are in a cross-expanded state when working.

[0079] The fuselage frame 2 is provided with a lifting mechanism 8. Preferably, the lifting mechanism 8 is arranged on the side of the fuselage frame 2, which lifts the folding rotor group 4 upward; the folding rotor group 4 rotates at the top of the fuselage frame 2 to just above the fixed rotor group 6, forming an upper and lower overlapping state.

[0080] The engineering heavy-load lifting UAV further includes a flight control system (not shown in the figure), which adjusts the rotation speed of the rotor 1 to control the heading and speed of the engineering heavy-load lifting UAV.

[0081] This heavy-load lifting drone utilizes a hydraulic power unit (power unit 3) powered by a fuel-powered aircraft engine, resulting in a strong load capacity. Refueling is convenient, and by increasing the external fuel capacity, it can travel long distances for extended periods, resulting in a long range. The retractable rotor assembly (4) is lifted by a lifting mechanism (8) and then rotated directly above the fixed rotor assembly (6), forming an overlapping position. This significantly reduces the width of the drone, making it easier to transport the drone to the lifting site via road using ground vehicles.

[0082] 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-expanded state. The fixed rotor assembly 6 and the folding rotor assembly 4 being located on the same plane is beneficial to flight stability and controllability.

[0083] 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 interrupted in the middle.

[0084] The rotors 1 at both ends of the retractable rotor assembly 4 are connected as a single unit via a retractable plate 5, facilitating their overall lifting to an appropriate height by a lifting mechanism 8, followed by their rotational retraction. The fixed plate 7 of the fixed rotor assembly 6 is interrupted in the middle, freeing up space for the retractable plate 5. This allows the fixed rotor assembly 6 and the retractable rotor assembly 4 to be mounted on the same plane, enhancing flight stability and maneuverability.

[0085] like Figure 3 As shown, the foldable plate frame 5 includes two parallel foldable straight beams 52, which are fixedly connected in the middle by multiple connecting plates 53; hydraulic oil pipes 33 are respectively provided on the inner sides of the foldable straight beams 52 along the length direction, and radiators 51 are respectively provided on the outer sides of both ends, that is, there are four radiators 51 on the foldable plate frame 5.

[0086] Specifically, the folding straight beam 52 is an aluminum square tube with a cross-sectional dimension of 40mm*80mm and a length of 4220mm. Two folding straight beams 52 are placed parallel to each other on the same plane with their ends aligned, and connected by multiple connecting plates 53 to form the main body of the folding plate frame 5.

[0087] like Figure 11As shown, the fixed plate frame 7 includes two groups of two parallel fixed straight beams 71, and the two parallel fixed straight beams 71 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 four radiators 51 on the fixed plate frame 7.

[0088] Specifically, the fixed straight beam 71 is an aluminum square tube with a cross-sectional size of 40 mm*80 mm and a length of 1515 mm.

[0089] The hydraulic oil pipe 33 is a metal oil pipe, which is tightly connected to the folding straight beam 52 and the fixed straight beam 71 by welding or clamping.

[0090] The radiator 51 is arranged at the head of the folding straight beam 52 and the fixed straight beam 71. The radiator 51 adopts an aluminum skived tooth radiator 51 and is connected to the folding straight beam 52 and the fixed straight beam 71 by welding; the heat in the hydraulic oil pipe 33 can be quickly transferred to the radiator 51 and then transferred to the air through the heat sink of the radiator 51.

[0091] Furthermore, if Figure 6 As shown, the radiator 51 is arranged 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.

[0092] like Figures 17 to 21 As shown, the lifting mechanism 8 includes an elevator 81, a lifting turntable 82, four support rods 83 and four pull rods 84; the four support rods 83 are arranged between the lifting turntable 82 and the folding rotor group 4, and the four pull rods 84 are arranged between the top of the fuselage frame 2 and the folding rotor group 4.

[0093] like Figure 17 、 Figure 19 and Figure 20 As described above, four hanging ears 823 are welded on 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 supported on the folding plate frame 5 .

[0094] The elevator 81 lifts the folding rotor group 4 to a preset height, which needs to be greater than the overall height of the fixed rotor group 6. The four support rods 83 support the folding rotor group 4; the rotation of the lifting turntable 82 drives the folding rotor group 4 to rotate to just above the fixed rotor group 6, and the four pull rods 84 tighten and lock the folding rotor group 4.

[0095] like Figure 17 As shown, the elevator 81 is a screw elevator arranged relatively. Figure 13 and Figure 23As shown, elevator mounting bases 25 are provided on opposite sides of the fuselage frame 2 for fixing the screw elevator 81 .

