Buffering type undercarriage of heavy unmanned aerial vehicle

Abstract

The utility model discloses a heavy unmanned aerial vehicle buffer type undercarriage, which relates to the technical field of unmanned aerial vehicles, and comprises a mounting frame, two sides of the mounting frame are provided with supporting mechanisms, each supporting mechanism comprises two hydraulic buffers, two supporting rods and a supporting plate, the hydraulic buffers are provided with electromagnetic valves, and the electromagnetic valves are connected with the supporting plates. A pressure sensor is installed in an inner cavity of the hydraulic buffer, a displacement sensor is installed on a piston rod of the hydraulic buffer, one end of the hydraulic buffer is installed on a supporting rod, and one end of the supporting rod is connected with the supporting plate. Side rods are mounted on the two supporting rods through adjusting mechanisms; a supporting assembly is arranged on the supporting plate; the electromagnetic valve, the pressure sensor and the displacement sensor are arranged on the hydraulic buffer, a real-time sensing and dynamic adjusting closed-loop buffer system is constructed, and the supporting mechanisms on the two sides have the flexible adjusting capacity by arranging the side rods with the adjusting mechanisms and the independent buffer assemblies.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a buffer-type landing gear for a heavy-duty UAV. Background Art

[0002] With the rapid development of aviation technology, heavy-lift drones are increasingly being used in logistics, emergency rescue, geological exploration, and other fields. These drones typically have a high takeoff weight (often over 500kg) and often need to take off and land on unpaved surfaces (such as grasslands, mountains, and temporary runways). This places extremely high demands on the landing gear's cushioning performance, structural strength, and terrain adaptability.

[0003] The existing buffer-type landing gear of heavy-duty UAVs mostly adopts traditional passive buffer structures, such as a single spring and damping combination or a hydraulic buffer with fixed parameters. This type of structure has obvious limitations: the buffer parameters are fixed and cannot be dynamically adjusted according to the actual landing scenario (such as heavy load / light load, flat / inclined ground). In the event of an emergency landing or uneven ground, the fuselage may be easily overloaded due to insufficient buffering, or the fuselage may be caused to bounce due to excessive buffering, increasing the risk of equipment damage. In addition, the landing gear support structure is mostly rigidly connected, and the support components on both sides lack the ability to independently adjust. When facing inclined ground or local protrusions, it is easy to cause unilateral overload due to uneven force, causing the fuselage to tilt or even roll over. Therefore, those skilled in the art provide a buffer-type landing gear for heavy-duty UAVs to solve the problems raised in the above background technology. Utility Model Content

[0004] The purpose of the present invention is to provide a buffer-type landing gear for a heavy-duty UAV to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] A heavy-duty UAV cushion-type landing gear, comprising:

[0007] A mounting frame, wherein support mechanisms are provided on both sides of the mounting frame, wherein the support mechanisms include two hydraulic buffers, two support rods and a support plate, wherein an electromagnetic valve is installed on the hydraulic buffer, a pressure sensor is installed in the inner cavity of the hydraulic buffer, and a displacement sensor is installed on the piston rod of the hydraulic buffer, wherein one end of the hydraulic buffer is installed on the support rod, and one end of the support rod is connected to the support plate;

[0008] Side rods are installed on the two support rods through an adjustment mechanism;

[0009] A supporting assembly is provided on the supporting plate.

[0010] Preferably, a connecting block is installed at one end of the hydraulic buffer away from the support rod, and a MEMS three-axis acceleration sensor is installed between the connecting block and the mounting frame.

[0011] Preferably, the adjusting mechanism includes an electric push rod, two rotating blocks and a slider, one end of the side rod is rotatably connected to the support rod, and a rotating groove is provided on the support rod. Among the two rotating blocks, one rotating block is connected to the fixed end of the electric push rod, and the other rotating block is connected to the output end of the electric push rod, wherein the rotating block connected to the fixed end of the electric push rod is rotatably connected in the rotating groove, and the rotating block connected to the output end of the electric push rod is rotatably connected to the slider, a sliding groove is provided on the side rod, and the slider is slidably connected in the sliding groove.

