Split disaster relief drone

Abstract

The present invention seeks protection for a split-type disaster relief drone, the key points of which are that it 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, the upper power assembly is installed on the end of the upper cantilever assembly away from the upper frame, the lower cantilever assembly is installed on the lower frame, the lower power assembly is installed on the end of the lower cantilever assembly away from the lower frame, and the upper frame is rotatably connected to the lower frame. The present invention realizes flexible switching between two different working modes through a unique upper and lower split structural design, combined with the dynamic adjustment capabilities of the rotatable frame and power assembly. The mode is switched with one click through the flight control system without the need to disassemble or replace parts, thereby achieving the purpose of changing its own shape according to actual needs, thereby improving scene adaptability.

Description

Technical Field

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

[0002] The split-type disaster relief drone is a dual-drone system combination drone that achieves rapid separation and flexible deployment through modular design. Its core feature is that it is equipped with two detachable independent drone modules, which significantly improves the adaptability to the scene. Disaster relief drones can be divided into many types according to their functions, including drones used for on-site visual inspections. In actual use, it is found that due to the uncertainty of the disaster situation, drones are usually required to conduct a rapid overall visual inspection and assessment, and then use drones to conduct a careful search close to the disaster area. Due to different purposes, the former usually uses high-power or multi-wing stabilized drones, and the latter uses smaller drones. This requires repeated release and recovery of drones of different models, which can easily waste time and miss the golden time for disaster relief. Therefore, a split-type disaster relief drone is needed. The device can change its own shape according to actual needs, thereby improving scene adaptability.

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

[0004] In response to the shortcomings of existing technologies, a split-type disaster relief drone is provided. The device can change its shape according to actual needs, thereby improving scene adaptability.

[0005] To achieve the above-mentioned purpose, the following technical solution is provided: a split-type disaster relief drone, comprising 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 an 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 an end of the lower cantilever assembly away from the lower frame, and the upper frame and the lower frame are rotatably connected;

[0006] In high-power mode, the upper cantilever assembly and the lower cantilever assembly overlap in the vertical direction, and the upper power assembly and the lower power assembly overlap in the vertical direction;

[0007] In the multi-wing stabilization mode, the upper boom assembly and the lower boom assembly are separated in the vertical direction, and the upper power assembly and the lower power assembly are separated in the vertical direction.

[0008] Furthermore, 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;

[0009] In the high-power mode and the multi-wing stable mode, the plug-in column is accommodated in the plug-in slot, the abutting piece abuts against the plug-in piece, and the abutting piece abuts against the inner wall of the plug-in slot;

[0010] In the separation mode, the plug-in post is separated from the plug-in slot, and the abutment piece is separated from the plug-in piece.

[0011] Furthermore, the lower frame also includes a main motor and a rotating resistance member, the upper frame also 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;

[0012] When the rotating abutment member abuts against the abutment column and rotates, the lower frame and the upper frame rotate relative to each other, and the abutment piece and the plug-in piece are separated;

[0013] When the rotating resistance 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.

[0014] 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.

[0015] Furthermore, 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.

[0016] 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, the upper power assembly is installed on the annular duct, and the annular duct is used to guide the airflow to spray downward.

[0017] Furthermore, the upper power assembly includes a guide plate, a turbine motor and a turbofan. The guide plate, the turbine motor and the turbofan are all installed in the upper cantilever shell. The turbine motor is connected to the turbofan, and the guide plate is used to guide the airflow to the annular duct.

[0018] Furthermore, as a 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.

[0019] Furthermore, 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.

[0020] 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 power assembly. The mode can be switched with one click through the flight control system without disassembly or replacement of parts, thereby realizing the purpose of changing its own shape according to actual needs, thereby improving the adaptability to the scene. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the three-dimensional structure of a split-type disaster relief drone;

[0022] Figure 2 It is a cross-sectional view of the upper frame in the present invention;

[0023] Figure 3 It is a cross-sectional view of the lower frame of the present invention;

[0024] Figure 4 It is a schematic diagram of the three-dimensional structure of the lower frame in the present invention;

[0025] Figure 5 It is a schematic diagram of the three-dimensional structure of the upper frame in the present invention;

[0026] Figure 6 It is a schematic diagram of the three-dimensional structure of the second embodiment of the present invention.

