CN113636103B - Unmanned aerial vehicle vibration testing device - Google Patents
Unmanned aerial vehicle vibration testing device Download PDFInfo
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- CN113636103B CN113636103B CN202111199582.7A CN202111199582A CN113636103B CN 113636103 B CN113636103 B CN 113636103B CN 202111199582 A CN202111199582 A CN 202111199582A CN 113636103 B CN113636103 B CN 113636103B
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- 238000012360 testing method Methods 0.000 title claims abstract description 51
- 230000007246 mechanism Effects 0.000 claims abstract description 49
- 230000001105 regulatory effect Effects 0.000 claims description 9
- 230000000694 effects Effects 0.000 abstract description 7
- 238000001514 detection method Methods 0.000 abstract description 2
- 230000036544 posture Effects 0.000 abstract description 2
- 230000002349 favourable effect Effects 0.000 abstract 1
- 230000002457 bidirectional effect Effects 0.000 description 10
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
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- 230000037237 body shape Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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Abstract
The invention discloses an unmanned aerial vehicle vibration testing device, which belongs to the technical field of unmanned aerial vehicle detection equipment and comprises a vibration equipment main body and a vibration test bench, wherein the vibration test bench is arranged at the upper end of the vibration equipment main body, an adjusting module for adjusting the placing angle of an unmanned aerial vehicle is assembled on the vibration test bench, the adjusting module comprises a first adjusting mechanism and a second adjusting mechanism, the first adjusting mechanism is used for adjusting the placing angle of the unmanned aerial vehicle in the vertical direction, the second adjusting mechanism is used for adjusting the placing angle of the unmanned aerial vehicle in the horizontal direction, the placing angle of the unmanned aerial vehicle can be adjusted, the vibration conditions of the unmanned aerial vehicle under different flight postures can be conveniently simulated, and the testing result is more accurate, simultaneously, be convenient for fix the unmanned aerial vehicle of modelling difference, improved unmanned aerial vehicle's fixed effect, improved the suitability of device, be favorable to carrying out the vibration test to unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle detection equipment, in particular to an unmanned aerial vehicle vibration testing device.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Because the environmental condition of unmanned aerial vehicle operation is often changeable and complicated, in order to satisfy more or the operation demand under the specific condition, need carry out multiple performance test to unmanned aerial vehicle, for example: high and low temperature tests, drop tests, GPS satellite search tests, vibration tests, and the like.
The vibration testing device is used for carrying out vibration testing on the unmanned aerial vehicle, because a plurality of sensors are arranged in the unmanned aerial vehicle, if data sensed by the sensors are influenced by vibration, the unmanned aerial vehicle is completely uncontrolled; secondly, the inside hardware structure of unmanned aerial vehicle is complicated, and the integration intensity requirement of fuselage is higher, and if vibration leads to the hardware connection unusual, screw or module laxity etc. all can lead to unmanned aerial vehicle to break down, and simultaneously, the vibration of aircraft self can influence the stability of flight and the effect of taking photo by plane, so the aircraft is not negligible to the ability of resisting of vibration.
However, most of the existing vibration testing devices can only test the unmanned aerial vehicle in the horizontal direction and the vertical direction, and cannot simulate the vibration conditions (such as inclined flight, rotating flight and the like) in different flight attitudes, so that the testing results are not accurate enough, and along with the development of science and technology, the modeling of the unmanned aerial vehicle is different, and when the existing device is used for vibration testing, the unmanned aerial vehicle with different modeling is mostly fixed through an elastic bandage, so that the fixing effect is not good, and the vibration testing is not facilitated.
Disclosure of Invention
Technical problem to be solved
Aiming at the problems in the prior art, the invention aims to provide an unmanned aerial vehicle vibration testing device which can adjust the placing angle of an unmanned aerial vehicle, is convenient for simulating the vibration condition of the unmanned aerial vehicle under different flight postures, enables the testing result to be more accurate, is convenient for fixing the unmanned aerial vehicles with different shapes, improves the fixing effect of the unmanned aerial vehicle, improves the applicability of the device and is beneficial to vibration testing of the unmanned aerial vehicle.
Technical scheme
In order to solve the above problems, the present invention adopts the following technical solutions.
