Undercarriage of bridge detection unmanned aerial vehicle

Abstract

The utility model relates to the technical field of bridge detection, in particular to a bridge detection unmanned aerial vehicle undercarriage which comprises a mounting plate, an inflating mechanism and an adjusting mechanism are arranged on the surface of the mounting plate, a supporting mechanism is arranged at the bottom of the mounting plate, and a controller is fixed to the left side of the surface of the mounting plate; the inflation mechanism comprises a honeycomb damping steel sheet, the bottom of the honeycomb damping steel sheet is fixedly connected with the top of the mounting plate, a high-elasticity silica gel air bag is fixed to the top of the honeycomb damping steel sheet, a wear-resistant anti-skid coating is arranged on the top of the high-elasticity silica gel air bag, and an air pressure sensor is fixed to the inner wall of the high-elasticity silica gel air bag. A two-way air pump is fixed to the right side of the surface of the mounting plate, and the surface of the two-way air pump communicates with an air supply hose and an air exhaust hose. According to the unmanned aerial vehicle undercarriage for bridge detection, through the composite buffering design of the honeycomb damping steel sheets and the high-elasticity silica gel air bags, multi-stage impact energy absorption is achieved, and impact damage to a vehicle body during landing of an unmanned aerial vehicle is remarkably reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to bridge detection technical field, concretely is a bridge detection unmanned plane landing gear. BACKGROUND

[0002] Traditional bridge detection method needs to detect personnel to go into bridge space or high altitude operation, and there is higher safety risk. The unmanned plane can be operated remotely, and the detection personnel can complete the detection work on the ground without contacting the high-risk environment, avoiding the risk of accidental injury. The unmanned plane needs to use the unmanned plane landing gear when landing.

[0003] The utility model discloses a kind of unmanned plane landing gears for bridge detection, including landing gear and recess, recess is fixedly arranged above landing gear, spring hinge is fixedly arranged at the bottom of landing gear, support is fixedly arranged at the bottom of spring hinge, air bag layer is fixedly arranged above recess, leather layer is closely attached to the upper surface of air bag layer, extrusion inflatable ball is fixedly arranged on the left side of air bag layer. The unmanned plane landing gear for bridge detection can provide a stable landing environment during the process of unmanned plane landing, reduce the damage to itself when unmanned plane lands, and can be folded and retracted, can be disassembled when not in use, conveniently move and assemble the unmanned plane landing gear.

[0004] However, the above-mentioned device is low in manual inflation efficiency by extruding inflatable ball, and the inflation amount is difficult to accurately control in emergency. At the same time, the size of the recess is fixed, which cannot adapt to different models of unmanned plane, limiting the application scene. UTILITY MODEL CONTENT

[0005] In order to make up for the shortcomings of the prior art, the utility model provides an unmanned plane landing gear for bridge detection to solve the problem that the air bag of the existing device needs to be inflated manually, which is low in efficiency and the size of the recess is fixed, poor in adaptability.

[0006] The technical scheme adopted by the utility model to solve its technical problems is:

[0007] An unmanned plane landing gear for bridge detection, comprising a mounting plate, the mounting plate surface is provided with an inflation mechanism and an adjusting mechanism, the mounting plate bottom is provided with a supporting mechanism, the mounting plate surface left side is fixed with a controller;

[0008] The inflation mechanism includes honeycomb shock steel sheets, the bottom of the honeycomb shock steel sheets is fixedly connected with the top of the mounting plate, high-elasticity silica gel air bags are fixedly connected with the top of the honeycomb shock steel sheets, wear-resistant and anti-skid coating is arranged on the top of the high-elasticity silica gel air bags, air pressure sensors are fixedly connected with the inner wall of the high-elasticity silica gel air bags, a two-way air pump is fixedly connected with the surface of the right side of the mounting plate, a gas feeding hose and a gas exhausting hose are communicated with the surface of the two-way air pump, two electromagnetic valves are communicated with the surface of the right side of the high-elasticity silica gel air bags, and the gas feeding hose and the gas exhausting hose are communicated with the electromagnetic valves.

