Unmanned aerial vehicle spare part strength detection device

Abstract

The utility model discloses an unmanned plane spare and parts strength detection device belongs to unmanned plane spare and parts detection technical field, aims at solving the fixture of most device in prior art and the stretching host computer adopt rigid fixed structure, lack standardization quick -change interface, and this design defect directly leads to the actual application rate of fixture to be lower, simultaneously, the existing fixture is many for single specification or material's spare and part design, when detecting object switches, often appears the fixture unable steady fixed work piece, or the clamping force and spare and part material quality mismatching situation, and this kind of adaptability insufficient problem not only is difficult to cover the diversified unmanned plane spare and part detection demand, also can cause the stretching data distortion because of the fixture improper adaptation, and further unable accurate judgment spare and part's actual stretching strength performance problem. Including host computer, the upper side of host computer is fixed with vertical mounting frame, and the middle part of vertical mounting frame is equipped with lifting mechanism, and the lifting mechanism includes guide mounting frame.

Description

Technical Field

[0001] This utility model belongs to the field of strength testing technology for drone parts, and specifically relates to a strength testing device for drone parts. Background Technology

[0002] Drone technology has fully penetrated the civilian market from the military field, and has been applied on a large scale in scenarios such as aerial surveying and mapping, logistics and transportation, agricultural plant protection, and power line inspection. This trend has driven the continuous expansion of the global drone market. As a precision equipment that works in collaboration with multiple systems, the mechanical structure and power system components of drones directly determine flight safety. According to strength requirements, they can be divided into key load-bearing components and auxiliary structural components. Before these components are put into practical use, they must be subjected to strength testing, which requires the use of specialized strength testing devices.

[0003] Currently, most strength testing devices use rigid fixed structures for their clamps and tensile testing units, lacking standardized quick-change interfaces. This design flaw directly leads to a low actual application rate of the clamps. At the same time, existing clamps are mostly designed for parts of a single specification or material. When the object to be tested is changed, the clamps often fail to stably fix the workpiece, or the clamping force is not compatible with the material of the part. This lack of adaptability not only makes it difficult to cover the diverse testing needs of UAV parts, but may also lead to distorted tensile data due to improper clamp adaptation, thus making it impossible to accurately determine the actual tensile strength performance of the parts. Utility Model Content

[0004] (1) Technical problems to be solved To address the shortcomings of existing technologies, the purpose of this utility model is to provide a strength testing device for UAV parts. This device addresses the issue that most existing devices employ rigid fixing structures for the clamps and tensile testing units, lacking standardized quick-change interfaces. This design flaw directly leads to a low practical application rate of the clamps. Furthermore, existing clamps are mostly designed for parts of a single specification or material. When the testing object changes, the clamps often fail to stably fix the workpiece, or the clamping force is mismatched with the part's material. This lack of adaptability not only makes it difficult to cover the diverse testing needs of UAV parts but may also lead to distorted tensile data due to improper clamp adaptation, thus making it impossible to accurately determine the actual tensile strength performance of the parts.

[0005] (2) Technical solution To address the aforementioned technical problems, this utility model provides a strength testing device for unmanned aerial vehicle (UAV) parts, comprising a main unit. A vertical mounting frame is fixedly mounted on one side of the upper part of the main unit, and a lifting mechanism is mounted in the middle of the vertical mounting frame. The lifting mechanism includes a guide frame, and clamping seats are provided at opposite positions below the front end of the guide frame and above the main unit. An adapter clamp is mounted in the middle of the two clamping seats. A quick-installation mechanism is provided in the middle of the clamping seats and at the contact part with the adapter clamp. The quick-installation mechanism includes an assembly groove, which is opened on the working surface of the clamping seats. An adjustment component is mounted in the lower middle section of the clamping seats. The adjustment component includes a first gear, and a linkage component is provided in the middle and above the first gear.

[0006] Furthermore, the adjustment assembly includes a female sleeve, which is fixedly disposed on the lower side inside the clamping seat. A return spring is provided in the middle of the female sleeve, and a sub-guide sleeve is connected to the end of the return spring. A pull plate is provided at one end of the sub-guide sleeve, and a connecting sleeve is fixedly disposed on one side of the middle section of the sub-guide sleeve. A rack is connected to one end of the connecting sleeve, and a first gear is engaged on the inner side of the rack.

