Unmanned aerial vehicle landing gear impact and temperature and humidity comprehensive environmental test bench

Abstract

The utility model discloses a kind of unmanned vehicle landing gear impact and temperature and humidity comprehensive environment test bench, it is related to unmanned vehicle testing technical field, to solve the technical problem of current installation structure inconvenient operation, easily damaged and affect detection efficiency, including test shell, landing gear body, linkage assembly and clamping assembly, the test shell top is erected with hydraulic mechanism, the linkage assembly includes the alignment plate being connected on the upper end of impact detection module, the cross bar being connected two alignment plate both ends, and the counterweight box being fixed at two cross bar middle, the cross bar both ends are equipped with the flat mouth end of bottom plane state, the clamping assembly includes the inner tube slidingly sleeved in the outer end of cross bar, the rotating sleeve in the outer side of inner tube, the fixed ring being fixed on cross bar, and the positioning slot being set in the inner tube. The utility model has the advantages of portable assembly structure, multidirectional location ensures stability.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) testing technology, and more specifically, to a comprehensive environmental test bench for UAV landing gear impact and temperature and humidity. Background Technology

[0002] The landing gear of a drone is a core load-bearing component that ensures the safe takeoff, landing, and ground parking of the drone. Its performance directly affects the drone's flight safety and mission reliability. The drone landing gear impact and temperature / humidity integrated environmental test bench is a device used to test the impact resistance of drone landing gear under different temperature and humidity conditions. By simulating real-world usage scenarios, it can comprehensively evaluate the performance and reliability of the landing gear.

[0003] After production, the landing gear of a drone requires performance testing to ensure its usability. The testing equipment needs to secure the landing gear and then apply an initial impact force via hydraulic components to simulate the impact of a drone landing, thereby testing the landing gear performance. Existing fixed structures often use bolts to maintain connection stability, which is difficult to assemble and disassemble, and the simulated environmental humidity can easily cause corrosion at the bolt connections, affecting stability. Therefore, we propose a comprehensive environmental test bench for drone landing gear impact and temperature / humidity. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the existing technology, adapt to the needs of reality, and provide a comprehensive environmental test bench for UAV landing gear impact and temperature and humidity, so as to solve the technical problems of inconvenient operation and easy damage of the current installation structure, which affects the testing efficiency.

[0005] To solve the above-mentioned technical problems, this utility model provides the following technical solution: a comprehensive environmental test bench for the impact and temperature and humidity of a UAV landing gear, including a test shell, a landing gear body, a linkage assembly, and a clamping assembly. A hydraulic mechanism is mounted on the top of the test shell, and a central control panel is installed in the middle of the test shell. Impact detection modules are provided on both sides of the central control panel. The linkage assembly includes an alignment plate connected to the upper end of the impact detection module, a crossbar connecting the two ends of the two alignment plates, and a counterweight box fixed in the middle of the two crossbars. The two ends of the crossbars are provided with flat ends with a flat bottom. The clamping assembly includes an inner cylinder slidably sleeved on the outer end of the crossbar, a rotating cylinder rotatably sleeved on the outer side of the inner cylinder, a fixing ring sleeved and fixed on the crossbar, and a positioning groove opened inside the inner cylinder. An inclined outer plate is fixed on the outer side of the rotating cylinder, and a mating interface is opened on the outer plate. The mating interface of the outer plate is connected to the landing gear body.

[0006] Preferably, both ends of the crossbar are provided with positioning strips arranged in a circular array, and the positioning strips slide and engage with the positioning grooves. The fixed ring and the rear end of the inner cylinder are elastically connected by a compression spring.

[0007] Preferably, the connecting surfaces of the rotating drum and the inner cylinder are connected by a coil spring, and the rotating drum and the inner cylinder are rotatably connected to the rotor through a notch.

[0008] Preferably, the landing gear body has a latch and a crossbar in the middle of the arc surface, and the latch is located on both sides of the crossbar, and the interface of the outer plate is latched on the upper side of the crossbar.