[0009] Preferably, the adjusting mechanism comprises two mounting shells, the mounting shells are oppositely arranged and fixed to the top of the mounting plate, a servo motor is fixed to the surface of the mounting shell, the output shaft of the servo motor penetrates through the mounting shell and is fixed with a two-way screw rod, one end of the two-way screw rod is rotatably connected with the inner wall of the mounting shell, two screw sleeves are threadedly connected with the surface of the two-way screw rod, shielding guards are fixed to the surface of the screw sleeves, and a bearing groove is formed between the two shielding guards.

[0010] Preferably, a sliding rail is fixed to the top of the mounting plate, a sliding block is slidably connected with the surface of the sliding rail, and the top of the sliding block is fixedly connected with the bottom of the shielding guard.

[0011] Preferably, two magnets are fixedly arranged on the surface of the shielding guard, a top guard is magnetically attracted to the surface of the magnet, and a baffle is fixed to the surface of the shielding guard.

[0012] Preferably, the supporting mechanism comprises four L-shaped blocks, the L-shaped blocks are fixedly connected with the surface of the mounting plate, movable rods are rotatably connected with the surfaces of the L-shaped blocks on the front and back sides, and two supporting legs are fixed to the surface of the movable rod.

[0013] Preferably, two perforations are formed in the surface of the L-shaped block, a pin rod is slidably connected with the surface of the lower perforation, a pin hole through which the pin rod passes is formed in the surface of the supporting leg, the surface of the pin rod is provided with threads, and a wing nut is threadedly connected with the surface of the pin rod.

[0014] Preferably, a pressure relief valve is communicated with the top of the high-elasticity silica gel air bag.

[0015] Compared with the prior art, the bridge detection unmanned aerial vehicle landing gear has the following beneficial effects:

[0016] First, the inflation mechanism realizes multi-stage impact energy absorption through the composite buffer design of the honeycomb shock-absorbing steel sheet and the high-elasticity silica gel air bag, significantly reduces the impact damage of the unmanned aerial vehicle body during landing, and the closed-loop control of the air pressure sensor and the two-way air pump ensures that the high-elasticity silica gel air bag pressure dynamically adapts to different landing conditions, avoids buffer failure caused by insufficient inflation, and prevents structural deformation caused by over inflation, The mechanism improves the adaptability of the landing gear to complex environments through pressure management and multi-material collaborative buffer of the high-elasticity silica gel air bag, and prolongs the service life of the unmanned aerial vehicle.

[0017] Second, the adjusting mechanism adopts a transmission of a servo motor driving a two-way screw rod to realize the adjustment of the size of the bearing groove, adapt to the landing needs of various models of unmanned aerial vehicles, and the linear guide design of the slide rail and the slide block ensures smooth movement of the shielding baffle, avoids jamming or deviation, and the combination of the magnetic top baffle and the baffle considers the rapid protection effect, The mechanism can adjust the capacity of the bearing groove according to the detection task requirements, and can be operated without tools, which greatly enhances the task adaptability of the unmanned aerial vehicle in bridge detection and reduces the risk of operation interruption caused by equipment mismatch. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is a three-dimensional structure schematic diagram of the utility model;

[0019] Figure 2 It is a sectional three-dimensional structure schematic diagram of the utility model;

[0020] Figure 3 It is a sectional structure schematic diagram of the inflation mechanism in the utility model;

[0021] Figure 4 It is a sectional structure schematic diagram of the adjusting mechanism in the utility model;

[0022] Figure 5 It is a structure schematic diagram of the supporting mechanism in the utility model.

[0023] Among them: 1, mounting plate; 2, inflation mechanism; 201, honeycomb shock-absorbing steel sheet; 202, high-elasticity silica gel air bag; 203, wear-resistant and anti-skid coating; 204, air pressure sensor; 205, two-way air pump; 206, air hose; 207, air hose; 208, electromagnetic valve; 209, pressure relief valve; 3, adjusting mechanism; 301, mounting shell; 302, servo motor; 303, two-way screw rod; 304, screw sleeve; 305, shielding baffle; 306, bearing groove; 307, slide rail; 308, slide block; 309, magnet; 310, top baffle; 311, baffle; 4, supporting mechanism; 401, L-shaped block; 402, movable rod; 403, supporting leg; 404, pin rod; 405, butterfly nut; 5, controller. DETAILED DESCRIPTION

[0024] The utility model discloses a bridge detection unmanned plane landing gear will be described in further detail below with the specific embodiments of the utility model.