[0007] Furthermore, the rack and connecting sleeve form a telescopic guide connection through the sub-guide cylinder, the return spring, and the mother cylinder.

[0008] Furthermore, the linkage component includes a rotating column, which is fixed in the middle of the first gear. A second gear is fixed at the top of the rotating column, and rack carriages mesh on both sides of the second gear. Guide frames are provided on both sides of the middle of the clamping seat to guide the movement of the corresponding rack carriages. Supporting guide plates are fixed above the opposite ends of the two rack carriages. Side guide blocks are provided at different ends of the middle of the clamping seat to support and guide the supporting guide plates. Inserting blocks are fixed on the opposite inner sides of the two supporting guide plates. Mounting grooves are opened on both sides of the middle of the assembly groove, and inserting grooves are opened on both sides of the lower part of the adapter fixture.

[0009] Furthermore, the mounting block and the mounting slot are connected by a mounting guide, and the end size of the mounting block matches the opening size of the mounting slot.

[0010] Furthermore, the lifting mechanism includes a lifting assembly, which is installed in the middle of the vertical mounting frame. The lifting assembly includes a guide frame, and the upper and lower sides of the guide frame are equipped with accordion-style protective covers.

[0011] Furthermore, the lifting assembly includes a servo motor, which is fixedly mounted inside the upper part of the vertical mounting frame. The output end of the servo motor is connected to a transmission screw, and a screw sleeve is screwed around one side of the transmission screw. A guide frame is screwed onto one section of the screw sleeve, and guide rods for guiding the guide frame are fixed on both sides of the front section of the middle part of the vertical mounting frame.

[0012] (3) Beneficial effects Compared with the prior art, the beneficial effects of this utility model are as follows: This invention allows operators to pre-change the corresponding adapter fixture according to the different drone parts to be tested for strength. The replacement method is as follows: the operator first pulls the pull plate, causing the sub-guide cylinder to move along the guide cylinder of the mother cylinder, and at the same time stretches the return spring used for connection. At this moment, the connecting sleeve fixed at one end of the sub-guide cylinder will move synchronously with the rack. As a result, the first gear meshing with the rack will drive the rotating column to rotate. Since the top of the rotating column is fixed with a second gear, and rack slides are meshed on both sides of the second gear, a pair of misaligned rack slides will mesh with the rotating second gear. Under the combined transmission, the guide frame moves relative to each other. Since the two rack and pinion carriages are fixed with support guide plates at their respective ends, and the inner end of the support guide plates is provided with an insert block, under the above-mentioned transmission action, the pair of support guide plates and insert blocks can be aligned with the support and guidance of the side guide blocks and mounting grooves, and disengage from the mounting grooves on both sides of the adapter fixture. In this state, the personnel replace the corresponding adapter fixture. After the replacement is completed, the pull plate is slowly released, and the return spring is reset, thereby driving all the above components back to the initial position. At this time, the stable limit of the new adapter fixture can be achieved.

[0013] After the corresponding fitting fixtures are assembled in the middle of the two clamping seats, the operator can clamp the two ends of the UAV parts to be tested through the two clamping structures. Then, the servo motor is started to rotate the transmission screw. The screw sleeve that cooperates with it will drive the guide frame and the corresponding clamping seat to rise along the guide rod, thereby moving the two clamps away from each other and realizing tensile strength testing. It is worth mentioning that accordion-style protective covers are installed on both sides of the guide frame, and the ends of the two accordion-style protective covers are fixed to the upper and lower ends of the vertical frame, respectively. At this time, the accordion-style protective covers will move synchronously with the displacement of the guide frame, thereby effectively protecting the transmission screw and the guide rod. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 This is a schematic diagram of the lifting mechanism. Figure 3 This is a schematic diagram of a three-dimensional partial structure; Figure 4 This is a three-dimensional perspective diagram of the clamping base. Figure 5 This is a schematic diagram of a local structure of the adjustment component.