[0009] Preferably, the flat ends of the crossbar are respectively inserted into the corresponding bayonet, and the inner side of the landing gear body is in contact with the front end of the rotating drum.

[0010] Preferably, the upper and lower surfaces of the alignment plate correspond to the hydraulic mechanism and the impact detection module, respectively.

[0011] Compared with the prior art, the beneficial effects of this utility model are: 1. The landing gear body of this utility model adopts a two-way snap-fit ​​method and is fixed to the crossbar by a clamping assembly. Corresponding landing gear bodies are respectively mounted at both ends of the device to maintain the balance of the device. A counterweight block is added to the counterweight box to simulate the weight of the UAV. The test shell door is closed to maintain a closed state. The hydraulic mechanism is activated to impact the alignment plate. During the impact, the landing gear body descends rapidly. The instantaneous impact speed is detected by the impact detection module. The bottom of the landing gear body hits the bottom of the test shell to simulate the impact effect of UAV landing. A temperature and humidity control module is installed in the test shell to control the temperature and humidity inside the test shell to simulate different working environments. The above structure can effectively detect the working status of the UAV landing gear body and reduce the difficulty of operation.

[0012] 2. When installing the landing gear body, the horizontal bar is inserted into the mating interface, and the landing gear body is pulled outward. At this time, the outer plate simultaneously drives the inner cylinder to slide outward, causing the bayonet and the flat end to misalign. Then, the landing gear body is lifted upward, and the outer plate drives the rotating cylinder to deflect, so that the bayonet and the flat end are in the same plane. The landing gear body is pushed inward so that the flat end is inserted into the bayonet. The landing gear body is released, and the clamping assembly is reset by the compression spring and the coil spring. After the reset is completed, the mating interface and the flat end limit the landing gear body laterally and longitudinally, respectively, to keep it in a fixed state. The above assembly method allows for convenient installation and disassembly, reduces the difficulty of test assembly and disassembly, and improves efficiency. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the main structure of this utility model; Figure 2 This is a schematic diagram of the installation state of this utility model; Figure 3 This is a schematic diagram of the fixed state of this utility model; Figure 4 This is a schematic diagram of the landing gear body of this utility model; Figure 5This is a schematic diagram of the linkage component of this utility model; Figure 6 This is a schematic diagram of the crossbar structure of this utility model; Figure 7 This is a schematic diagram of the clamping component of this utility model; Figure 8 This is a cross-sectional schematic diagram of the clamping component of this utility model.

[0014] The following are the labels in the diagram: 1. Test housing; 101. Hydraulic mechanism; 102. Central control panel; 103. Impact detection module; 2. Landing gear body; 201. Bayonet; 202. Crossbar; 3. Linkage assembly; 301. Crossbar; 302. Counterweight box; 303. Alignment plate; 304. Flat end; 305. Positioning strip; 4. Clamping assembly; 401. Rotary cylinder; 402. Inner cylinder; 403. Outer plate; 404. Interlocking interface; 405. Fixing ring; 406. Compression spring; 407. Positioning groove; 408. Coil spring. Detailed Implementation

