Split type disaster relief unmanned aerial vehicle

Abstract

According to the technical scheme, the split type disaster relief unmanned aerial vehicle is characterized in that the split type disaster relief unmanned aerial vehicle comprises an upper rack, an upper cantilever assembly, an upper power assembly, a lower rack, a lower cantilever assembly and a lower power assembly, the upper cantilever assembly is installed on the upper rack, the upper power assembly is installed at the end, away from the upper rack, of the upper cantilever assembly, and the lower cantilever assembly is installed on the lower rack; according to the unmanned aerial vehicle, through the unique upper and lower split structural design and the combination of the dynamic adjustment capacity of the rotatable rack and the power assembly, flexible switching of two different working modes is achieved, the modes are switched through one key of the flight control system, and therefore the unmanned aerial vehicle is more convenient to use. Parts do not need to be disassembled or replaced, the shape of the device can be changed according to actual requirements, and therefore the scene adaptability is improved.

Description

Technical Field

[0001] The present invention relates to a drone, and more specifically, to a split-type disaster relief drone. Background Art

[0002] A split-type disaster relief drone is a combined drone of a dual-drone system that achieves rapid separation and flexible deployment through modular design. Its core feature is that it is provided with two separable independent drone modules, thus significantly improving scene adaptability. Disaster relief drones can be classified into various types according to their usage functions, including drones for on-site visual inspection. In actual use, it is found that due to the uncertainty of the disaster situation, drones are usually required to conduct a quick overall visual inspection and assessment, and then use drones to approach the interior of the disaster area for careful search. Due to different purposes, the former usually uses high-power or multi-wing stable drones, and the latter uses smaller drones. This leads to the need to repeatedly release and recover different models of drones, which is likely to waste time and miss the golden time for disaster relief. Therefore, a split-type disaster relief drone is needed, and this device can change its own shape according to actual needs, thereby improving scene adaptability.

[0003] Combined with the above reasons, how to change its own shape is exactly the problem considered in this application. Summary of the Invention

[0004] In view of the deficiencies of the prior art, a split-type disaster relief drone is provided, and this device can change its own shape according to actual needs, thereby improving scene adaptability.

[0005] To achieve the above object, the following technical solutions are provided: The split-type disaster relief drone includes an upper frame, an upper cantilever assembly, an upper power assembly, a lower frame, a lower cantilever assembly, and a lower power assembly. The upper cantilever assembly is installed on the upper frame, and the upper power assembly is installed at one end of the upper cantilever assembly away from the upper frame. The lower cantilever assembly is installed on the lower frame, and the lower power assembly is installed at one end of the lower cantilever assembly away from the lower frame. The upper frame is rotatably connected to the lower frame; In the high-power mode, the upper cantilever assembly and the lower cantilever assembly coincide in the vertical direction, and the upper power assembly and the lower power assembly coincide in the vertical direction; In the multi-wing stable mode, the upper cantilever assembly and the lower cantilever assembly are separated in the vertical direction, and the upper power assembly and the lower power assembly are separated in the vertical direction.

[0006] Further, the lower frame includes a plug post and a plug piece, and the upper frame includes a plug slot and a contact piece. The plug piece is fixedly connected to the plug piece, and the contact piece is fixedly connected to the plug slot. The plug slot is used to accommodate the plug post, and the contact piece is used to contact the plug piece; In the high-power mode and the multi-wing stable mode, the plug post is accommodated in the plug slot, the contact piece is in contact with the plug piece, and the contact piece is in contact with the inner wall of the plug slot; In the separation mode, the plug post is separated from the plug slot, and the abutting piece is separated from the plug piece.

[0007] Furthermore, the lower frame further includes a main motor and a rotating abutting member, and the upper frame further includes a receiving groove, a partition board and an abutting post. The partition board is provided with a through hole, and the partition board is fixedly connected to the receiving groove to form a closed space. The abutting post is fixedly connected to the receiving groove and is arranged in the closed space. The rotating abutting member passes through the through hole and is received in the closed space. The rotating abutting member is used to abut against the abutting post and the partition board, and the main motor is connected to the rotating abutting member; When the rotating abutting member abuts against the abutting post and rotates, the lower frame rotates relative to the upper frame, and the abutting piece is separated from the plug piece; When the rotating abutting member rotates to the through hole, the plug post is separated from the plug slot, and the lower frame is separated from the upper frame.