[0025] The specific embodiment of this embodiment of a bridge detection unmanned plane landing gear, please refer to Figures 1-5 , including installation board 1, installation board 1 surface is provided with inflation mechanism 2 and adjusting mechanism 3, installation board 1 bottom is provided with support mechanism 4, installation board 1 surface left side is fixed with controller 5;

[0026] Inflation mechanism 2 includes honeycomb shock attenuation steel sheet 201, honeycomb shock attenuation steel sheet 201 bottom and installation board 1 top fixed connection, honeycomb shock attenuation steel sheet 201 top is fixed with high elasticity silica gel air bag 202, high elasticity silica gel air bag 202 top is provided with wear-resistant antiskid coating 203, high elasticity silica gel air bag 202 inner wall is fixed with air pressure sensor 204, installation board 1 surface right side is fixed with two-way air pump 205, two-way air pump 205 surface is communicated with gas supply hose 206 and air extraction hose 207, high elasticity silica gel air bag 202 surface right side is communicated with two electromagnetic valves 208, and gas supply hose 206 and air extraction hose 207 are communicated with electromagnetic valve 208.

[0027] Through the above technical scheme, controller 5 can control two-way air pump 205, and high elasticity silica gel air bag 202 is inflated through gas supply hose 206, so that the air bag expands, and high elasticity silica gel air bag 202 can absorb impact force, air pressure sensor 204 monitors the pressure change inside high elasticity silica gel air bag 202 in real time when the unmanned plane lands, to ensure that the pressure of high elasticity silica gel air bag 202 is always within a safe range; controller 5 controls two-way air pump 205 according to the pressure data, and high elasticity silica gel air bag 202 is inflated or air is extracted through air extraction hose 207 through gas supply hose 206, when inflating, the electromagnetic valve 208 connected with gas supply hose 206 opens the gas supply path, and the electromagnetic valve 208 on the surface of air extraction hose 207 is closed, and when exhausting, the reverse operation is performed, this design can prevent airflow backflow, and can effectively avoid the air leakage condition, honeycomb shock attenuation steel sheet 201 is located below high elasticity silica gel air bag 202, and forms a multi-stage buffer system with high elasticity silica gel air bag 202, which absorbs high-frequency impact through the elastic deformation of the honeycomb structure, high elasticity silica gel air bag 202 disperses low-frequency vibration through deformation, wear-resistant antiskid coating 203 increases the friction force with the unmanned plane body to prevent sliding, avoids side slip deviation, and enhances landing stability, which is suitable for uneven landing environment in bridge detection, significantly reduces the damage of landing impact force to the unmanned plane body, through the above design, the problems of low inflation efficiency and single buffering effect in the traditional scheme are solved.

[0028] The adjusting mechanism 3 comprises two mounting shells 301 oppositely arranged and fixed on the top of the mounting plate 1, a servo motor 302 fixed on the surface of the mounting shell 301, an output shaft of the servo motor 302 penetrating through the mounting shell 301 and fixed with a bidirectional screw rod 303, one end of the bidirectional screw rod 303 being rotatably connected with the inner wall of the mounting shell 301, two screw sleeves 304 being threadedly connected with the surface of the bidirectional screw rod 303, shielding baffle plates 305 being fixed on the surface of the screw sleeves 304, and a bearing groove 306 being formed between the two shielding baffle plates 305.

[0029] Through the above technical scheme, the servo motor 302 drives the bidirectional screw rod 303 to rotate, and drives the two screw sleeves 304 to synchronously move along the axial direction of the screw rod, so as to push the shielding baffle plates 305 to expand or shrink the size of the bearing groove 306, thereby adapting to the take-off requirements of different models of unmanned aerial vehicles.

[0030] The top of the mounting plate 1 is fixed with a sliding rail 307, the sliding rail 307 is slidingly connected with a sliding block 308, and the top of the sliding block 308 is fixedly connected with the bottom of the shielding baffle plate 305.