The utility model provides an unmanned aerial vehicle vibration test device, includes vibration equipment main part and vibration test platform, vibration test platform sets up in the upper end of vibration equipment main part, be equipped with the regulation module that is used for adjusting unmanned aerial vehicle and puts the angle on the vibration test platform, it includes first adjustment mechanism and second adjustment mechanism to adjust the module, first adjustment mechanism is used for adjusting the angle of putting of unmanned aerial vehicle vertical direction, second adjustment mechanism is used for adjusting the angle of putting of unmanned aerial vehicle horizontal direction, be equipped with on the first adjustment mechanism and be used for carrying out the centre gripping fixed centre gripping module to the unmanned aerial vehicle of molding difference.
Further, first adjustment mechanism includes first motor, first axle bed, first worm, first turbine and first angle regulating plate, first motor and first axle bed all are fixed in the lower extreme of vibration test platform, first worm is fixed in the output of first motor, just first worm and first axle bed pass through ball bearing and rotate the connection, first turbine meshing is connected in the upper end of first worm, one side of first turbine is fixed with the angle sign, first angle regulating plate welds in one side of first turbine, just first angle regulating plate rotates with the vibration test platform and connects.
Further, second adjustment mechanism includes second motor, second angle modulation board and second pedestal, the second motor is fixed in the lower extreme of first angle modulation board, second angle modulation board is fixed in the output of second motor, the direction spout has been seted up to the inside of second angle modulation board, just second angle modulation board and first angle modulation board rotate to be connected, the second pedestal welds in the upper end of second angle modulation board.
Further, the upper end of first angle regulating plate evenly is provided with a plurality of angle sign lines, the upper end of second angle regulating plate is provided with the instruction arrow point.
Further, the centre gripping module includes two-way threaded rod, two fixture and location knob, two-way threaded rod rotates to be connected in the inside of second axle seat, two external screw thread sections have been seted up in two-way threaded rod's the outside, and two the screw thread opposite direction of external screw thread section, two fixture assembles the outside at two external screw thread sections respectively, the one end of two-way threaded rod is fixed in to the location knob.
Furthermore, the clamping mechanism comprises a lower sliding rod, a clamping base, a central shaft rod, a straight gear, a second turbine, two racks, two clamping side plates, a second worm and a clamping knob, the lower sliding rod is in threaded connection with the outer side of the external thread section, the clamping base is welded at the upper end of the lower sliding rod, the central shaft rod is rotatably connected inside the clamping base, the straight gear and the second turbine are both fixed on the outer side of the central shaft rod, the two racks are respectively meshed and connected with the two sides of the straight gear, and the two clamping side plates are respectively rotatably connected with the upper ends of the two racks;
the second worm is connected to one end of the second worm wheel in a meshed mode, the second worm is rotatably connected with the clamping base, and the clamping knob is fixed to one end, extending out of the clamping base, of the second worm.
Furthermore, the lower end of the lower sliding rod is provided with a sliding block, and the sliding block is connected to the inside of the guide sliding groove in a sliding mode.
Furthermore, two the equal adhesive connection of one end that the centre gripping curb plate is close to each other has the rubber pad.
Furthermore, two spacing logical groove has all been seted up to the inside of rack, the inside of centre gripping base is fixed with a plurality of T shape guide pin poles, and is a plurality of T shape guide pin pole is located the inside in two spacing logical grooves respectively.
The invention has the technical effects that:
according to the invention, through the mutual matching of the first adjusting mechanism and the second adjusting mechanism, the device is convenient for adjusting the placing angle of the unmanned aerial vehicle, is convenient for simulating the vibration conditions of the unmanned aerial vehicle under different flight attitudes, and is more accurate in test result;
according to the device, the second angle adjusting plate, the bidirectional threaded rod and the clamping mechanism are matched with each other, so that the device is convenient for fixing the unmanned aerial vehicles with different shapes, the fixing effect of the unmanned aerial vehicles is improved, the applicability of the device is improved, and the vibration test of the unmanned aerial vehicles is facilitated.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of a first adjustment mechanism and a second adjustment mechanism of the present invention;
FIG. 3 is an enlarged view of a portion of the invention at A in FIG. 2;
FIG. 4 is an exploded view of the first and second adjustment mechanisms of the present invention;
FIG. 5 is a schematic view of a clamping module according to the present invention;
FIG. 6 is a schematic structural view of a clamping mechanism according to the present invention;
FIG. 7 is a structural cross-sectional view of a clamping mechanism of the present invention;
fig. 8 is an exploded view of the structure of the clamping mechanism of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. vibrating the apparatus main body; 2. a vibration test bench; 3. a first adjustment mechanism; 4. a second adjustment mechanism; 5. a clamping module; 6. a first motor; 7. a first shaft seat; 8. a first worm; 9. a first turbine; 10. a first angle adjusting plate; 11. a second motor; 12. a second angle adjusting plate; 13. a second shaft base; 14. a bidirectional threaded rod; 15. a clamping mechanism; 16. a lower sliding rod; 17. clamping the base; 18. a central shaft; 19. a spur gear; 20. a second turbine; 21. a rack; 22. clamping the side plate; 23. a second worm; 24. a clamping knob; 25. a T-shaped guide pin.