[0015] like Figures 1 to 5 As shown, this utility model relates to a comprehensive environmental test bench for the impact and temperature / humidity of a UAV landing gear, including a test shell 1, a landing gear body 2, a linkage assembly 3, and a clamping assembly 4. A hydraulic mechanism 101 is mounted on the top of the test shell 1. A central control panel 102 is installed in the middle of the interior of the test shell 1, and impact detection modules 103 are provided on both sides of the central control panel 102. The linkage assembly 3 includes an alignment plate 303 connected to the upper end of the impact detection module 103, a crossbar 301 connecting the two ends of the two alignment plates 303, and a counterweight box 302 fixed in the middle of the two crossbars 301. The crossbars 301 have flat ends 304 with a flat bottom. Positioning strips 305 are distributed in a circular array at both ends of the crossbars 301, and the positioning strips 305 slide and engage with positioning grooves 407. The fixed ring 405 and the rear end of the inner cylinder 402 are elastically connected by a compression spring 406. The rotating cylinder 401 and The inner cylinder 402 is connected to the connecting surface by a coil spring 408. The rotating cylinder 401 and the inner cylinder 402 are rotatably connected to the rotor through a notch. The landing gear body 2 is fixed to the crossbar 301 by a bidirectional snap-fit ​​method through a clamping assembly 4. The two ends of the device are respectively equipped with corresponding landing gear bodies 2 to maintain the balance of the device. A counterweight is added to the counterweight box 302 to simulate the weight of the UAV. The test shell 1 is closed to keep it in a closed state. The hydraulic mechanism 101 is activated to impact the alignment plate 303. During the impact, the landing gear body 2 descends rapidly. The instantaneous impact speed is detected by the impact detection module 103. The bottom of the landing gear body 2 hits the bottom of the test shell 1 to simulate the impact effect of the UAV landing. A temperature and humidity control module is installed in the test shell 1 to control the temperature and humidity inside the test shell 1 to simulate different working environments. The above structure can effectively detect the working status of the UAV landing gear body 2 and reduce the difficulty of operation.

[0016] like Figures 3 to 8 As shown, this utility model relates to a comprehensive environmental test bench for the impact and temperature / humidity of a UAV landing gear, including a test shell 1, a landing gear body 2, a linkage assembly 3, and a clamping assembly 4. The clamping assembly 4 includes an inner cylinder 402 slidably sleeved on the outer end of a crossbar 301, a rotating cylinder 401 rotatably sleeved on the outer side of the inner cylinder 402, a fixing ring 405 sleeved and fixed on the crossbar 301, and a positioning groove 407 formed inside the inner cylinder 402. An inclined outer plate 403 is fixed to the side, and a mating interface 404 is provided on the outer plate 403. The mating interface 404 of the outer plate 403 is connected to the landing gear body 2. The landing gear body 2 has a latch 201 and a crossbar 202 in the middle of the arc surface, and the latch 201 is located on both sides of the crossbar 202. The mating interface 404 of the outer plate 403 is snapped into the upper side of the crossbar 202. The flat ends 304 at both ends of the crossbar 301 are respectively inserted into the corresponding latch 201. The inner side of the body 2 is in contact with the front end of the rotating drum 401. The upper and lower surfaces of the alignment plate 303 correspond to the hydraulic mechanism 101 and the impact detection module 103, respectively. When installing the landing gear body 2, the crossbar 202 is inserted into the interface 404, and the landing gear body 2 is pulled outward. At this time, the outer plate 403 simultaneously drives the inner drum 402 to slide outward, so that the locking 201 is misaligned with the flat end 304. Then, the landing gear body 2 is lifted upward, and the outer plate 403 drives the rotating drum 401 to deflect. Position the bayonet 201 and the flat end 304 in the same plane, push the landing gear body 2 inward so that the flat end 304 is inserted into the bayonet 201, release the landing gear body 2 and reset the clamping assembly 4 by compressing the spring 406 and the coil spring 408. After the reset is completed, the interface 404 and the flat end 304 are used to limit the landing gear body 2 laterally and longitudinally respectively to keep it in a fixed state. The above assembly method allows for convenient installation and disassembly, reduces the difficulty of test assembly and disassembly, and improves efficiency.