[0031] Through the above technical scheme, when the servo motor 302 drives the bidirectional screw rod 303 to rotate, the screw sleeve 304 drives the shielding baffle plate 305 to move, and the sliding block 308 synchronously translates along the sliding rail 307 following the shielding baffle plate 305, so as to ensure that the shielding baffle plate 305 always moves along a straight line.

[0032] Two magnets 309 are embedded and fixed on the surface of the shielding baffle plate 305, a top baffle plate 310 is magnetically attracted on the surface of the magnet 309, and a baffle plate 311 is fixed on the surface of the shielding baffle plate 305.

[0033] Through the above technical scheme, when the device is not used, the top baffle plate 310 can be installed on the top of the two shielding baffle plates 305 by magnetic attraction, so as to shield the bearing groove 306 and avoid damage to the top of the high-elasticity silica gel air bag 202 due to collision, the baffle plate 311 can limit the left-right position of the top baffle plate 310 to prevent the top baffle plate 310 from sliding, and the design of magnetic attraction enables the top baffle plate 310 to be quickly disassembled and assembled.

[0034] The supporting mechanism 4 comprises four L-shaped blocks 401 fixedly connected with the surface of the mounting plate 1, movable rods 402 rotatably connected with the surfaces of the front and rear L-shaped blocks 401, and two supporting legs 403 fixed on the surface of the movable rod 402.

[0035] Through the above technical scheme, the supporting legs 403 can be unfolded or folded by rotating the movable rod 402, the supporting legs 403 are rotated to the vertical position when unfolded, and the supporting legs 403 are upwardly rotated to be stored when folded, so as to reduce the overall space occupied by the device.

[0036] The L-shaped block 401 is provided with two through holes on the surface, and a pin rod 404 is slidably connected to the lower through hole. The supporting leg 403 is provided with a pin hole through which the pin rod 404 passes. The surface of the pin rod 404 is provided with threads, and the pin rod 404 is threadedly connected with a wing nut 405.

[0037] According to the above technical scheme, after the supporting leg 403 is rotated to the vertical position, the pin rod 404 passes through the lower through hole of the L-shaped block 401 and the pin hole of the supporting leg 403, and the wing nut 405 is screwed onto the threaded end of the pin rod 404. The position of the supporting leg 403 is fixed by friction, preventing the supporting leg 403 from moving. When folding is needed, the wing nut 405 is loosened in the opposite direction, and the pin rod 404 is extracted to release the supporting leg 403. The pin rod 404 is then passed through the upper through hole and the pin hole of the supporting leg 403 to reposition the supporting leg 403.

[0038] The top of the high-elasticity silica gel air bag 202 is connected with a pressure relief valve 209.

[0039] According to the above technical scheme, when the internal pressure of the high-elasticity silica gel air bag 202 exceeds the set threshold, the valve core is pressed and opened, releasing excess gas to the outside. When the pressure returns to a safe value, the valve core automatically resets and seals, preventing the high-elasticity silica gel air bag 202 from overpressurizing and rupturing due to faults in the bidirectional air pump 205 or extreme impact.

[0040] The controller 5 is electrically connected with the servo motor 302, the electromagnetic valve 208, the air pressure sensor 204, and the bidirectional air pump 205.

[0041] The working principle is as follows: when the unmanned aerial vehicle performs a bridge detection task, the supporting leg 403 is first unfolded, and then locked by the pin rod 404 and the wing nut 405 to provide stable support. The controller 5 starts the adjusting mechanism 3 according to the preset program or real-time instructions. The servo motor 302 drives the bidirectional screw rod 303 to rotate, driving the screw sleeve 304 and the shielding cover 305 to slide along the slide rail 307, expanding or contracting the bearing groove 306 to adapt to the size of the unmanned aerial vehicle. The air pressure sensor 204 of the inflation mechanism 2 continuously monitors the internal pressure of the high-elasticity silica gel air bag 202. The controller 5 controls the bidirectional air pump 205 according to the predicted value of the landing impact force during daily use, so that the bidirectional air pump 205 pre-inflates the high-elasticity silica gel air bag 202 through the air supply hose 206, and the high-elasticity silica gel air bag 202 expands to the appropriate pressure. At the moment of landing, the cellular shock-absorbing steel sheet 201 absorbs high-frequency impact through elastic deformation of the cellular structure, and the high-elasticity silica gel air bag 202 disperses low-frequency vibration through deformation. The wear-resistant and anti-skid coating 203 increases the friction force of the contact surface to prevent the aircraft body from sliding, achieving the absorption of impact force when the unmanned aerial vehicle falls. If the pressure of the high-elasticity silica gel air bag 202 exceeds the safety threshold, the pressure relief valve 209 automatically opens to release the gas. After the task is completed, the bidirectional air pump 205 exhausts the air through the air exhaust hose 207, the adjusting mechanism 3 contracts the bearing groove 306, and the supporting leg 403 is folded and stored, minimizing the overall size of the device.