[0012] Preferably, a first abutment plate is provided at one end of the side rod away from the support rod, and a first rubber layer is provided on the first abutment plate.

[0013] Preferably, the support assembly includes a titanium alloy honeycomb sheet, a second abutment plate and a second rubber layer, the titanium alloy honeycomb sheet is installed between the second abutment plate and the support plate, and the second rubber layer is connected to the second abutment plate.

[0014] Preferably, the titanium alloy honeycomb sheet is filled with silica gel, and the first rubber layer and the second rubber layer are provided with a plurality of anti-slip grooves.

[0015] Preferably, a PLC controller is installed on the installation frame, and the PLC controller is electrically connected to the pressure sensor, the displacement sensor, the MEMS three-axis acceleration sensor and the electric push rod respectively.

[0016] Compared with the prior art, the beneficial effects of the present invention are:

[0017] This utility model establishes a closed-loop buffering system with real-time sensing and dynamic adjustment by installing electromagnetic valves, pressure sensors, and displacement sensors on the hydraulic buffer. The pressure sensor monitors load changes during the buffering process in real time, and the displacement sensor accurately captures buffering stroke data. The flight control system uses this information to dynamically adjust the damping parameters of the hydraulic buffer via the electromagnetic valve, enabling the landing gear to adaptively adjust its buffering effect based on landing scenarios (such as heavy / light loads and changes in impact intensity). This effectively solves the problem of insufficient or excessive buffering caused by fixed buffering parameters in traditional landing gear, significantly improving landing safety under complex operating conditions.

[0018] This new design incorporates sidebars with adjustment mechanisms and independent buffer assemblies, enabling flexible adjustment of the support mechanisms on both sides. The adjustment mechanisms adjust the support angles and spacing of the sidebars, and in conjunction with the independently functioning buffer assemblies, they adapt to sloped or partially uneven terrain. This avoids the unilateral overload issues associated with traditional rigid connection structures due to uneven force distribution, reduces the risk of fuselage tilt or even rollover, and enhances the landing gear's adaptability to complex terrain. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the main structure of a buffer-type landing gear for a heavy-duty UAV in an embodiment of the present application;

[0020] Figure 2 This is a schematic cross-sectional view of a buffer-type landing gear for a heavy-duty UAV according to an embodiment of the present application;

[0021] Figure 3 for Figure 2 Enlarged view of point A in the middle.

[0022] In the figure: 1. Mounting frame; 2. Support rod; 3. Support plate; 4. Hydraulic buffer; 5. Solenoid valve; 6. Pressure sensor; 7. Displacement sensor; 8. Side rod; 9. Connecting block; 10. MEMS three-axis acceleration sensor; 11. Electric push rod; 12. Rotating block; 13. Slider; 14. Rotating groove; 15. Sliding groove; 16. First abutment plate; 17. First rubber layer; 18. Titanium alloy honeycomb sheet; 19. Second abutment plate; 20. Second rubber layer; 21. Anti-slip groove; 22. PLC controller. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0024] See also Figure 1-Figure 3 , the utility model provides a technical solution:

[0025] A heavy-duty UAV cushion-type landing gear, comprising:

[0026] An installation frame 1 is provided with support mechanisms on both sides of the installation frame 1. The support mechanisms include two hydraulic buffers 4, two support rods 2 and a support plate 3. An electromagnetic valve 5 is installed on the hydraulic buffer 4. A pressure sensor 6 is installed in the inner cavity of the hydraulic buffer 4, and a displacement sensor 7 is installed on the piston rod of the hydraulic buffer 4. One end of the hydraulic buffer 4 is installed on the support rod 2, and one end of the support rod 2 is connected to the support plate 3. A connecting block 9 is installed on the end of the hydraulic buffer 4 away from the support rod 2, and a MEMS triaxial acceleration sensor 10 is installed between the connecting block 9 and the installation frame 1;

[0027] Mounting frame 1 is connected to the heavy-duty drone. Before takeoff, the operator, through the ground control system, presets various landing scenario parameters (such as conventional landing and heavy-load landing) in the PLC controller 22 on mounting frame 1. This provides a basis for subsequent takeoff and landing adjustments. When the drone approaches the landing point, PLC controller 22 automatically activates all sensing components, including pressure sensor 6, displacement sensor 7, and MEMS triaxial accelerometer 10, to enter real-time monitoring mode.