Detailed Description
In order that the objects and advantages of the invention will be more clearly understood, the following description is given in conjunction with the accompanying examples. It is to be understood that the following text is merely illustrative of one or more specific embodiments of the invention and does not strictly limit the scope of the invention as specifically claimed.
As shown in fig. 1, an unmanned aerial vehicle vibration testing device comprises a vibration equipment main body 1 and a vibration test bench 2, wherein the vibration test bench 2 is arranged at the upper end of the vibration equipment main body 1, an adjusting module for adjusting the placing angle of an unmanned aerial vehicle is assembled on the vibration test bench 2, the adjusting module comprises a first adjusting mechanism 3 and a second adjusting mechanism 4, the first adjusting mechanism 3 is used for adjusting the placing angle of the unmanned aerial vehicle in the vertical direction, the second adjusting mechanism 4 is used for adjusting the placing angle of the unmanned aerial vehicle in the horizontal direction, and a clamping module 5 for clamping and fixing unmanned aerial vehicles with different shapes is assembled on the first adjusting mechanism 3;
referring to fig. 2-4, the first adjusting mechanism 3 includes a first motor 6, a first shaft seat 7, a first worm 8, a first worm wheel 9 and a first angle adjusting plate 10, the first motor 6 and the first shaft seat 7 are both fixed at the lower end of the vibration test table 2, the first worm 8 is fixed at the output end of the first motor 6, the first worm 8 and the first shaft seat 7 are rotatably connected through a ball bearing, the first worm wheel 9 is engaged with the upper end of the first worm 8, an angle indicator is fixed at one side of the first worm wheel 9, the first angle adjusting plate 10 is welded at one side of the first worm wheel 9, and the first angle adjusting plate 10 is rotatably connected with the vibration test table 2;
start first motor 6 for first motor 6 drives first worm 8 and rotates, connects through the meshing of first worm 8 and first turbine 9, makes first worm 8 drive first turbine 9 and rotates, through the fixed connection of first turbine 9 and first angle regulating plate 10, makes first turbine 9 drive first angle regulating plate 10 and rotates, and then drives unmanned aerial vehicle and carries out first angle adjustment of putting
The second adjusting mechanism 4 comprises a second motor 11, a second angle adjusting plate 12 and a second shaft seat 13, the second motor 11 is fixed at the lower end of the first angle adjusting plate 10, the second angle adjusting plate 12 is fixed at the output end of the second motor 11, a guide chute is formed in the second angle adjusting plate 12, the second angle adjusting plate 12 is rotatably connected with the first angle adjusting plate 10, and the second shaft seat 13 is welded at the upper end of the second angle adjusting plate 12;
starting the second motor 11, so that the second motor 11 drives the second angle adjusting plate 12 to rotate, and further drives the unmanned aerial vehicle to perform second placing angle adjustment;
referring to fig. 3, a plurality of angle identification lines are uniformly arranged at the upper end of the first angle adjusting plate 10, and an indication arrow is arranged at the upper end of the second angle adjusting plate 12, so that the placing angle of the unmanned aerial vehicle can be accurately adjusted;
referring to fig. 4-5, the clamping module 5 includes a bidirectional threaded rod 14, two clamping mechanisms 15 and a positioning knob, the bidirectional threaded rod 14 is rotatably connected to the inside of the second shaft seat 13, two external thread sections are provided on the outer side of the bidirectional threaded rod 14, the thread directions of the two external thread sections are opposite, the two clamping mechanisms 15 are respectively mounted on the outer sides of the two external thread sections, and the positioning knob is fixed to one end of the bidirectional threaded rod 14;
the positioning knob is rotated, the bidirectional threaded rod 14 is rotated through the fixed connection of the positioning knob and the bidirectional threaded rod 14, the two clamping mechanisms 15 are driven to move, and the distance between the two clamping mechanisms 15 is adjusted according to the length of the unmanned aerial vehicle body;