[0008] Furthermore, the lower cantilever assembly includes a lower cantilever shell and a lower annular track. The lower annular track is fixedly connected to the lower cantilever shell, and the lower power assembly is installed on the lower annular track.

[0009] Furthermore, the lower power assembly includes a lower power motor and lower power blades. The lower power motor is connected to the lower power blades and is used to drive the lower power blades. The lower power blades are slidably connected to the lower annular track.

[0010] Furthermore, the upper cantilever assembly includes an upper cantilever shell and an annular duct. The annular duct is fixedly connected to the upper cantilever shell, and the upper power assembly is installed on the annular duct. The annular duct is used to guide the air flow to be ejected downward.

[0011] Furthermore, the upper power assembly includes a diversion plate, a turbine motor and a turbine fan. The diversion plate, the turbine motor and the turbine fan are all installed in the upper cantilever shell. The turbine motor is connected to the turbine fan, and the diversion plate is used to guide the air flow to the annular duct.

[0012] Furthermore, as the second embodiment of the present invention, the upper cantilever assembly includes an upper cantilever shell and an upper annular track. The upper annular track is fixedly connected to the upper cantilever shell, and the upper power assembly is installed on the upper annular track.

[0013] Furthermore, the upper power assembly includes an upper power motor and upper power blades. The upper power motor is connected to the upper power blades and is used to drive the upper power blades. The upper power blades are slidably connected to the upper annular track.

[0014] To sum up, the above technical solution has the following beneficial effects: the present invention realizes flexible switching between two different working modes through a unique upper and lower split structure design, combined with the dynamic adjustment capability of the rotatable frame and the power assembly, and switches the mode with one key through the flight control system without disassembling or replacing parts, thereby achieving the purpose of changing its own shape according to actual needs, thereby improving the purpose of scene adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the three-dimensional structure of a split-type disaster relief drone; Figure 2 It is a cross-sectional view of the upper frame in the present invention; Figure 3 It is a cross-sectional view of the lower frame in the present invention; Figure 4 It is a schematic diagram of the three-dimensional structure of the lower frame in the present invention; Figure 5 It is a schematic diagram of the three-dimensional structure of the upper frame in the present invention; Figure 6 It is a schematic diagram of the three-dimensional structure of the second embodiment of the present invention.

[0016] Reference numerals: 1, upper frame; 2, upper cantilever assembly; 3, upper power assembly; 4, lower frame; 5, lower cantilever assembly; 6, lower power assembly; 11. Insertion slot; 12. Resistance sheet; 13. Accommodation slot; 14. Blocking plate; 15. Resistance column; 16. Through hole; 21. upper cantilever shell; 22. annular duct; 23. upper annular track; 31. guide plate; 32. turbine motor; 33. turbo fan; 34. upper power motor; 35. upper power blade; 41. Plug-in column; 42. Plug-in sheet; 43. Main motor; 44. Rotating resistance member; 51. lower cantilever shell; 52. lower annular track; 61. Lower power motor; 62. Lower power blade. DETAILED DESCRIPTION

[0017] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. The same parts are represented by the same reference numerals. It should be noted that the words "front", "rear", "left", "right", "upper" and "lower" used in the following description refer to directions in the accompanying drawings, and the words "bottom surface" and "top surface", "inner" and "outer" refer to directions toward or away from the geometric center of a specific component, respectively.

[0018] Reference Figures 1-5As shown, the split-type disaster relief drone includes an upper frame 1, an upper cantilever assembly 2, an upper power assembly 3, a lower frame 4, a lower cantilever assembly 5 and a lower power assembly 6. The upper cantilever assembly 2 is mounted on the upper frame 1, the upper power assembly 3 is mounted on one end of the upper cantilever assembly 2 away from the upper frame 1, the lower cantilever assembly 5 is mounted on the lower frame 4, and the lower power assembly 6 is mounted on one end of the lower cantilever assembly 5 away from the lower frame 4. The upper frame 1 is rotatably connected to the lower frame 4; In the high-power mode, the upper cantilever assembly 2 and the lower cantilever assembly 5 overlap in the vertical direction, and the upper power assembly 3 and the lower power assembly 6 overlap in the vertical direction; In the multi-wing stabilization mode, the upper boom assembly 2 is separated from the lower boom assembly 5 in the vertical direction, and the upper power assembly 3 is separated from the lower power assembly 6 in the vertical direction.