[0096] like Figures 23 to 27 As shown, the working process of the lifting mechanism 8 is as follows:

[0097] like Figure 24 and Figure 25 As shown, first use the screw lift 81 to lift the folding rotor assembly 4 to a preset height (greater than the overall height of the fixed rotor assembly 6), 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 lift 81; Figure 26 and Figure 27 As shown, the folding rotor assembly 4 is pushed to rotate until it overlaps and aligns with the fixed rotor assembly 6, and then the folding rotor assembly 4 is tightened and locked at the four corners through four retractable pull rods 84.

[0098] like Figure 13 and Figure 22 As shown, a turntable support plate 28 is provided on the top of the fuselage frame 2, and a lifting turntable 82 is provided with a plurality of rotating rollers 821 supported on the turntable support plate 28, and a plurality of limiting wheels 822 are provided on the turntable support plate 28 to position the lifting turntable 82 for rotation.

[0099] Specifically, the lifting turntable 82 is a circular ring structure, with 16 rotating rollers 821, each evenly spaced in pairs and positioned on the inner and outer sides of the ring of the lifting turntable 82. The turntable support plate 28 is also a circular ring structure, with 6 limiting wheels 822, evenly spaced on the inner side of the ring of the turntable support plate 28, to position the inner ring of the lifting turntable 82.

[0100] like Figure 1 and Figure 13 As shown, a plurality of plate fasteners 23 are provided on the top of the fuselage frame 2 to connect and fix the folding rotor group 4 and the fixed rotor group 6; the total number of plate fasteners 23 is 16, of which 8 are used for the folding rotor group 4 and the fixed rotor group 6, respectively, to fix the folding straight beam 52 and the fixed straight beam 71.

[0101] 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 fuselage frame 2 , and the upper fastener 232 is connected to the lower fastener 231 .

[0102] Lower fastener 231 and upper fastener 232 form a stopper and abutment portion 234 on one side and a clamping portion 235 on the other side. Clamping portion 235 clamps folding beam 52 of folding rotor assembly 4 and fixed beam 71 of fixed rotor assembly 6. Upper fastener 232 has a connecting hole 233 on the side where stopper and abutment portion 234 is located, securing it to lower fastener 231.

[0103] When the connection between the upper fastener 232 and the lower fastener 231 is loosened, the upper fastener 232 can slide back and forth from the lower fastener 231 and then the folding rotor group 4 can be lifted and rotated to achieve folding. The folding rotor group 4 or the fixed rotor group 6 can also be disassembled for easy maintenance and replacement.

[0104] like Figure 14 As shown, the cross-section of the lower fastener 231 is L-shaped with an upper hook on the horizontal side, and a limiting groove 236 is provided on its vertical surface; the cross-section of the upper fastener 232 is F-shaped with a lower hook on the horizontal side, and the raised structure on its vertical surface is a limiting protrusion 237 that fits with the limiting groove 236; the limiting protrusion 237 is located in the limiting groove 236 to form a limiting fitting portion 234, and the horizontal side of the upper fastener 231 with the upper hook and the horizontal side of the upper fastener 232 with the lower hook form a clamping portion 235.

[0105] like Figure 4 and Figure 5 As shown, the rotor 1 includes blades 11, a hub 12, a speed changer 15 and a hydraulic motor 16; the blades 11 are mounted on the hub 12, the speed changer 15 is connected to the hub 12 via a propeller shaft 151, and the hydraulic motor 16 is connected to the speed changer 15.

[0106] like Figure 3 and Figure 11 As shown, the folding plate frame 5 and the fixed plate frame 7 are respectively provided with a transmission mounting plate 54 at both ends thereof to connect and fix the transmission 15 .

[0107] The power unit 3 outputs high-pressure hydraulic oil which is input into the hydraulic motor 16 through the hydraulic oil pipe 33 to drive the hydraulic motor 16 to rotate. After the speed is changed by the speed changer 15, the propeller shaft 151 is driven to rotate, thereby driving the propeller hub 12 and the propeller blades 11 to rotate and generate a thrust force.

[0108] like Figure 4 and Figure 5 As shown, the rotor 1 further includes a fairing cap 13, which is mounted on the hub 12. The fairing cap 13 is mounted on the hub 12, which is beneficial to improving the intake airflow, reducing resistance, and improving the appearance.

