Unmanned aerial vehicle optical fiber communication structure capable of being quickly assembled

Abstract

The utility model relates to the technical field of unmanned aerial vehicle optical fiber communication, and discloses an unmanned aerial vehicle optical fiber communication structure capable of being quickly assembled, which comprises an aircraft frame, two supporting plates are fixedly arranged on the aircraft frame, supporting frames are arranged on the two supporting plates in a penetrating and sliding manner, and transverse limiting plates are fixedly arranged on the two supporting frames. The two transverse limiting plates are fixedly provided with clamping plates, an optical fiber barrel is fixedly arranged between the two clamping plates, a plurality of fixing bolts are arranged between the two clamping plates in a penetrating mode, and a rotating rod is fixedly arranged between the two supporting frames. And then the supporting frame, the transverse limiting plate and the clamping plate are matched, the optical fiber barrel is fixed through the fixing bolts, installation of the optical fiber barrel is completed, meanwhile, the supporting frame is limited through the first assembling mechanism and the second assembling mechanism, and the firmness of the optical fiber barrel after fixing is improved.

Description

A rapidly assembled UAV fiber optic communication structure Technical Field

[0001] This utility model relates to the field of fiber optic communication technology for unmanned aerial vehicles (UAVs), and specifically to a UAV fiber optic communication structure that can be quickly assembled. Background Technology

[0002] Unmanned aerial vehicle (UAV) fiber optic communication is an innovative communication method that combines fiber optic transmission technology with UAV platforms. Its core lies in achieving high-speed, low-latency data transmission through fiber optics. The video signal captured by the camera on the UAV is converted into an optical signal and transmitted at high speed through fiber optics to the ground control station. Then, it is converted back into an electrical signal and decoded into video for display. It shows unique advantages, especially in complex electromagnetic environments and scenarios requiring high confidentiality.

[0003] The existing method of installing fiber optic canisters requires staff to use bandages to wrap the canisters multiple times around the tail of the drone to complete the installation. However, this method of fixing is affected by the drone's vibration, which affects stability. In addition, the multiple wrappings are cumbersome and not convenient to use. Summary of the Invention

[0004] The purpose of this utility model is to provide a fast-assembly fiber optic communication structure for unmanned aerial vehicles (UAVs) in order to solve the above problems. First, two support plates initially limit the corresponding number of support frames, lateral limiting plates, and clamping plates. Then, the fiber optic tube is installed with the clamping plates by fixing bolts. Finally, it is connected to the UAV.

[0005] This utility model achieves the above objectives through the following technical solutions:

[0006] A fast-assembly UAV fiber optic communication structure includes: an aircraft frame, wherein the aircraft frame is fixedly provided with two support plates, each of the two support plates is slidably provided with a support frame, each of the two support frames is fixedly provided with a lateral limiting plate, and each of the two lateral limiting plates is fixedly provided with a clamping plate.

[0007] An optical fiber barrel is fixedly disposed between the two clamping plates, and multiple fixing bolts are disposed through the two clamping plates. A rotating rod is fixedly disposed between the two support frames. The two rotating rods are respectively provided with a first assembly mechanism and a second assembly mechanism. Both support plates are provided with a first threaded hole.

[0008] Furthermore, the first assembly mechanism includes a groove frame and a screw body, wherein the groove frame has a first sliding frame through it and a first through hole through it.

[0009] Furthermore, the groove frame is provided with storage slots, which are respectively provided with nut placement slots and screw end placement slots.

[0010] Furthermore, a first mortise is provided on the side of the groove frame away from the storage slot, and a plurality of first tenons are fixedly provided in the first mortise.

[0011] Furthermore, the screw body is fixedly provided with a screw end, and the screw body is threadedly fitted with a screw nut.

[0012] Furthermore, the second assembly mechanism includes a snap-fit ​​frame, through which a second sliding frame is provided.

[0013] Furthermore, the snap-fit ​​frame has a second through hole, and the snap-fit ​​frame is fixedly provided with a plurality of second tenons, with a second mortise formed between the plurality of second tenons.

[0014] Furthermore, propeller supports are provided on all four sides of the upper part of the aircraft frame.

