Impact force testing device for manufacturing unmanned aerial vehicle

Abstract

The utility model discloses an impact force test device for unmanned aerial vehicle manufacturing, and belongs to the technical field of unmanned aerial vehicles. The device comprises a test box, a lifting assembly and a clamping assembly, a circular groove is formed in the test box, the lifting assembly comprises two supporting plates, a driving roller and a motor, the supporting plates are installed on the test box, through holes are formed in the supporting plates, the two ends of the driving roller are rotationally matched with the two through holes respectively, a traction rope is arranged on the driving roller, and the traction rope penetrates through the circular groove. According to the utility model, through the arrangement of the lifting assembly, the problems that in practical application, the unmanned aerial vehicle may face impacts of various heights, if the test device cannot adjust the height of the impact block, the test result may have a deviation from the practical situation, and the deviation may cause misjudgment of the impact endurance capability of the unmanned aerial vehicle; therefore, the safety and the reliability of the product are influenced.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned aerial vehicle technical field, concretely is the impact force test device for unmanned aerial vehicle manufacturing. BACKGROUND

[0002] The unmanned aerial vehicle impact force test device is a device specially used for testing the tolerance and protection performance of unmanned aerial vehicles under impact or collision, and the design of the device aims to simulate the force that the unmanned aerial vehicle may suffer in accidental impact or collision to evaluate its resistance to impact and structural stability.

[0003] In practical application, the unmanned aerial vehicle may face impacts of various heights, and if the test device cannot adjust the height of the impact block, the test result may deviate from the actual situation, which may lead to misjudgment of the impact tolerance of the unmanned aerial vehicle, thereby affecting the safety and reliability of the product. UTILITY MODEL CONTENT

[0004] The utility model discloses a impact force test device for unmanned aerial vehicle manufacturing, through opening motor, make motor drive the rotation of driving roller, drive the traction rope reeling simultaneously, traction rope drive support plate moves up, support plate drive battery moves up simultaneously drive electromagnet moves up, so that electromagnet drive impact iron ball moves up, when impact iron ball reaches the designated position, cut off the power of electromagnet, make impact iron ball no longer adsorb in electromagnet, so that impact iron ball falls on unmanned aerial vehicle body, solved in practical application, the unmanned aerial vehicle may face impacts of various heights, and if the test device cannot adjust the height of the impact block, the test result may deviate from the actual situation, which may lead to misjudgment of the impact tolerance of the unmanned aerial vehicle, thereby affecting the safety and reliability of the product.

[0005] The utility model is realized through the following technical schemes:

[0006] The utility model discloses a impact force test device for unmanned aerial vehicle manufacturing, including test box, lifting assembly and clamping assembly, the circular groove is set up on test box, lifting assembly includes support board, driving roller and motor, support board installs on test box, support board is provided with two, the through -hole is set up on support board, and the both ends of driving roller are rotated and are matched in two through -holes respectively, and the traction rope is set up on driving roller, and the traction rope passes through circular groove, and the traction rope is installed with support plate on the one end away from driving roller, and the support plate is installed with battery, and the bottom of support plate is installed with electromagnet, and the connecting mode of electromagnet and battery is electric connection, and the impact iron ball is adsorbed on electromagnet, and the motor is installed on test box, and the power output shaft of motor is connected with the center shaft of driving roller.

[0007] Further, two sliding grooves are formed on the test box, and two sliding plates are installed on the supporting plate and are respectively slidably connected to the two sliding grooves.

[0008] Further, the clamping assembly comprises a base plate and two threaded rods, the base plate is installed on the test box, the threaded rods are provided with handles at one ends and clamping plates at the other ends, the two clamping plates are connected to the UAV body, two threaded holes are formed on the test box and are threadedly connected to the threaded rods, and two limiting grooves are formed on the base plate and are respectively slidably connected to the two clamping plates.

[0009] Further, a door is installed on the opening of the test box, the door is connected to the test box through a hinge, and a handle is installed on the door.

[0010] Further, an observation window is formed on the door.

[0011] Further, a universal wheel is installed at the corner of the bottom of the test box.