[0019] The drone is divided into an upper frame 1 and a lower frame 4, which can be connected by components such as a rotating shaft, allowing the upper frame 1 and the lower frame 4 to rotate relative to each other in the horizontal plane. The upper frame 1 part extends outward through the upper cantilever assembly 2, and an upper power assembly 3 is installed at the end. The lower frame 4 part is installed in a symmetrical or staggered manner through the lower cantilever assembly 5, and a lower power assembly 6 is also installed at the end. The upper power assembly 3 and the lower power assembly 6 can realize synchronous adjustment of parameters such as rotation speed and inclination angle through the flight control system. In the high-power mode, the upper cantilever assembly 2 and the lower cantilever assembly 5 are adjusted to completely overlap in the vertical direction by rotating the upper frame 1 and the lower frame 4, so that the air flow directions of the upper power assembly 3 and the lower power assembly 6 are coaxially aligned, generating a superimposed lift, which is suitable for occasions requiring a large load (such as delivering relief supplies) or high-speed flight (such as quickly reaching a disaster area). By superimposing power, the load of a single motor is reduced, the life of the power system is extended, and the risk of overheating in a high-temperature environment is avoided; In the multi-wing stable mode, the upper frame 1 and the lower frame 4 rotate relative to each other. If necessary, they can also be converted in the high-power mode or converted to the high-power mode. The upper cantilever assembly 2 and the lower cantilever assembly 5 are driven to rotate to be staggered in the vertical direction, so that the upper power assembly 3 and the lower power foot sword can be distributed on different height planes, thereby forming multiple sets of independent rotors, improving redundancy and stability. It is suitable for occasions that require fine control (such as post-disaster search and rescue positioning), resistance to strong wind interference or long-term hovering (such as communication relay in disaster areas). The flight control system can independently adjust the speed of each motor to offset turbulent disturbances (such as strong side winds in mountain canyons). When a single motor fails, the remaining motors can still maintain balance through power redistribution, and safety redundancy is improved; The present invention realizes flexible switching between two different working modes through a unique upper and lower split structure design, combined with the dynamic adjustment capabilities of a rotatable frame and a power assembly. The mode can be switched with one click through the flight control system without disassembling or replacing parts, thereby achieving the purpose of changing its own shape according to actual needs, thereby improving the purpose of scene adaptability.

[0020] Further, the lower frame 4 includes a plug-in column 41 and a plug-in sheet 42, and the upper frame 1 includes a plug-in slot 11 and a contact sheet 12, the plug-in sheet 42 is fixedly connected to the plug-in sheet 42, and the contact sheet 12 is fixedly connected to the plug-in slot 11, the plug-in slot 11 is used to accommodate the plug-in column 41, and the contact sheet 12 is used to contact the plug-in sheet 42; In the high-power mode and the multi-wing stable mode, the plug-in column 41 is accommodated in the plug-in slot 11, the abutting piece 12 abuts against the plug-in piece 42, and the abutting piece 12 abuts against the inner wall of the plug-in slot 11; In the separation mode, the plug-in post 41 is separated from the plug-in slot 11 , and the abutment piece 12 is separated from the plug-in piece 42 .

[0021] The lower frame 4 and the upper frame 1 include a plug-in structure to achieve rapid switching of different working modes. In the high-power mode and the multi-wing stable mode, the plug-in column 41 of the lower frame 4 is precisely embedded in the plug-in slot 11 of the upper frame 1 to form axial positioning. At the same time, the plug-in piece 42 and the contact piece 12 form a bite structure, which cooperates with the inner wall of the plug-in slot 11 to form a three-dimensional constraint to form a torsion and shear resistance structure. In the separation mode, an axial pull-out design is adopted to separate the lower frame 4 and the upper frame 1 by rotating them to form two independent UAV structures.