[0027] Reference numerals: 1, upper frame; 2, upper cantilever assembly; 3, upper power assembly; 4, lower frame; 5, lower cantilever assembly; 6, lower power assembly;

[0028] 11. Insertion slot; 12. Interference piece; 13. Accommodation slot; 14. Blocking plate; 15. Interference column; 16. Through hole;

[0029] 21. Upper cantilever shell; 22. Annular duct; 23. Upper annular track;

[0030] 31. Guide plate; 32. Turbine motor; 33. Turbofan; 34. Upper power motor; 35. Upper power blade;

[0031] 41. Connecting post; 42. Connecting piece; 43. Main motor; 44. Rotating resistance member;

[0032] 51. Lower cantilever shell; 52. Lower annular track;

[0033] 61. Lower power motor; 62. Lower power blade. DETAILED DESCRIPTION

[0034] The present invention will be described in further detail below with reference to the accompanying drawings and embodiments. Identical components are denoted by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "upper," and "lower" used in the following description refer to directions in the accompanying drawings, and the terms "bottom," "top," "inner," and "outer" refer to directions toward or away from the geometric center of a particular component, respectively.

[0035] Reference Figure 1-5 As 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 the 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 the 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;

[0036] In 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;

[0037] In the multi-wing stabilization mode, the upper boom assembly 2 and the lower boom assembly 5 are separated in the vertical direction, and the upper power assembly 3 and the lower power assembly 6 are separated in the vertical direction.

[0038] The drone is divided into an upper frame 1 and a lower frame 4, which can be connected by a rotating shaft and other components, allowing the upper frame 1 and the lower frame 4 to rotate relative to each other in the horizontal plane. The upper frame 1 extends outward through the upper cantilever assembly 2, and the upper power assembly 3 is installed at the end. The lower frame 4 is installed in a symmetrical or staggered manner through the lower cantilever assembly 5, and the lower power assembly 6 is also installed at the end. The upper power assembly 3 and the lower power assembly 6 can achieve synchronous adjustment of parameters such as speed and inclination through the flight control system.

[0039] In high-power mode, the upper boom assembly 2 and the lower boom assembly 5 are rotated and adjusted by the upper frame 1 and the lower frame 4 until they completely overlap in the vertical direction. This allows the air flow directions of the upper power assembly 3 and the lower power assembly 6 to be coaxially aligned, generating superimposed lift. This is suitable for situations requiring large payloads (such as delivering relief supplies) or high-speed flight (such as quickly reaching a disaster area). By superimposing power, the load on a single motor set is reduced, the power system life is extended, and the risk of overheating in high-temperature environments is avoided.

[0040] 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 until they are staggered in the vertical direction. In this way, 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, thereby improving safety redundancy;

[0041] The present invention achieves flexible switching between two different operating modes through a unique upper and lower split structural design, combined with the dynamic adjustment capabilities of the rotatable frame and power assembly. The mode can be switched with one click through the flight control system without the need to disassemble or replace components, and its shape can be changed according to actual needs, thereby improving the purpose of scene adaptability.

[0042] Furthermore, the lower frame 4 includes a plug-in column 41 and a plug-in piece 42, and the upper frame 1 includes a plug-in slot 11 and a contact piece 12. The plug-in piece 42 is fixedly connected to the plug-in piece 42, and the contact piece 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 piece 12 is used to contact the plug-in piece 42.

[0043] 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;

[0044] In the separation mode, the plug post 41 is separated from the plug slot 11 , and the abutment piece 12 is separated from the plug piece 42 .

[0045] 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 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 torsional and shear-resistant structure. In the separation mode, an axial pull-out design is adopted to separate the lower frame 4 part and the upper frame 1 part by rotating to form two independent UAV structures.

[0046] Furthermore, the lower frame 4 also includes a main motor 43 and a rotating resistance member 44, and 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 disposed 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. The main motor 43 is connected to the rotating resistance member 44;

[0047] When the rotating abutment member 44 abuts against the abutment post 15 and rotates, the lower frame 4 and the upper frame 1 rotate relative to each other, and the abutment piece 12 is separated from the plug-in piece 42;

[0048] When the rotating resisting member 44 rotates to the through hole 16 , the plug-in post 41 is separated from the plug-in slot 11 , and the lower frame 4 is separated from the upper frame 1 .