[0012] The utility model has the following beneficial effects:

[0013] The utility model discloses a test device for unmanned aerial vehicle, which comprises a test box, a supporting plate, a battery, a motor, a driving roller, a traction rope, an electromagnet and an impact iron ball.

[0014] Of course, any product implementing the utility model does not necessarily need to achieve all the advantages mentioned above. DRAWINGS

[0015] Figure 1 It is a whole structure schematic diagram of impact force test device.

[0016] Figure 2 It is a whole structure schematic diagram of lifting assembly.

[0017] Figure 3 It is a connecting structure schematic diagram of clamping assembly and unmanned aerial vehicle body.

[0018] Figure 4It is a schematic view of the connecting structure of the test box, the circular groove, the sliding groove and the threaded hole.

[0019] Figure 5 It is a schematic view of the connecting structure of the support plate and the through hole.

[0020] In the figure: 1, test box; 101, circular groove; 102, sliding groove; 103, threaded hole; 2, lifting assembly; 201, support plate; 202, through hole; 203, driving roller; 204, traction rope; 205, support plate; 206, battery; 207, electromagnet; 208, impact iron ball; 209, motor; 210, sliding plate; 3, clamping assembly; 301, base plate; 302, threaded rod; 303, handle; 304, clamping plate; 305, limiting groove; 4, unmanned aerial vehicle body; 5, box door; 6, handle; 7, observation window; 8, universal wheel. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0022] Please refer to Figures 1-5 The present application provides a technical solution: an impact force test device for unmanned aerial vehicle manufacturing, comprising a test box 1, a lifting assembly 2 and a clamping assembly 3, a circular groove 101 is formed on the test box 1, the circular groove 101 is used to cooperate with the traction rope 204,

[0023] A box door 5 is installed at the opening of the test box 1, the box door 5 is connected with the test box 1 through a hinge, and a handle 6 is installed on the box door 5, under the condition that the handle 6 is pulled, the handle 6 drives the box door 5 to open, so as to place the unmanned aerial vehicle body 4 on the base plate 301.

[0024] The clamping assembly 3 comprises a base plate 301 and a threaded rod 302, the base plate 301 is fixedly installed on the test box 1 through bolts, two threaded holes 103 are formed on the test box 1, the threaded rod 302 is threadedly matched with the threaded hole 103, two limiting grooves 305 are formed on the base plate 301, two clamping plates 304 are respectively slidingly matched with the two limiting grooves 305, the limiting grooves 305 limit the clamping plates 304, so as to avoid the deviation of the clamping plates 304 in the sliding process.

[0025] When the unmanned aerial vehicle body 4 needs to be clamped, two threaded rods 302 are arranged, one end of the threaded rod 302 is provided with a handle 303, the other end of the threaded rod 302 is provided with a clamping plate 304, the handle 303 is driven to move the threaded rod 302 by rotating the handle 303, the threaded rod 302 drives the clamping plate 304 to clamp the unmanned aerial vehicle body 4, and the unmanned aerial vehicle body 4 is fixed, so that the displacement of the unmanned aerial vehicle body 4 in the test process is avoided, and the test result is affected.

[0026] The lifting assembly 2 comprises a support plate 201, a driving roller 203 and a motor 209, the support plate 201 is installed on the test box 1, the support plate 201 is provided with two through holes 202, and the two ends of the driving roller 203 are respectively rotationally fitted in the two through holes 202.

[0027] The test box 1 is provided with two sliding grooves 102, and the support plate 205 is provided with two sliding plates 210, the two sliding plates 210 are respectively slidably fitted in the two sliding grooves 102, and the sliding groove 102 limits the sliding plate 210, so that the sliding plate 210 is prevented from deviating during upward and downward sliding.