[0028] Based on the real-time data collected, the PLC controller 22, as the core control unit, immediately starts the dynamic adjustment mechanism: for the hydraulic buffer 4, the controller accurately controls the opening of the electromagnetic valve 5 according to the calculation results, and adjusts the damping coefficient in real time by changing the oil circulation speed, so that the buffering effect can flexibly adapt to different impact intensities.

[0029] The two support rods 2 are equipped with side rods 8 through an adjusting mechanism. The adjusting mechanism includes an electric push rod 11, two rotating blocks 12 and a slider 13. One end of the side rod 8 is rotatably connected to the support rod 2. A rotating groove 14 is provided on the support rod 2. Among the two rotating blocks 12, one rotating block 12 is connected to the fixed end of the electric push rod 11, and the other rotating block 12 is connected to the output end of the electric push rod 11. The rotating block 12 connected to the fixed end of the electric push rod 11 is rotatably connected in the rotating groove 14, and the rotating block 12 connected to the output end of the electric push rod 11 is rotatably connected to the slider 13. A sliding groove 15 is provided on the side rod 8, and the slider 13 is slidably connected in the sliding groove 15. A first abutment plate 16 is provided at the end of the side rod 8 away from the support rod 2, and a first rubber layer 17 is provided on the first abutment plate 16;

[0030] To adjust the sidebar 8, the controller instructs the electric push rod 11 to extend and retract, and with the help of the rotating block 12, the slider 13 slides in the sliding groove 15 of the sidebar 8, causing the sidebar 8 to rotate around the connection point with the support rod 2, thereby adjusting the support angle and ensuring that the first abutment plate 16 can closely contact the ground, helping to stabilize the fuselage;

[0031] The angle adjustment function of the side rod 8 and the structural design of the support assembly enable the landing gear to flexibly adapt to tilted and uneven surfaces, avoiding the uneven force problem common in rigid connection structures, significantly reducing the risk of fuselage tilt and rollover, and greatly enhancing terrain adaptability.

[0032] A support assembly is provided on the support plate 3, which includes a titanium alloy honeycomb sheet 18, a second abutment plate 19 and a second rubber layer 20. The titanium alloy honeycomb sheet 18 is installed between the second abutment plate 19 and the support plate 3, and the second rubber layer 20 is connected to the second abutment plate 19. The titanium alloy honeycomb sheet 18 is filled with silicone, and a number of anti-slip grooves 21 are provided on the first rubber layer 17 and the second rubber layer 20.

[0033] As the drone begins to land, the support assembly first contacts the ground. At this point, the second abutment plate 19 is subjected to the ground's reaction force, and the force transmission path extends through the titanium alloy honeycomb sheet 18 to the support plate 3. The titanium alloy honeycomb sheet 18 and the silicone filling inside it immediately take effect, initially absorbing the impact energy through its own structural deformation and material properties, completing the first level of cushioning. Simultaneously, each sensor simultaneously initiates data acquisition: the pressure sensor 6 captures the pressure changes within the hydraulic buffer 4 in real time, accurately determining the magnitude of the impact load; the displacement sensor 7 continuously monitors the piston rod's expansion and contraction, providing real-time information on the dynamics of the cushioning stroke; and the MEMS triaxial accelerometer 10 sensitively captures the acceleration changes and attitude deviations of the aircraft. This critical data is rapidly transmitted to the PLC controller 22 for comprehensive analysis and processing.

[0034] Furthermore, the anti-skid grooves 21 on the first and second rubber layers 17, 20 significantly increase friction with the ground, effectively preventing slipping during landing. After landing, all components automatically reset under the control of the PLC controller 22, ready for the next operation.