[0109] like Figure 1 and Figure 4 As shown, each rotor 1 is surrounded by a duct 14. Duct 14 concentrates the exhaust from rotor 1 and sprays it backward, improving the aerodynamic performance and lift of rotor 1. Duct 14 also surrounds and protects blades 11, reducing the risk of blade strikes and improving safety.

[0110] like Figures 6 to 10As shown, duct support rods 55 and duct connectors 56 are respectively installed at both ends of the folding plate frame 5 and the fixed plate frame 7, which are used to install the opposite ends of the fixed duct 14, wherein the duct connectors 56 are connected between the inner wall of the duct 14 and the folding plate frame 5 and the fixed plate frame 7 on the left and right sides.

[0111] like Figure 13 As shown, the fuselage frame 2 is a polygonal frame structure, which is formed by welding a plurality of round rods 21 and brackets 22; specifically, the fuselage frame 2 is an octagon.

[0112] like Figure 13 、 Figure 15 As shown, a plurality of detachable cross-shaped railings 24 are provided on the side of the fuselage frame 2, and the four corners thereof are connected and fixed to the brackets 22 welded to the frame by screws.

[0113] The bottom surface of the fuselage frame 2 is provided with a plurality of universal rollers 27 . Specifically, there are eight universal rollers 27 with a brake function.

[0114] The detachable cross railing 24 facilitates the installation and maintenance of the power unit 3, and the universal roller 27 can easily move the drone on the ground.

[0115] like Figure 13 and Figure 15 As shown, four tie rod bases 26 are further provided on the top of the fuselage frame 2 for fixing the bottom of the connecting tie rods 84 . The four tie rods 84 are used to fix the folding rotor assembly 4 in the folded state.

[0116] like Figure 28 As shown, the power unit 3 includes an engine 31 and a hydraulic pump 32 arranged in a mounting frame 34. The engine 31 drives the hydraulic pump 32 to output high-pressure hydraulic oil. The engine 31 uses an aviation fuel engine. In addition, an engine radiator 35 is fixed on the mounting frame 34 to meet the heat dissipation needs of the engine 31. The number of power units 3 is at least 1. Of course, the number of power units 3 can also be 2 or 4. The power output by the power unit 3 drives the rotor 1 to rotate. The power is transmitted by the hydraulic pump 32 through the hydraulic oil pipe 33 and the hydraulic oil therein. Because the hydraulic oil pipe 33 can be flexibly turned and arranged, the direction of power transmission is not restricted, and the speed and torque control of the hydraulic transmission system is more precise, which is conducive to improving flight stability. Using multiple power units to work in parallel can further enhance the carrying capacity of engineering heavy-load drones.

[0117] The heavy-load UAV in this project is hoisted with a hydraulic power system using a fuel engine as the prime mover, which has a strong load-bearing capacity and a long range. It has a foldable rotor system, and the external dimensions of the rotor after folding meet the size requirements of road transportation, making it convenient to use ground vehicles to transport the UAV to the lifting project site by road.

[0118] In summary, the present invention, as described in the specification and illustrations, has been manufactured into actual samples and tested multiple times. The test results show that the invention can achieve its intended purpose and its practicality is beyond doubt. The above embodiments are only used to facilitate the description of the content of the invention and are not intended to be formally limited thereto. Any equivalent embodiment made by a person with common knowledge in the relevant technical field and making partial changes or modifications to the technical content disclosed in the invention without departing from the scope of the technical features and similar features of the present invention, falls within the scope of protection of the present invention.

Claims

1. A heavy-load UAV for engineering lifting, characterized by: It comprises a fuselage frame (2), inside of which a power unit (3) is provided, and the power unit (3) is a hydraulic power system; A foldable rotor group (4) and a fixed rotor group (6) are provided on the top of the fuselage frame (2), and at least one rotor (1) is provided at each end thereof, and the power unit (3) drives the rotors (1) to rotate respectively; the fixed rotor group (6) is fixed, and the foldable rotor group (4) and the fixed rotor group (6) are in a cross-expanded 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 on the top of the fuselage frame (2) to be directly above the fixed rotor assembly (6), forming an upper and lower overlapping state; It also includes a flight control system, which adjusts the rotation speed of the rotor to control the heading and speed of the engineering lifting heavy-load drone.

2. The heavy-load engineering lifting drone according to claim 1 is characterized in that: The folding rotor assembly (4) comprises an integrally continuous folding plate frame (5), and the fixed rotor assembly (6) comprises a fixed plate frame (7) that is disconnected in the middle.