[0015] Furthermore, the aircraft frame is fixedly equipped with a battery retaining strap.

[0016] Furthermore, a storage battery is snapped between the aircraft frame and the battery fixing strap.

[0017] In summary, the beneficial effects of this utility model are as follows: the two support plates fixed by the aircraft frame, together with the support frame, clamping plate and fixing bolts, can quickly fix the optical fiber tube. At the same time, the first assembly mechanism and the second assembly mechanism reinforce the support frame a second time through the two screw bodies and the first threaded holes opened on the two support plates, which further improves the clamping firmness of the optical fiber tube. At the same time, the operation is simple and convenient. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 is a front view of this utility model;

[0020] Figure 2 is a side view of this utility model near the battery fixing belt;

[0021] Figure 3 is an axonometric view of this utility model near the support plate;

[0022] Figure 4 is an enlarged view of section A in Figure 2 of this utility model;

[0023] Figure 5 is an axonometric view of the first assembly mechanism and the second assembly mechanism of this utility model after partial separation.

[0024] Figure 6 is an axonometric view of the present invention near the second assembly mechanism in Figure 5.

[0025] The annotations in the attached figures are explained as follows:

[0026] 1. Aircraft frame; 2. Battery fixing strap; 3. Battery; 4. Support frame; 5. Support plate; 6. Clamping plate; 7. Fixing bolt; 8. Fiber optic tube; 9. Lateral limiting plate; 10. First assembly mechanism; 1001. Groove frame; 1002. First through hole; 1003. First sliding frame; 1004. Storage slot; 1005. Nut placement slot; 1006. Screw end placement slot; 1007. First mortise; 1008. First tenon; 1009. Screw body; 1010. Screw nut; 1011. Screw end; 11. Second assembly mechanism; 1101. Snap-fit ​​frame; 1102. Second sliding frame; 1103. Second through hole; 1104. Second tenon; 1105. Second mortise; 12. First threaded hole; 13. Propeller bracket; 14. Rotating rod. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0028] Referring to Figures 1-4, this utility model provides a rapidly assembleable UAV fiber optic communication structure, comprising: an aircraft frame 1, wherein the aircraft frame 1 is fixedly provided with two support plates 5, each of the two support plates 5 is slidably provided with a support frame 4, each of the two support frames 4 is fixedly provided with a transverse limiting plate 9, each of the two transverse limiting plates 9 is fixedly provided with a clamping plate 6, an optical fiber tube 8 is fixedly provided between the two clamping plates 6, a plurality of fixing bolts 7 are provided through the two clamping plates 6, a rotating rod 14 is fixedly provided between the two support frames 4, the two rotating rods 14 are respectively rotatably provided with a first assembly mechanism 10 and a second assembly mechanism 11, each of the two support plates 5 is provided with a first threaded hole 12, propeller brackets 13 are fixedly provided around the upper perimeter of the aircraft frame 1, a battery fixing strap 2 is fixedly provided on the aircraft frame 1, and a storage battery 3 is snapped between the aircraft frame 1 and the battery fixing strap 2;

[0029] Using the above technical solution, a support plate 5 is fixed below the aircraft frame 1. A hole is opened in the middle of the support plate 5 to provide space for the insertion of the support frame 4 and facilitate the installation of the fiber optic tube 8. The two support frames 4 pass through the support plate 5, and the lateral limiting plate 9 on the upper part of the support frame 4 restricts the descent distance of the support frame 4, while also supporting the clamping plate 6, serving a supporting function. Simultaneously, fixing bolts 7 are used to clamp and fix the clamping plate 6 and the fiber optic tube 8 through the clamping plate 6, making the fixation of the fiber optic tube 8 more stable and secure. To improve the stability of fiber optic transmission, the first assembly mechanism 10 and the second assembly mechanism 11, which slide on the outer surface of the rotating rod 14 fixed between the two support frames 4, and in conjunction with the two support plates 5, limit the lower part, so that the first assembly mechanism 10 and the second assembly mechanism 11 and the two support plates 5 form a stable support, improving the firmness between the support frame 4, the lateral limiting plate 9 and the clamping plate 6 and the support plate 5. The battery 3 is bound by the battery fixing strap 2 to provide power drive for the aircraft frame 1, and the drone is driven to complete the flight through the propeller bracket 13.