[0015] The labels in the attached diagram are as follows: 1. Main unit; 2. Vertical mounting frame; 3. Lifting mechanism; 31. Lifting assembly; 311. Servo motor; 312. Transmission screw; 313. Screw sleeve; 314. Guide frame; 315. Guide rod; 32. Bellows-style protective cover; 4. Clamping seat; 5. Quick installation mechanism; 51. Assembly slot; 52. Adjustment assembly; 521. Mother cylinder; 522. Return spring; 523. Sub-guide cylinder; 524. Pull plate; 525. Connecting sleeve; 526. Rack; 527. First gear; 53. Linkage assembly; 531. Rotating column; 532. Second gear; 533. Rack slide; 534. Guide frame; 535. Support guide plate; 536. Side guide block; 537. Insert block; 538. Mounting slot; 539. Inserting slot; 6. Adaptive fixture. Detailed Implementation

[0016] This specific embodiment is a strength testing device for unmanned aerial vehicle (UAV) components, and its structural schematic diagram is shown below. Figures 1 to 4 As shown, the system includes a main unit 1. A vertical mounting frame 2 is fixedly mounted on one side of the upper part of the main unit 1. A lifting mechanism 3 is mounted in the middle of the vertical mounting frame 2. The lifting mechanism 3 includes a guide frame 314. A clamping seat 4 is provided at the lower front end of the guide frame 314 and at the opposite position above the main unit 1. An adapter clamp 6 is installed in the middle of the two clamping seats 4. A quick-installation mechanism 5 is provided in the middle of the clamping seat 4 and the contact part with the adapter clamp 6. The lifting mechanism 3 includes a lifting assembly 31, which is installed in the middle of the vertical mounting frame 2. The lifting assembly 31 includes the guide frame 314, and accordion-style protective covers 32 are installed on the upper and lower sides of the guide frame 314. The lifting assembly 31 includes a servo motor 311, which is fixedly mounted inside the upper part of the vertical mounting frame 2. The output end of the servo motor 311 is connected to a transmission screw 312, and a screw sleeve 313 is screwed around one side of the transmission screw 312. A guide frame 314 is provided on one end of the screw of 313. Guide rods 315 are fixed on both sides of the front section of the middle of the vertical mounting frame 2 to guide the guide frame 314. After the corresponding matching fixtures 6 are assembled in the middle of the two clamping seats 4, the staff can clamp the two ends of the UAV parts to be tested through the two clamping structures. Then, the servo motor 311 is started to rotate the transmission screw 312. The screw sleeve 313 that cooperates with it will drive the guide frame 314 and the corresponding clamping seat 4 to rise along the guide rod 315, thereby making the two clamps move away from each other and realizing the tensile strength test. It is worth mentioning that accordion-style protective covers 32 are installed on both sides of the guide frame 314, and the ends of the two accordion-style protective covers 32 are fixed to the upper and lower ends of the vertical mounting frame 2 respectively. At this time, the accordion-style protective covers 32 will move synchronously with the displacement of the guide frame 314, thereby effectively protecting the transmission screw 312 and the guide rod 315.