[0035] Dynamic damping adjustment is achieved through the cooperation of the hydraulic buffer 4 and the electromagnetic valve 5. Combined with the initial buffering of the titanium alloy honeycomb sheet 18 and silicone, a multi-level adaptive buffering mechanism is formed, which completely solves the problem of insufficient or excessive buffering caused by the fixed buffering parameters of traditional landing gear, and greatly improves the ability to cope with different impact intensities.

[0036] In the above embodiment, a PLC controller 22 is installed on the mounting frame 1 , and the PLC controller 22 is electrically connected to the pressure sensor 6 , the displacement sensor 7 , the MEMS triaxial acceleration sensor 10 and the electric push rod 11 .

[0037] It should be noted that the specific models and specifications of the PLC controller 22, pressure sensor 6, displacement sensor 7, MEMS three-axis acceleration sensor 10 and electric push rod 11 need to be selected and determined based on the actual specifications of the device. The specific selection calculation method adopts the existing technology in this field, so it will not be described in detail.

[0038] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A heavy-duty UAV cushioned landing gear, characterized in that: include: A mounting frame (1), wherein support mechanisms are provided on both sides of the mounting frame (1), wherein the support mechanisms include two hydraulic buffers (4), two support rods (2) and a support plate (3), wherein an electromagnetic valve (5) is installed on the hydraulic buffer (4), a pressure sensor (6) is installed in the inner cavity of the hydraulic buffer (4), and a displacement sensor (7) is installed on the piston rod of the hydraulic buffer (4), wherein one end of the hydraulic buffer (4) is installed on the support rod (2), and one end of the support rod (2) is connected to the support plate (3); Side rods (8) are installed on the two support rods (2) through an adjustment mechanism; A support assembly is provided on the support plate (3).

2. The heavy-duty UAV cushioned landing gear according to claim 1, characterized in that: A connecting block (9) is installed at one end of the hydraulic buffer (4) away from the support rod (2), and a MEMS three-axis acceleration sensor (10) is installed between the connecting block (9) and the installation frame (1).

3. The heavy-duty UAV cushioned landing gear according to claim 2, characterized in that: The adjustment mechanism comprises an electric push rod (11), two rotating blocks (12) and a slider (13); one end of the side rod (8) is rotatably connected to the support rod (2); a rotating groove (14) is provided on the support rod (2); of the two rotating blocks (12), one rotating block (12) is connected to the fixed end of the electric push rod (11); and the other rotating block (12) is connected to the output end of the electric push rod (11); the rotating block (12) connected to the fixed end of the electric push rod (11) is rotatably connected in the rotating groove (14); the rotating block (12) connected to the output end of the electric push rod (11) is rotatably connected to the slider (13); a sliding groove (15) is provided on the side rod (8); and the slider (13) is slidably connected in the sliding groove (15).

4. The heavy-duty UAV cushioned landing gear according to claim 1, characterized in that: A first abutment plate (16) is provided at one end of the side rod (8) away from the support rod (2), and a first rubber layer (17) is provided on the first abutment plate (16).

5. The heavy-duty UAV cushioned landing gear according to claim 4, characterized in that: The support assembly comprises a titanium alloy honeycomb sheet (18), a second abutment plate (19) and a second rubber layer (20); the titanium alloy honeycomb sheet (18) is installed between the second abutment plate (19) and the support plate (3); and the second rubber layer (20) is connected to the second abutment plate (19).

6. The heavy-duty UAV cushioned landing gear according to claim 5, characterized in that: The titanium alloy honeycomb sheet (18) is filled with silica gel, and a plurality of anti-slip grooves (21) are provided on the first rubber layer (17) and the second rubber layer (20).

7. The heavy-duty UAV cushioned landing gear according to claim 3, characterized in that: A PLC controller (22) is installed on the installation frame (1), and the PLC controller (22) is electrically connected to the pressure sensor (6), the displacement sensor (7), the MEMS three-axis acceleration sensor (10), and the electric push rod (11).

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