[0030] Referring to Figures 4-6, the first assembly mechanism 10 includes a groove frame 1001 and a screw body 1009. The groove frame 1001 has a first sliding frame 1003 through it, a first through hole 1002 through it, a storage slot 1004, a nut placement slot 1005 and a screw end placement slot 1006 respectively, a first mortise 1007 on the side of the groove frame 1001 away from the storage slot 1004, a plurality of first tenons 1008 are fixedly provided in the first mortise 1007, a screw end 1011 is fixedly provided in the screw body 1009, and a screw nut 1010 is threadedly fitted onto the screw body 1009.

[0031] In use, the groove frame 1001 and the second assembly mechanism 11 are used to form a horizontal splice. The screw body 1009 is included in both the first assembly mechanism 10 and the second assembly mechanism 11. The first slide frame 1003 and the rotating rod 14 fixed between the support frame 4 allow the first assembly mechanism 10 to rotate around the rotating rod 14, making it easy for the support frame 4 to be inserted into the hole opened in the support plate 5. The screw body 1009 passes through the first through hole 1002 and, after passing through the entire groove frame 1001, is connected into the first threaded hole 12 of the support plate 5, completing the fixed connection between the groove frame 1001 and the first threaded hole 12. The screw body 1009, screw nut 1010 and screw end 1011 are stored and placed through the storage slot 1004, nut placement slot 1005 and screw end placement slot 1006. Finally, the first mortise 1007 opened in the groove frame 1001 and the first tenon 1008 inside the mortise complete the horizontal splice with the second assembly mechanism 11.

[0032] Referring to Figures 5 and 6, the second assembly mechanism 11 includes a snap-fit ​​frame 1101, a second sliding frame 1102 is provided through the snap-fit ​​frame 1101, a second through hole 1103 is provided through the snap-fit ​​frame 1101, and a plurality of second tenons 1104 are fixedly provided on the snap-fit ​​frame 1101, with a second mortise 1105 provided between the plurality of second tenons 1104.

[0033] In the above embodiment, both the second assembly mechanism 11 and the first assembly mechanism 10 have storage slots 1004, nut placement slots 1005 and screw end placement slots 1006, as well as screw bodies 1009, screw nuts 1010 and screw ends 1011 placed inside. There are two screw bodies 1009, facilitating the through-connection of the first threaded holes 12 on both the first assembly mechanism 10, the second assembly mechanism 11, and the two support plates 5. The second sliding frame 1102, in conjunction with one of the two rotating rods 14, allows the entire snap-fit ​​frame 1101 to continue rotating around the rotating rod 14. The second through hole 1103, in conjunction with the first threaded hole 12 on one of the support plates 5, fixes the snap-fit ​​frame 1101 in parallel. The second tenon 1... The first tenon 1007 and the first tenon 1008 in the first assembly mechanism 10 are engaged and fixed with the second mortise 1105 and the first mortise 1007 in the first assembly mechanism 10. After the engaging frame 1101 is rotated and balanced around the rotating rod 14, the engaging frame 1101 and the groove frame 1001 are engaged and spliced ​​laterally. Finally, two screw bodies 1009 are used to pass through the first through hole 1002 and the second through hole 1103 respectively, and extend through the two support plates 5 and the first threaded hole 12 opened in the support plate 5. Then, the workers use screw nuts 1010 to put on the outside of the support plate 5, so that the groove frame 1001 and the engaging frame 1101 are fixed in parallel, completing the fixation of the lower part of the first assembly mechanism 10 and the second assembly mechanism 11, and strengthening the stable connection between the fiber optic tube 8 and the aircraft frame 1.