[0022] Further, the lower frame 4 also includes a main motor 43 and a rotating resistance member 44, the upper frame 1 also includes a receiving groove 13, a blocking plate 14 and a resistance column 15, the blocking plate 14 is provided with a through hole 16, the blocking plate 14 is fixedly connected to the receiving groove 13 to form a closed space, the resistance column 15 is fixedly connected to the receiving groove 13 and is arranged in the closed space, the rotating resistance member 44 passes through the through hole 16 and is accommodated in the closed space, the rotating resistance member 44 is used to resist the resistance column 15 and the blocking plate 14, and the main motor 43 is connected to the rotating resistance member 44; When the rotating abutment member 44 abuts against the abutment column 15 and rotates, the lower frame 4 and the upper frame 1 rotate relative to each other, and the abutment sheet 12 and the plug-in sheet 42 are separated; When the rotating abutment member 44 rotates to the through hole 16 , the plug-in column 41 is separated from the plug-in slot 11 , and the lower frame 4 is separated from the upper frame 1 .

[0023] Multi-mode rapid switching can be achieved through a mechanical plug-in and rotational separation mechanism. The plug-in column 41 of the lower frame 4 and the plug-in slot 11 of the upper frame 1 form an axial positioning unit to ensure rapid alignment. The plug-in plate 42 and the abutment plate form an anti-torsion and anti-shear unit to realize whether the lower frame 4 is separated from the upper frame 1.

[0024] Furthermore, the lower cantilever assembly 5 includes a lower cantilever shell 51 and a lower annular track 52 . The lower annular track 52 is fixedly connected to the lower cantilever shell 51 , and the lower power assembly 6 is installed on the lower annular track 52 .

[0025] Further, the lower power assembly 6 includes a lower power motor 61 and lower power blades 62. The lower power motor 61 is connected to the lower power blades 62 and is used to drive the lower power blades 62. The lower power blades 62 are slidably connected to the lower annular track 52.

[0026] The lower cantilever shell 51 serves as the core support structure to fix other components. The lower annular track 52 is fixed to the cantilever shell, providing an accurate circular motion path for the lower power assembly 6. The lower power motor 61 serves as the power source to drive the blade movement. The lower power blades 62 are dynamically matched with the lower annular track 52 to achieve controllable movement. Usually, the center of the lower power blades 62 is connected to the lower power motor 61, and the blade ends are slidably connected to the lower annular track 52, making a circular slide along the lower annular track 52 to form a continuous circular motion trajectory. The lower annular track 52 restricts the path of the lower power blades 62 to ensure the movement accuracy.

[0027] Further, the upper cantilever assembly 2 includes an upper cantilever shell 21 and an annular duct 22. The annular duct 22 is fixedly connected to the upper cantilever shell 21. The upper power assembly 3 is installed in the annular duct 22. The annular duct 22 is used to guide the air flow to jet downward.

[0028] Further, the upper power assembly 3 includes a flow guiding plate 31, a turbine motor 32, and a turbine fan 33. The flow guiding plate 31, the turbine motor 32, and the turbine fan 33 are all installed inside the upper cantilever shell 21. The turbine motor 32 is connected to the turbine fan 33. The flow guiding plate 31 is used to guide the air flow to the annular duct 22.

[0029] The bladeless power structure is a new technology, and its main purpose is to avoid the air flow conflict between the upper power assembly 3 and the lower power assembly 6. For the specific principle, reference can be made to Patent CN201920230903.7.

[0030] Further, as Figure 6 shown, as the second embodiment of the present invention, the upper cantilever assembly 2 includes an upper cantilever shell 21 and an upper annular track 23. The upper annular track 23 is fixedly connected to the upper cantilever shell 21. The upper power assembly 3 is installed on the upper annular track 23.

[0031] Further, the upper power assembly 3 includes an upper power motor 34 and upper power blades 35. The upper power motor 34 is connected to the upper power blades 35 and is used to drive the upper power blades 35. The upper power blades 35 are slidably connected to the upper annular track 23.

[0032] In the second embodiment, the upper power assembly 3 also adopts a bladed structure. The structural principle of the cooperation between the upper cantilever assembly 2 and the upper power assembly 3 is the same as that of the cooperation between the lower cantilever assembly 5 and the lower power assembly 6.

[0033] The above are only the preferred embodiments of the present invention. The protection scope of the present invention is not limited to the above embodiments. Any technical solutions falling within the concept of the present invention belong to the protection scope of the present invention. It should be noted that for those of ordinary skill in the art, several improvements and refinements made without departing from the principle of the present invention should also be regarded as within the protection scope of the present invention.