3. The heavy-load drone for engineering lifting according to claim 2 is characterized in that: The folding plate frame (5) comprises two parallel folding straight beams (52) fixedly connected in the middle by a plurality of connecting plates (53); hydraulic oil pipes (33) are respectively provided on the inner sides of the folding straight beams (52) along the length direction, and radiators (51) are respectively provided on the outer sides of both ends; The fixed plate frame (7) comprises two groups of two parallel fixed straight beams (71), the two parallel fixed straight beams (71) being fixedly connected in the middle by a connecting plate (53); hydraulic oil pipes (33) are respectively provided on the inner sides 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).

4. The heavy-load drone for engineering lifting according to claim 3 is characterized in that: The radiator (51) is arranged at the lower part of the rotor (1).

5. The heavy-load drone for engineering lifting according to claim 1 is characterized in that: The lifting mechanism (8) includes a lift (81), a lifting turntable (82), a plurality of support rods (83) and a plurality of pull rods (84); A plurality of the support rods (83) are arranged between the lifting turntable (82) and the folding rotor assembly (4), and a plurality of the pull rods (84) are arranged 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 a plurality of the support rods (83) support the folding rotor assembly (4); the rotation of the lifting turntable (82) drives the folding rotor assembly (4) to rotate to the top of the fixed rotor assembly (6), and a plurality of the pull rods (84) tighten and lock the folding rotor assembly (4).

6. The heavy-load drone for engineering lifting according to claim 5 is characterized in that: A turntable support plate (28) is provided on the top of the fuselage frame (2), the lifting turntable (82) is provided with a plurality of rotating rollers (821) supported on the turntable support plate (28), and the turntable support plate (28) is provided with a plurality of limiting wheels (822) for positioning the lifting turntable (82) for rotation.

7. The heavy-load engineering lifting drone according to claim 1 is characterized in that: A plurality of plate fasteners (23) are provided on the top of the fuselage frame (2) for connecting and fixing the folding rotor assembly (4) and the fixed rotor assembly (6); The plate frame fastener (23) comprises a lower fastener (231) and an upper fastener (232), wherein the lower fastener (231) is fixedly connected to the top of the fuselage 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 portion (234) on one side and a clamping portion (235) on the other side. The clamping portion (235) clamps the folding rotor assembly (4) and the fixed rotor assembly (6).

8. The heavy-load drone for engineering lifting according to claim 7 is characterized in that: The cross section of the lower fastener (231) is L-shaped with a hook on the horizontal side, and a limiting groove (236) is provided on its vertical surface; The cross section of the upper fastener (232) is an F-shaped one with a horizontal side and a lower hook, and the raised 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 portion (234), and the horizontal edge with the upper hook on the lower fastener (231) and the horizontal edge with the lower hook on the upper fastener (232) form the clamping portion (235).

9. The heavy-load drone for engineering lifting according to claim 1 is characterized in that: The periphery of each rotor (1) is covered with a duct (14).

10. The heavy-load drone for engineering lifting according to claim 1 is characterized in that: The folding rotor assembly (4) and the fixed rotor assembly (6) are located on the same plane when in a cross-expanded state.

11. The heavy-load drone for engineering lifting according to claim 1 is characterized in that: The rotor (1) includes blades (11), a hub (12), a speed changer (15) and a hydraulic motor (16); The blade (11) is mounted on the hub (12), the speed changer (15) is connected to the hub (12) via a propeller shaft (151), and the hydraulic motor (16) is axially connected to the speed changer (15); The power unit (3) outputs high-pressure hydraulic oil which is input into the hydraulic motor (16) through a pipeline to drive the hydraulic motor (16) to rotate. After the speed is changed by the speed changer (15), the propeller shaft (151) is driven to rotate, thereby driving the propeller blade (11) to rotate and generate a thrust force.

12. The heavy-load engineering lifting drone according to claim 11, characterized in that: The rotor (1) further includes a fairing cap (13) which is mounted on the hub (12).

13. The heavy-load drone for engineering lifting according to claim 1 is characterized in that: The fuselage frame (2) is a polygonal frame structure, formed by connecting a plurality of round rods (21) and brackets (22); The side of the fuselage frame (2) is provided with a plurality of detachable railings (24), and the bottom surface is provided with a plurality of universal rollers (27).

14. The heavy-load UAV for engineering lifting according to claim 10, characterized in that: The power unit (3) comprises an engine (31) and a hydraulic pump (32), and the engine (31) drives the hydraulic pump (32) to output high-pressure hydraulic oil.

15. The heavy-load drone for engineering lifting according to claim 1, characterized in that: The number of the power units (3) is 1, 2 or 4.

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