[0042] It should be noted that although the specific embodiments of the present application have been shown and described, it is to be understood that for the purpose of protection of principles and spirits, various changes, modifications, replacements and variations of the specific embodiments can be made by those skilled in the art, and the scope of protection is defined by the appended claims and their equivalents.

Claims

1. A bridge inspection drone landing gear, characterized by: Including the installation plate (1), the installation plate (1) surface is provided with inflation mechanism (2) and adjusting mechanism (3), the installation plate (1) bottom is provided with support mechanism (4), the installation plate (1) surface left side is fixed with controller (5); The inflation mechanism (2) includes honeycomb shock absorbing steel sheet (201), the bottom of the honeycomb shock absorbing steel sheet (201) is fixedly connected with the top of the installation plate (1), the top of the honeycomb shock absorbing steel sheet (201) is fixedly connected with high elasticity silica gel air bag (202), the top of the high elasticity silica gel air bag (202) is provided with wear-resistant antiskid coating (203), the inner wall of the high elasticity silica gel air bag (202) is fixedly connected with air pressure sensor (204), the right side of the installation plate (1) surface is fixedly connected with two-way air pump (205), the surface of the two-way air pump (205) is communicated with air hose (206) and air hose (207), the right side of the surface of the high elasticity silica gel air bag (202) is communicated with two electromagnetic valves (208), the air hose (206) and the air hose (207) are communicated with the electromagnetic valve (208).

2. The bridge detection unmanned aerial vehicle landing gear of claim 1, wherein: The adjusting mechanism (3) includes two installation shells (301), the installation shells (301) are oppositely arranged and fixed to the top of the installation plate (1), the surface of the installation shell (301) is fixedly connected with servo motor (302), the output shaft of the servo motor (302) penetrates the installation shell (301) and is fixedly connected with two-way screw rod (303), one end of the two-way screw rod (303) is rotatably connected with the inner wall of the installation shell (301), the surface of the two-way screw rod (303) is screw-connected with two screw sleeves (304), the surface of the screw sleeve (304) is fixedly connected with shielding baffle (305), the bearing groove (306) is formed between the two shielding baffles (305).

3. The bridge inspection UAV landing gear of claim 2, wherein: The top of the installation plate (1) is fixedly connected with slide rail (307), the surface of the slide rail (307) is slidably connected with sliding block (308), and the top of the sliding block (308) is fixedly connected with the bottom of the shielding baffle (305).

4. The bridge inspection unmanned aerial vehicle landing gear of claim 2, wherein: The surface of the shielding baffle (305) is embeddedly fixedly connected with two magnets (309), the surface of the magnet (309) is magnetically attracted to top baffle (310), and the surface of the shielding baffle (305) is fixedly connected with baffle (311).

5. The bridge inspection drone landing gear of claim 1, wherein: The support mechanism (4) includes four L-shaped blocks (401), the L-shaped blocks (401) are fixedly connected with the surface of the installation plate (1), the front and rear sides of the L-shaped blocks (401) are rotatably connected with movable rods (402), and the surface of the movable rod (402) is fixedly connected with two supporting legs (403).

6. The bridge inspection drone landing gear of claim 5, wherein: Two perforations are formed in the surface of the L-shaped block (401), the lower perforation surface is slidably connected with pin rod (404), the surface of the supporting leg (403) is provided with pin hole through which the pin rod (404) passes, the surface of the pin rod (404) is provided with threads, and the surface of the pin rod (404) is screw-connected with butterfly nut (405).

7. The bridge inspection drone landing gear of claim 1, wherein: The top of the high elasticity silica gel air bag (202) is communicated with pressure relief valve (209).

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