Claims

1. Split-type disaster relief unmanned aerial vehicle, characterized in that, It comprises an upper frame, an upper cantilever assembly, an upper power assembly, a lower frame, a lower cantilever assembly and a lower power assembly, wherein the upper cantilever assembly is mounted on the upper frame, the upper power assembly is mounted on one end of the upper cantilever assembly away from the upper frame, the lower cantilever assembly is mounted on the lower frame, the lower power assembly is mounted on one end of the lower cantilever assembly away from the lower frame, and the upper frame is rotatably connected to the lower frame; In the high-power mode, the upper cantilever assembly overlaps with the lower cantilever assembly in the vertical direction, and the upper power assembly overlaps with the lower power assembly in the vertical direction; In the multi-wing stable mode, the upper boom assembly is separated from the lower boom assembly in the vertical direction, and the upper power assembly is separated from the lower power assembly in the vertical direction.

2. The split-type disaster relief UAV according to claim 1, wherein The lower frame includes a plug-in column and a plug-in sheet, and the upper frame includes a plug-in slot and a contact sheet, the plug-in sheet is fixedly connected to the plug-in sheet, the contact sheet is fixedly connected to the plug-in slot, the plug-in slot is used to accommodate the plug-in column, and the contact sheet is used to contact the plug-in sheet; In the high-power mode and the multi-wing stable mode, the plug-in column is accommodated in the plug-in slot, the abutment sheet abuts against the plug-in sheet, and the abutment sheet abuts against the inner wall of the plug-in slot; In the separation mode, the plug-in column is separated from the plug-in slot, and the abutment sheet is separated from the plug-in sheet.

3. The split disaster relief UAV according to claim 2, characterized in that, The lower frame further includes a main motor and a rotating resistance member, the upper frame further includes a receiving groove, a blocking plate and a resistance column, the blocking plate is provided with a through hole, the blocking plate is fixedly connected to the receiving groove to form a closed space, the resistance column is fixedly connected to the receiving groove and is arranged in the closed space, the rotating resistance member passes through the through hole and is accommodated in the closed space, the rotating resistance member is used to resist the resistance column and the blocking plate, and the main motor is connected to the rotating resistance member; When the rotating abutment piece abuts against the abutment column and rotates, the lower frame and the upper frame rotate relatively, and the abutment piece and the plug-in piece are separated; When the rotating abutment piece rotates to the through hole, the plug-in column is separated from the plug-in slot, and the lower frame is separated from the upper frame.

4. The split-type disaster relief UAV according to any one of claims 1-3, characterized in that, The lower cantilever assembly comprises a lower cantilever shell and a lower annular track, the lower annular track is fixedly connected to the lower cantilever shell, and the lower power assembly is installed on the lower annular track.

5. The split-type disaster relief unmanned aerial vehicle according to claim 4, characterized in that, The lower power assembly includes a lower power motor and a lower power blade. The lower power motor is connected to the lower power blade and is used to drive the lower power blade. The lower power blade is slidably connected to the lower annular track.

6. The split disaster relief UAV according to any one of claims 1-3, characterized in that The upper cantilever assembly includes an upper cantilever shell and an annular duct, wherein the annular duct is fixedly connected to the upper cantilever shell, and the upper power assembly is installed on the annular duct, and the annular duct is used to guide the airflow to spray downward.

7. The split-type disaster relief unmanned aerial vehicle according to claim 6, wherein The upper power assembly includes a guide plate, a turbine motor and a turbofan, which are all installed in an upper cantilever shell. The turbine motor is connected to the turbofan, and the guide plate is used to guide the airflow to flow toward the annular duct.

8. The split-type disaster relief unmanned aerial vehicle according to any one of claims 1-3, characterized in that, The upper cantilever assembly comprises an upper cantilever shell and an upper annular track, the upper annular track is fixedly connected to the upper cantilever shell, and the upper power assembly is installed on the upper annular track.

9. The split disaster relief UAV according to claim 8, wherein, The upper power assembly includes an upper power motor and an upper power blade. The upper power motor is connected to the upper power blade and is used to drive the upper power blade. The upper power blade is slidably connected to the upper annular track.

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