[0017] The quick-installation mechanism 5 includes an assembly groove 51, which is located on the working surface of the clamping base 4. An adjustment component 52 is installed in the lower middle section of the clamping base 4. The adjustment component 52 includes a female mounting cylinder 521, which is fixedly located inside the clamping base 4 on the lower side. A return spring 522 is located in the middle of the female mounting cylinder 521, and a sub-guide cylinder 523 is connected to the end of the return spring 522. A pull plate 524 is located at one end of the sub-guide cylinder 523, and a connecting sleeve 525 is fixedly located on one side of the middle section of the sub-guide cylinder 523. A rack 526 is connected to one end of the connecting sleeve 525, and a first gear 527 meshes with the inner side of the rack 526. The rack 526 and the connecting sleeve 525 form an extension through the sub-guide cylinder 523, the return spring 522, and the female mounting cylinder 521. The first gear 527 is connected to a guide, and a linkage component 53 is provided at the middle and above of the first gear 527. The linkage component 53 includes a rotating column 531, which is fixed at the middle of the first gear 527. A second gear 532 is fixed at the top of the rotating column 531, and rack and pinion carriages 533 mesh on both sides of the second gear 532. Guide frames 534 are provided on both sides of the middle of the clamping base 4 to guide the movement of the corresponding rack and pinion carriages 533. Supporting guide plates 535 are fixed above the opposite ends of the two rack and pinion carriages 533. Side guide blocks 536 are provided at different ends of the middle of the clamping base 4 to support and guide the supporting guide plates 535. Embedding blocks 537 are fixed on the opposite inner sides of the two supporting guide plates 535. Mounting grooves 538 are provided on both sides of the middle of the assembly groove 51 to adapt to... The fixture 6 has mounting slots 539 on both sides below. The mounting block 537 and the mounting slot 538 are connected by a mounting guide. The end size of the mounting block 537 matches the opening size of the mounting slot 539. The operator can change the corresponding adapter fixture 6 in advance according to the different drone parts to be tested. The change method is as follows: the operator first pulls the pull plate 524, so that the sub-guide cylinder 523 moves along the guide cylinder 521. At the same time, the return spring 522 used for connection is stretched. At this time, the connecting sleeve 525 fixed at one end of the sub-guide cylinder 523 will move synchronously with the rack 526. As a result, the first gear 527 meshing with the rack 526 will drive the rotating column 531 to rotate. Since the top of the rotating column 531 is fixed with a second gear 532, and the second gear 532 is fixed with a second gear 532, the operator can change the corresponding adapter fixture 6 in advance. The guide frame 534 has rack and pinion carriages 533 meshing on both sides of the 32. Therefore, a pair of misaligned rack and pinion carriages 533 will move relative to each other under the meshing transmission of the rotating second gear 532. Since each pair of rack and pinion carriages 533 has a supporting guide plate 535 fixed at its opposite end, and the inner end of the supporting guide plate 535 has an insert block 537, under the aforementioned transmission action, the pair of supporting guide plates 535 and insert blocks 537 can be aligned with the support and guidance of the side guide block 536 and the mounting groove 538, and disengage from the mounting grooves 539 on both sides of the adapter clamp 6. In this state, the personnel replace the corresponding adapter clamp 6. After the replacement is completed, the pull plate 524 is slowly released, and the return spring 522 returns to its original position, thereby driving all the above components back to their initial positions.This allows for stable positioning of the new adapter fixture 6.

[0018] Working principle: Operators can pre-change the corresponding adapter clamp 6 according to the different drone parts to be tested for strength. The replacement method is as follows: Operators first pull the pull plate 524, causing the sub-guide cylinder 523 to move along the guide cylinder 521, simultaneously stretching the reset spring 522 used for connection. At this moment, the connecting sleeve 525 fixed at one end of the sub-guide cylinder 523 will move synchronously with the rack 526. Thus, the first gear 527 meshing with the rack 526 will drive the rotating column 531 to rotate. Since a second gear is fixed at the top of the rotating column 531… 532, and rack and pinion carriages 533 are meshed on both sides of the second gear 532. Therefore, a pair of misaligned rack and pinion carriages 533 will move relative to each other with the guide frame 534 under the meshing transmission of the rotating second gear 532. Since a support guide plate 535 is fixed at the opposite end of each pair of rack and pinion carriages 533, and an insert block 537 is provided at the inner end of the support guide plate 535, under the above-mentioned transmission action, the pair of support guide plates 535 and insert blocks 537 can be aligned with the support and guidance of the side guide block 536 and the mounting groove 538. The device detaches from the mounting slots 539 on both sides of the adapter fixture 6. In this state, the operator replaces the corresponding adapter fixture 6. After the replacement is completed, the pull plate 524 is slowly released, and the return spring 522 returns to its original position, thereby driving all the above components back to their initial positions. At this time, the new adapter fixture 6 can be stably limited. Next, after the corresponding adapter fixture 6 is assembled in the middle of the two clamping seats 4, the operator can clamp the two ends of the UAV parts to be tested through the two clamping structures. Then, the servo motor 311 is started to rotate the transmission screw 312. When the guide rod is moved, the lead screw sleeve 313 will drive the guide frame 314 and the corresponding clamping seat 4 to rise along the guide rod 315, thereby moving the two clamps away from each other and realizing tensile strength testing. It is worth mentioning that both sides of the guide frame 314 are equipped with bellows-type protective covers 32, and the ends of the two bellows-type protective covers 32 are respectively fixed to the upper and lower ends of the vertical frame 2. At this time, the bellows-type protective covers 32 will move synchronously with the displacement of the guide frame 314, thereby effectively protecting the transmission lead screw 312 and the guide rod 315.