[0017] Working Principle: This embodiment provides a comprehensive environmental test bench for UAV landing gear impact and temperature / humidity. The landing gear body 2 is fixed to the crossbar 301 via a bidirectional snap-fit ​​method using a clamping assembly 4. Corresponding landing gear bodies 2 are mounted at both ends of the device to maintain balance. A counterweight is added to the counterweight box 302 to simulate the weight of the UAV. The test shell 1 is closed to maintain a sealed state. The hydraulic mechanism 101 is activated to impact the alignment plate 303, causing the landing gear body 2 to descend rapidly. The instantaneous impact velocity is detected by the impact detection module 103. The bottom of the landing gear body 2 impacts the bottom of the test shell 1, simulating the impact effect of UAV landing. A temperature and humidity control module is installed inside the test shell 1 to control the temperature inside the test shell 1. To simulate different working environments with varying humidity levels, when installing the landing gear body 2, the crossbar 202 is inserted into the interface 404, and the landing gear body 2 is pulled outward. At this time, the outer plate 403 simultaneously drives the inner cylinder 402 to slide outward, causing the bayonet 201 to be misaligned with the flat end 304. Then, the landing gear body 2 is lifted upward, and the outer plate 403 drives the rotating cylinder 401 to deflect, so that the bayonet 201 and the flat end 304 are in the same plane. The landing gear body 2 is pushed inward so that the flat end 304 is inserted into the bayonet 201. The landing gear body 2 is released, and the clamping assembly 4 is reset by the compression spring 406 and the coil spring 408. After the reset is completed, the interface 404 and the flat end 304 limit the landing gear body 2 laterally and longitudinally, respectively, to maintain its fixed state.

[0018] The embodiments disclosed herein are preferred embodiments, but are not limited thereto. Those skilled in the art can readily grasp the spirit of this utility model based on the above embodiments and make different extensions and variations. However, as long as they do not depart from the spirit of this utility model, they are all within the protection scope of this utility model.

Claims

1. A comprehensive environmental test bench for unmanned aerial vehicle (UAV) landing gear impact and temperature and humidity, comprising a test shell (1), a landing gear body (2), a linkage assembly (3), and a clamping assembly (4), characterized in that: The test housing (1) is equipped with a hydraulic mechanism (101) on the top. A central control panel (102) is installed in the middle of the test housing (1). Both sides of the central control panel (102) are equipped with impact detection modules (103). The linkage component (3) includes an alignment plate (303) connected to the upper end of the impact detection module (103), a crossbar (301) connecting the two ends of the two alignment plates (303), and a counterweight box (302) fixed in the middle of the two crossbars (301). The two ends of the crossbar (301) are provided with flat ends (304) with a bottom flat state. The clamping assembly (4) includes an inner cylinder (402) slidably sleeved on the outer end of the crossbar (301), a rotating cylinder (401) rotatably sleeved on the outer side of the inner cylinder (402), a fixing ring (405) sleeved and fixed on the crossbar (301), and a positioning groove (407) opened inside the inner cylinder (402). An inclined outer plate (403) is fixed on the outer side of the rotating cylinder (401), and a docking interface (404) is opened on the outer plate (403). The docking interface (404) of the outer plate (403) is connected to the landing gear body (2).

2. The UAV landing gear impact and temperature / humidity integrated environmental test bench according to claim 1, characterized in that: The crossbar (301) has positioning strips (305) arranged in a ring array at both ends, and the positioning strips (305) slide to engage with the positioning groove (407). The fixed ring (405) and the rear end of the inner cylinder (402) are elastically connected by a compression spring (406).

3. The UAV landing gear impact and temperature / humidity integrated environmental test bench according to claim 2, characterized in that: The connecting surfaces of the rotating drum (401) and the inner drum (402) are connected by a coil spring (408), and the rotating drum (401) and the inner drum (402) are rotatably connected to the rotor through a notch.

4. The UAV landing gear impact and temperature / humidity integrated environmental test bench according to claim 3, characterized in that: The landing gear body (2) has a bayonet (201) and a crossbar (202) in the middle of the arc surface, and the bayonet (201) is located on both sides of the crossbar (202). The interface (404) of the outer plate (403) is snapped onto the upper side of the crossbar (202).

5. The UAV landing gear impact and temperature / humidity integrated environmental test bench according to claim 4, characterized in that: The flat ends (304) at both ends of the crossbar (301) are respectively inserted into the corresponding bayonet (201), and the inner side of the landing gear body (2) is in contact with the front end of the rotating drum (401).

6. The UAV landing gear impact and temperature / humidity integrated environmental test bench according to claim 1, characterized in that: The upper and lower surfaces of the alignment plate (303) correspond to the hydraulic mechanism (101) and the impact detection module (103), respectively.

Images