as shown in fig. 5-8, the clamping mechanism 15 includes a lower sliding rod 16, a clamping base 17, a central shaft 18, a spur gear 19, a second worm gear 20, two racks 21, two clamping side plates 22, a second worm 23, and a clamping knob 24, the lower sliding rod 16 is screwed to the outer side of the external thread section, the clamping base 17 is welded to the upper end of the lower sliding rod 16, the central shaft 18 is rotatably connected to the inside of the clamping base 17, the spur gear 19 and the second worm gear 20 are both fixed to the outer side of the central shaft 18, the two racks 21 are respectively engaged with the two sides of the spur gear 19, and the two clamping side plates 22 are respectively rotatably connected to the upper ends of the two racks 21;
the second worm 23 is meshed and connected with one end of the second worm wheel 20, the second worm 23 is rotatably connected with the clamping base 17, and the clamping knob 24 is fixed at one end of the second worm 23 extending out of the clamping base 17;
the clamping knob 24 is rotated, the clamping knob 24 drives the second worm 23 to rotate, the second worm 23 is connected with the second worm wheel 20 in a meshed mode, the second worm wheel 20 is driven to rotate by the second worm 23, the central shaft rod 18 and the straight gear 19 are further driven to rotate, the straight gear 19 is connected with the rack 21 in a meshed mode, the rack 21 is driven to move by the straight gear 19, the distance between the clamping side plates 22 located on two sides of the same clamping base 17 is further adjusted, after the clamping side plates 22 are in contact with the unmanned aerial vehicle body, the clamping side plates 22 are connected with the rack 21 in a rotating mode, the clamping side plates 22 can rotate according to the unmanned aerial vehicle body model, the clamping side plates 22 are attached to the unmanned aerial vehicle body, and the unmanned aerial vehicle body is clamped through the matching of the two clamping side plates 22;
the lower end of the lower sliding rod 16 is provided with a sliding block which is connected inside the guide sliding chute in a sliding manner, so that the lower sliding rod 16 can be guided conveniently;
one ends, close to each other, of the two clamping side plates 22 are connected with rubber pads in an adhering mode, so that the surface of the unmanned aerial vehicle is prevented from being scratched;
spacing logical groove has all been seted up to two rack 21's inside, and the inside of centre gripping base 17 is fixed with a plurality of T shape guide pin pole 25, and a plurality of T shape guide pin poles 25 are located the inside in two spacing logical grooves respectively, are convenient for carry on spacing direction to rack 21.
The working principle of the invention is as follows: the positioning knob is rotated, the bidirectional threaded rod 14 is rotated through the fixed connection of the positioning knob and the bidirectional threaded rod 14, the two clamping mechanisms 15 are driven to move, and the distance between the two clamping mechanisms 15 is adjusted according to the length of the unmanned aerial vehicle body;
after the distance between the two clamping mechanisms 15 is adjusted, the unmanned aerial vehicle is placed at the upper end of the clamping base 17, the clamping knob 24 is rotated, the clamping knob 24 is fixedly connected with the second worm 23, the clamping knob 24 drives the second worm 23 to rotate, the second worm 23 is meshed with the second worm gear 20, the second worm gear 23 drives the second worm gear 20 to rotate, the second worm gear 20 drives the central shaft 18 to rotate through the fixed connection between the second worm gear 20 and the central shaft 18, the central shaft 18 drives the straight gear 19 to rotate through the fixed connection between the central shaft 18 and the straight gear 19, the straight gear 19 drives the rack 21 to move through the meshed connection between the straight gear 19 and the rack 21, the distance between the clamping side plates 22 on two sides of the same clamping base 17 is adjusted, when the clamping side plates 22 are in contact with the unmanned aerial vehicle body, through the rotating connection of the clamping side plate 22 and the rack 21, the clamping side plate 22 can rotate according to the body shape of the unmanned aerial vehicle, so that the clamping side plate 22 is attached to the body of the unmanned aerial vehicle, the body of the unmanned aerial vehicle is clamped through the matching of the two clamping side plates 22, and the unmanned aerial vehicle with different shapes can be clamped and fixed conveniently by the device, the application type of the device is improved, and the fixing effect of the unmanned aerial vehicle is improved;