[0049] Multi-mode rapid switching can be achieved through the mechanical plug-in and rotation 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 piece 42 and the abutment piece form an anti-torsion and anti-shear unit to realize whether the lower frame 4 and the upper frame 1 are separated.

[0050] 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 .

[0051] Furthermore, the lower power assembly 6 includes a lower power motor 61 and a lower power blade 62 . The lower power motor 61 is connected to the lower power blade 62 and is used to drive the lower power blade 62 . The lower power blade 62 is slidably connected to the lower annular track 52 .

[0052] The lower cantilever shell 51 serves as the core supporting structure to fix other components. The lower annular track 52 is fixed on the cantilever shell to provide a precise annular motion path for the lower power component 6. The lower power motor 61 serves as the power source to drive the blade movement. The lower power blade 62 dynamically cooperates with the lower annular track 52 to achieve controllable motion. Usually, the center of the lower power blade 62 is connected to the lower power motor 61, and the end of the blade is slidably connected to the lower annular track 52, and slides in a circle along the lower annular track 52 to form a continuous annular motion trajectory. The lower annular track 52 constrains the path of the lower power blade 62 to ensure motion accuracy.

[0053] Furthermore, 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 on the annular duct 22 . The annular duct 22 is used to guide the airflow to spray downward.

[0054] Furthermore, the upper power assembly 3 includes a guide plate 31, a turbine motor 32 and a turbofan 33. The guide plate 31, the turbine motor 32 and the turbofan 33 are all installed in the upper cantilever shell 21. The turbine motor 32 is connected to the turbofan 33. The guide plate 31 is used to guide the airflow to the annular duct 22.

[0055] The bladeless power structure is a new technology, the main purpose of which is to avoid airflow conflict between the upper power assembly 3 and the lower power assembly 6. For the specific principle, please refer to patent CN201920230903.7.

[0056] Further, such as Figure 6 As shown, as a 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 , and the upper power assembly 3 is installed on the upper annular track 23 .

[0057] Furthermore, the upper power assembly 3 includes an upper power motor 34 and an upper power blade 35 . The upper power motor 34 is connected to the upper power blade 35 and is used to drive the upper power blade 35 . The upper power blade 35 is slidably connected to the upper annular track 23 .

[0058] In the second embodiment, the upper power assembly 3 also adopts a leaf structure, and the structural principle of the cooperation between the upper cantilever assembly 2 and the upper power assembly 3 is the same as the structural principle of the cooperation between the lower cantilever assembly 5 and the lower power assembly 6.

[0059] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiment. All technical solutions based on the concept of the present invention are within the scope of protection of the present invention. It should be noted that for those skilled in the art, various improvements and modifications that do not depart from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. Split-type disaster relief drone, characterized by: It includes 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 high-power mode, the upper cantilever assembly and the lower cantilever assembly overlap in the vertical direction, and the upper power assembly and the lower power assembly overlap in the vertical direction; In the multi-wing stabilization mode, the upper boom assembly and the lower boom assembly are separated in the vertical direction, and the upper power assembly and the lower power assembly are separated in the vertical direction.

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

3. The split-type disaster relief drone according to claim 2, characterized in that: The lower frame further includes a main motor and a rotating resistance member, and the upper frame further includes a receiving groove, a blocking plate and a resistance column, wherein 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 member abuts against the abutment column and rotates, the lower frame and the upper frame rotate relative to each other, and the abutment piece and the plug-in piece are separated; When the rotating resistance 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 drone according to any one of claims 1 to 3, characterized in that: 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.

5. The split-type disaster relief drone 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-type disaster relief drone according to any one of claims 1 to 3, characterized in that: The upper cantilever assembly includes an upper cantilever shell and an annular duct, the annular duct is fixedly connected to the upper cantilever shell, 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 drone according to claim 6, characterized in that: The upper power assembly includes a guide plate, a turbine motor and a turbofan. The guide plate, the turbine motor and the turbofan are all installed in the upper cantilever shell. The turbine motor is connected to the turbofan. The guide plate is used to guide the airflow to the annular duct.

8. The split-type disaster relief drone according to any one of claims 1 to 3, characterized in that: 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.

9. The split-type disaster relief drone according to claim 8, characterized in that: 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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