[0028] When the impact force test of the unmanned aerial vehicle body 4 is needed, the motor 209 is installed on the test box 1 through the mounting seat, the power output shaft of the motor 209 is connected with the center shaft of the driving roller 203, the motor 209 is turned on through an external power supply, the power output shaft of the motor 209 drives the driving roller 203 to rotate, the driving roller 203 is provided with a traction rope 204, the traction rope 204 drives the support plate 205 to move upward, the support plate 205 is provided with a battery 206, the bottom of the support plate 205 is provided with an electromagnet 207, the connection mode between the electromagnet 207 and the battery 206 is electrical connection, the electromagnet 207 is provided with an impact iron ball 208, the support plate 205 drives the battery 206 and the electromagnet 207 to move upward, the electromagnet 207 drives the iron ball 208 to move upward to a specified position, the iron ball 208 is dropped to the unmanned aerial vehicle body 4 by turning off the electromagnet 207, so that the impact force test of the unmanned aerial vehicle body 4 is completed.

[0029] The box door 5 is provided with an observation window 7, when the impact force test is carried out, the box door 5 is in a closed state, the fragments of the unmanned aerial vehicle body 4 in the test are prevented from splashing, and the safety of the test personnel is ensured, and the observation window 7 is used for observing the impact force test in the test box 1.

[0030] The universal wheels 8 are installed at the bottom of the test box 1 and at the corners, facilitating the movement of the test box 1 to a designated position, avoiding manual carrying and reducing the workload of the test personnel.

[0031] The above disclosed preferred embodiments of the utility model are only used for helping to set forth the utility model. The preferred embodiments do not describe all the details exhaustively, and also do not limit the utility model to only the specific implementation manners described. Obviously, according to the content of the description, many modifications and changes can be made. The description selects and specifically describes these embodiments in order to better explain the principle and practical application of the utility model, so that the persons skilled in the art can well understand and utilize the utility model. The utility model is limited by the claims and the whole scope and equivalents thereof.

Claims

1. An impact force testing device for manufacturing unmanned aerial vehicles, comprising a test chamber (1), wherein a circular groove (101) is provided on the test chamber (1), characterized in that; It also includes a lifting assembly (2), which includes a support plate (201), a drive roller (203), and a motor (209). The support plate (201) is mounted on the test chamber (1). There are two support plates (201). The support plate (201) has through holes (202). The two ends of the drive roller (203) are respectively rotatably fitted into the two through holes (202). A traction rope (204) is provided on the drive roller (203). The traction rope (204) passes through the circular groove (101). 204) A support plate (205) is installed at the end away from the drive roller (203). A storage battery (206) is installed on the support plate (205). An electromagnet (207) is installed at the bottom of the support plate (205). The electromagnet (207) is electrically connected to the storage battery (206). An impact iron ball (208) is attracted to the electromagnet (207). The motor (209) is installed on the test chamber (1). The power output shaft of the motor (209) is connected to the central shaft of the drive roller (203).

2. The impact force testing device for manufacturing unmanned aerial vehicles according to claim 1, characterized in that, The test chamber (1) has two slide grooves (102), and the support plate (205) is equipped with two slide plates (210). The two slide plates (210) are respectively slidably engaged with the two slide grooves (102).

3. The impact force testing device for manufacturing unmanned aerial vehicles according to claim 1, characterized in that, It also includes a clamping assembly (3), which includes a base plate (301) and a threaded rod (302). The base plate (301) is mounted on the test chamber (1). There are two threaded rods (302). One end of the threaded rod (302) is equipped with a handle (303), and the other end of the threaded rod (302) is equipped with a clamping plate (304). The two clamping plates (304) are fitted together with the unmanned aerial vehicle body (4). The test chamber (1) has two threaded holes (103). The threaded rod (302) is threadedly engaged with the threaded holes (103). The base plate (301) has two limiting grooves (305). The two clamping plates (304) are slidably engaged with the two limiting grooves (305).

4. The impact force testing device for manufacturing unmanned aerial vehicles according to claim 3, characterized in that, The test chamber (1) is equipped with a door (5) at its opening. The door (5) is connected to the test chamber (1) by a hinge, and a handle (6) is installed on the door (5).

5. The impact force testing device for manufacturing unmanned aerial vehicles according to claim 4, characterized in that, An observation window (7) is provided on the box door (5).

6. The impact force testing device for manufacturing unmanned aerial vehicles according to claim 5, characterized in that, The test chamber (1) is equipped with casters (8) at the bottom and corner.

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