the first motor 6 is started to enable the output end of the first motor 6 to rotate, the first motor 6 drives the first worm 8 to rotate through the fixed connection of the first motor 6 and the first worm 8, the first worm 8 drives the first worm wheel 9 to rotate through the meshed connection of the first worm 8 and the first worm wheel 9, the first worm wheel 9 drives the first angle adjusting plate 10 to rotate through the fixed connection of the first worm wheel 9 and the first angle adjusting plate 10, the rotating angle of the first angle adjusting plate 10 can be conveniently recognized through the angle indicating plate arranged on one side of the first worm wheel 9, and the unmanned aerial vehicle is further driven to perform first-time placing angle adjustment;
the second motor 11 is started, so that the output end of the second motor 11 rotates, the second motor 11 drives the second angle adjusting plate 12 to rotate through the fixed connection of the second motor 11 and the second angle adjusting plate 12, the rotation angle of the second angle adjusting plate 12 can be conveniently identified through an angle marking line arranged on the surface of the first angle adjusting plate 10 and an indicating arrow arranged on the surface of the second angle adjusting plate 12, the unmanned aerial vehicle is further driven to carry out the second-time placing angle adjustment, the vibration device main body 1 is then started, and the unmanned aerial vehicle is subjected to vibration test;
through the cooperation of first adjustment mechanism 3 and second adjustment mechanism 4 for arbitrary angle can be put to unmanned aerial vehicle, and then makes the device be convenient for simulate the vibration condition of unmanned aerial vehicle under different flight attitudes, makes the test result more accurate.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of the present invention, and these improvements and modifications should also be construed as the protection scope of the present invention. Structures, devices, and methods of operation not specifically described or illustrated herein are generally practiced in the art without specific recitation or limitation.
Claims (6)
1. The utility model provides an unmanned aerial vehicle vibration test device, includes vibration equipment main part (1) and vibration test platform (2), vibration test platform (2) set up in the upper end of vibration equipment main part (1), its characterized in that: the vibration test table (2) is provided with an adjusting module for adjusting the placing angle of the unmanned aerial vehicle, the adjusting module comprises a first adjusting mechanism (3) and a second adjusting mechanism (4), the first adjusting mechanism (3) is used for adjusting the placing angle of the unmanned aerial vehicle in the vertical direction, the second adjusting mechanism (4) is used for adjusting the placing angle of the unmanned aerial vehicle in the horizontal direction, and the first adjusting mechanism (3) is provided with a clamping module (5) for clamping and fixing the unmanned aerial vehicles with different shapes;
the first adjusting mechanism (3) comprises a first motor (6), a first shaft seat (7), a first worm (8), a first worm wheel (9) and a first angle adjusting plate (10), the first motor (6) and the first shaft seat (7) are both fixed at the lower end of the vibration test bench (2), the first worm wheel (8) is fixed at the output end of the first motor (6), the first worm wheel (8) is rotatably connected with the first shaft seat (7) through a ball bearing, the first worm wheel (9) is meshed and connected with the upper end of the first worm wheel (8), an angle indication plate is fixed on one side of the first worm wheel (9), the first angle adjusting plate (10) is welded on one side of the first worm wheel (9), and the first angle adjusting plate (10) is rotatably connected with the vibration test bench (2);
the second adjusting mechanism (4) comprises a second motor (11), a second angle adjusting plate (12) and a second shaft seat (13), the second motor (11) is fixed at the lower end of the first angle adjusting plate (10), the second angle adjusting plate (12) is fixed at the output end of the second motor (11), a guide chute is formed in the second angle adjusting plate (12), the second angle adjusting plate (12) is rotatably connected with the first angle adjusting plate (10), and the second shaft seat (13) is welded at the upper end of the second angle adjusting plate (12);
centre gripping module (5) are including two-way threaded rod (14), two fixture (15) and location knob, two-way threaded rod (14) are rotated and are connected in the inside of second axle seat (13), two external screw thread sections have been seted up in the outside of two-way threaded rod (14), and two the screw thread opposite direction of external screw thread section, two fixture (15) assemble respectively in the outside of two external screw thread sections, the location knob is fixed in the one end of two-way threaded rod (14).