[0019] It should be noted that: 《1》The inner walls of the contact parts of the adapter fixture (6) and the clamping base (4) are provided with vibration damping and anti-slip pads. By setting the vibration damping and anti-slip pads, the stress load can be increased when the two are used to clamp the drone parts. At the same time, it can also play the role of vibration damping and anti-slip, ensuring the stability of the parts clamping during the testing process. The clamp structure in the "2" adapter clamp (6) is the conventional clamping structure on the market, and will not be described in detail here.

Claims

1. A strength testing device for unmanned aerial vehicle (UAV) components, comprising a main unit (1), characterized in that, A vertical mounting frame (2) is fixedly provided on one side above the host (1), and a lifting mechanism (3) is provided in the middle of the vertical mounting frame (2). The lifting mechanism (3) includes a guide frame (314). A clamping seat (4) is provided at the lower front end of the guide frame (314) and at the opposite position above the host (1). An adapter clamp (6) is provided in the middle of the two clamping seats (4). A quick installation mechanism (5) is provided in the middle of the clamping seat (4) and the contact part with the adapter clamp (6). The quick installation mechanism (5) includes an assembly groove (51), and the assembly groove (51) is opened on the working surface of the clamping seat (4). An adjustment component (52) is installed in the lower middle section of the clamping seat (4). The adjustment component (52) includes a first gear (527), and a linkage component (53) is provided in the middle and above of the first gear (527).

2. The strength testing device for UAV parts according to claim 1, characterized in that, The adjustment assembly (52) includes a female sleeve (521), which is fixedly disposed on the lower side inside the clamping seat (4). A return spring (522) is provided in the middle of the female sleeve (521), and a sub-guide sleeve (523) is connected to the end of the return spring (522). A pull plate (524) is provided at one end of the sub-guide sleeve (523), and a connecting sleeve (525) is fixedly disposed on one side of the middle section of the sub-guide sleeve (523). A rack (526) is connected to one end of the connecting sleeve (525), and a first gear (527) is meshed on the inner side of the rack (526).

3. The strength testing device for UAV parts according to claim 2, characterized in that, The rack (526) and connecting sleeve (525) form a telescopic guide connection through the sub-guide cylinder (523), the return spring (522) and the mother cylinder (521).

4. The strength testing device for UAV parts according to claim 1, characterized in that, The linkage component (53) includes a rotating column (531), which is fixed in the middle of the first gear (527). A second gear (532) is fixed at the top of the rotating column (531), and a rack slide (533) meshes with both sides of the second gear (532). Guide frames (534) are provided on both sides of the middle of the clamping seat (4) to guide the movement of the corresponding rack slide (533). Supporting guide plates (535) are fixed above the opposite ends of the two rack slides (533). Side guide blocks (536) are provided at different ends of the middle of the clamping seat (4) to support and guide the supporting guide plates (535). Inserting blocks (537) are fixed on the opposite inner sides of the two supporting guide plates (535). Mounting grooves (538) are opened on both sides of the middle of the assembly groove (51), and inserting grooves (539) are opened on both sides of the lower part of the adapter clamp (6).

5. The strength testing device for unmanned aerial vehicle (UAV) components according to claim 4, characterized in that, The mounting block (537) and the mounting groove (538) are connected by a mounting guide, and the end size of the mounting block (537) matches the opening size of the mounting groove (539).

6. The strength testing device for unmanned aerial vehicle (UAV) components according to claim 1, characterized in that, The lifting mechanism (3) includes a lifting component (31), and the lifting component (31) is installed in the middle of the vertical frame (2). The lifting component (31) includes a guide frame (314), and the upper and lower sides of the guide frame (314) are equipped with accordion-style protective covers (32).

7. The strength testing device for unmanned aerial vehicle (UAV) components according to claim 6, characterized in that, The lifting assembly (31) includes a servo motor (311), and the servo motor (311) is fixedly installed inside the upper part of the vertical mounting frame (2). The output end of the servo motor (311) is connected to a transmission screw (312), and a screw sleeve (313) is screwed around one side of the transmission screw (312). A guide frame (314) is screwed onto one section of the screw sleeve (313). Guide rods (315) for guiding the guide frame (314) are fixed on both sides of the front section of the middle part of the vertical mounting frame (2).

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