[0034] Using the above structure, when it is necessary to install the fiber optic tube 8 and the aircraft, firstly, the support frame 4 passes through the support plate 5, and the support frame 4 is limited by the lateral limiting plate 9 to prevent the support frame 4 from sinking downwards. At the same time, the lateral limiting plate 9 supports the clamping plate 6, and the clamping plate 6 clamps the fiber optic tube 8 to one side of the aircraft. Then, multiple fixing bolts 7 pass through the clamping plate 6 and the fiber optic tube 8 to complete the fixing of the fiber optic tube 8. Then, the first assembly mechanism 10 and the second assembly mechanism 11 are rotated and parallel to each other outside the rotating rod 14 through the first sliding frame 1003 and the second sliding frame 1102 respectively. Then, the groove frame 1001 of the second assembly mechanism 11 is brought close to the snap-fit ​​frame 1101 of the second assembly mechanism 11 to fix one side of the snap-fit ​​frame 1101. The second tenon 1104 and the second mortise 1105 are respectively engaged with the first mortise 1007 and the first tenon 1008 to complete the initial connection between the groove frame 1001 and the engaging frame 1101. Then, the two screw bodies 1009 are taken out from the storage slots 1004 of the groove frame 1001 and the engaging frame 1101, and the two screw bodies 1009 are respectively passed through the first through hole 1002, the second through hole 1103 and the first threaded hole 12 that are passed through the two support plates 5. Then, the screw nut 1010 is used to fit from the top to fix the groove frame 1001 and the first threaded hole 12 together. With the help of the transverse limiting plate 9, the support frame 4 and the clamping plate 6 are locked to complete the assembly and connection of the fiber optic tube 8 and the aircraft frame 1.

[0035] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A rapidly assembleable fiber optic communication structure for unmanned aerial vehicles (UAVs), characterized in that, include: Aircraft frame (1), the aircraft frame (1) is fixedly provided with two support plates (5), both support plates (5) are slidably provided with support frames (4), both support frames (4) are fixedly provided with transverse limiting plates (9), both transverse limiting plates (9) are fixedly provided with clamping plates (6); fiber optic tubes (8) are fixedly provided between the two clamping plates (6), multiple fixing bolts (7) are provided through the two clamping plates (6), rotating rods (14) are fixedly provided between the two support frames (4), the two rotating rods (14) are respectively rotatably provided with a first assembly mechanism (10) and a second assembly mechanism (11), and both support plates (5) are provided with first threaded holes (12).

2. The rapidly assembleable UAV fiber optic communication structure according to claim 1, characterized in that: The first assembly mechanism (10) includes a groove frame (1001) and a screw body (1009). The groove frame (1001) has a first sliding frame (1003) through it and a first through hole (1002) through it.

3. The rapidly assembleable UAV fiber optic communication structure according to claim 2, characterized in that: The groove frame (1001) has a storage slot (1004), and the storage slot (1004) has a nut placement slot (1005) and a screw end placement slot (1006).

4. The rapidly assembleable UAV fiber optic communication structure according to claim 3, characterized in that: The groove frame (1001) has a first mortise (1007) on the side away from the storage groove (1004), and a plurality of first tenons (1008) are fixedly provided in the first mortise (1007).

5. The rapidly assembleable UAV fiber optic communication structure according to claim 4, characterized in that: The screw body (1009) is fixedly provided with a screw end (1011), and the screw body (1009) is threadedly fitted with a screw nut (1010).

6. The rapidly assembleable UAV fiber optic communication structure according to claim 1, characterized in that: The second assembly mechanism (11) includes a snap-fit ​​frame (1101), through which a second sliding frame (1102) is provided.

7. The rapidly assembleable UAV fiber optic communication structure according to claim 6, characterized in that: The snap-fit ​​frame (1101) has a second through hole (1103) through it, and the snap-fit ​​frame (1101) is fixedly provided with a plurality of second tenons (1104), and a second mortise (1105) is provided between the plurality of second tenons (1104).

8. The rapidly assembleable UAV fiber optic communication structure according to claim 1, characterized in that: The aircraft frame (1) is provided with propeller supports (13) on all four sides near the top.

9. The rapidly assembleable UAV fiber optic communication structure according to claim 1, characterized in that: The aircraft frame (1) is fixedly equipped with a battery fixing strap (2).

10. The rapidly assembleable UAV fiber optic communication structure according to claim 1, characterized in that: A storage battery (3) is snapped between the aircraft frame (1) and the battery fixing strap (2).

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