2. The unmanned aerial vehicle vibration testing device of claim 1, wherein: the upper end of first angle regulating plate (10) evenly is provided with a plurality of angle sign lines, the upper end of second angle regulating plate (12) is provided with the instruction arrow point.
3. The vibration testing device of the unmanned aerial vehicle of claim 1, wherein: the clamping mechanism (15) comprises a lower sliding rod (16), a clamping base (17), a central shaft rod (18), a straight gear (19), a second worm wheel (20), two racks (21), two clamping side plates (22), a second worm (23) and a clamping knob (24), the lower sliding rod (16) is in threaded connection with the outer side of an external thread section, the clamping base (17) is welded at the upper end of the lower sliding rod (16), the central shaft rod (18) is rotatably connected inside the clamping base (17), the straight gear (19) and the second worm wheel (20) are both fixed on the outer side of the central shaft rod (18), the two racks (21) are respectively connected to two sides of the straight gear (19) in a meshed mode, and the two clamping side plates (22) are respectively rotatably connected to the upper ends of the two racks (21);
the second worm (23) is connected to one end of the second worm wheel (20) in a meshed mode, the second worm (23) is connected with the clamping base (17) in a rotating mode, and the clamping knob (24) is fixed to one end, extending out of the clamping base (17), of the second worm (23).
4. The vibration testing device of the unmanned aerial vehicle of claim 3, wherein: the lower end of the lower sliding rod (16) is provided with a sliding block, and the sliding block is connected to the inside of the guide sliding groove in a sliding mode.
5. The vibration testing device of the unmanned aerial vehicle of claim 3, wherein: and one ends of the two clamping side plates (22) close to each other are all connected with rubber pads in an adhering manner.
6. An unmanned aerial vehicle vibration testing arrangement according to claim 3, characterized in that: two spacing logical groove has all been seted up to the inside of rack (21), the inside of centre gripping base (17) is fixed with a plurality of T shape guide pin pole (25), and is a plurality of T shape guide pin pole (25) are located the inside in two spacing logical grooves respectively.
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| CN202111199582.7A CN113636103B (en) | 2021-10-14 | 2021-10-14 | Unmanned aerial vehicle vibration testing device |
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| CN202111199582.7A CN113636103B (en) | 2021-10-14 | 2021-10-14 | Unmanned aerial vehicle vibration testing device |
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| CN116594082B (en) * | 2023-07-19 | 2023-09-29 | 山东慧宇航空遥感技术有限公司 | Balanced testing arrangement of hyperspectral remote sensing geological survey appearance |
| CN118254962B (en) * | 2024-05-31 | 2024-07-26 | 烟台中商人工智能科技有限公司 | Unmanned aerial vehicle mechanical vibration testing arrangement |
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| CN105083588A (en) * | 2015-08-17 | 2015-11-25 | 华南农业大学 | Performance test platform and method for multi-rotor unmanned aerial vehicle |
| CN207045785U (en) * | 2017-06-12 | 2018-02-27 | 工业和信息化部计算机与微电子发展研究中心（中国软件评测中心） | A kind of electronic unmanned plane dynamical system is test bed and test system |
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| CN210761369U (en) * | 2019-09-29 | 2020-06-16 | 深圳市赛为智能股份有限公司 | Many rotor unmanned aerial vehicle testing arrangement |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083588A (en) * | 2015-08-17 | 2015-11-25 | 华南农业大学 | Performance test platform and method for multi-rotor unmanned aerial vehicle |
| CN207045785U (en) * | 2017-06-12 | 2018-02-27 | 工业和信息化部计算机与微电子发展研究中心（中国软件评测中心） | A kind of electronic unmanned plane dynamical system is test bed and test system |
| CN207510743U (en) * | 2017-11-14 | 2018-06-19 | 深圳市科比特航空科技有限公司 | Unmanned plane test platform |
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Effective date of registration: 20230410 Address after: 515800 No.8 East Jiangbei Road, Guangyi Longtian, Chenghai District, Shantou City, Guangdong Province Patentee after: SHANTOU HELICUTE MODEL AIRCRAFT INDUSTRIAL Co.,Ltd. Address before: Room 105b, block B, animation building, No.11 Xinghuo Road, Jiangbei new district, Nanjing, Jiangsu 210000 Patentee before: Nanjing Luda Electric Appliance Co.,Ltd. |