A flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body and its preparation method

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) fuselage technology, specifically to a flame-retardant, high-temperature resistant carbon fiber composite UAV fuselage, comprising: a bracket, a support frame fixed to the bottom of the bracket, a connecting rod fixed to the surface of the support frame, an extension frame fixed to the surface of the connecting rod, a telescopic rod inside the extension frame, a fixing block and a top holding block on the surface of the telescopic rod, a buffer block fixed to the surface of the fixing block, a connecting pipe at the end of the telescopic rod, and a fixing frame fixed to the other end of the connecting pipe; the beneficial effects are: the buffer block and the fixing block are removed from the through groove, while the top holding block remains in the through groove, and the two sets of top holding blocks are also held against the inner wall of the through groove by the support of the first spring, stabilizing the position of the telescopic rod and achieving the stability of the fixed frame; after the buffer block and the fixing block are removed from the through groove, the buffer block on the surface of the fixing block can be directly replaced without dismantling other structures.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) airframe technology, specifically to a flame-retardant, high-temperature resistant carbon fiber composite UAV airframe and its preparation method. Background Technology

[0002] With the continuous advancement of science and technology and the continuous improvement of drone technology, drones are unmanned aircraft controlled by radio remote control equipment and their own program control devices. Currently, they are widely used in fields such as aerial photography, agriculture, plant protection, mini selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying, news reporting, power line inspection, disaster relief, film and television shooting, and creating romance, greatly expanding the uses of drones. Developed countries are also actively expanding industry applications and developing drone technology.

[0003] In the prior art, patent CN109383777B discloses a drone body, including a fuselage, two side shafts, a tail shaft, a detachable mounting shaft, and a landing balancing system. An ultrasonic ranging module mounting port is located at the front of the fuselage, a remote control antenna is located at the top of the fuselage, and a communication antenna is located at the end of the tail shaft. Mounting components are located on both side shafts, and a connecting component is located on the tail shaft. Both the mounting components and the connecting component have drive motors and multiple fixing components. Multiple rotors are mounted on the drive motors. The landing balancing system includes a landing stabilization balance shaft and an arc-shaped balancing component. A gravity sensor and a balance control device are located inside the fuselage. The gravity sensor senses the balance state of the landing stabilization balance shaft, and the balance control device controls the landing stabilization balance shaft to be in a vertical position. This design solves the problems of low fuselage strength, large fuselage weight, difficulty in balancing the fuselage, high cost, and inconvenient installation in the prior art, ensuring the drone's balance through the landing stabilization balance shaft and the arc-shaped balancing component.

[0004] However, existing drones have shock-absorbing modules at the connection between the drone body and the camera. When the shock-absorbing module needs to be replaced, the camera part of the structure needs to be dismantled, resulting in low efficiency in replacing the shock-absorbing module. Summary of the Invention

[0005] The purpose of this invention is to provide a flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body and its preparation method, so as to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle (UAV) body, comprising: The bracket has a support frame fixed at its bottom, a connecting rod fixed on the surface of the support frame, an extension frame fixed on the surface of the connecting rod, a telescopic rod inside the extension frame, a fixing block and a top holding block on the surface of the telescopic rod, a buffer block fixed on the surface of the fixing block, a connecting pipe at the end of the telescopic rod, and a fixing frame fixed at the other end of the connecting pipe.

[0007] Preferably, the connecting pipe has an internal telescopic groove, and the telescopic rod is inserted into the telescopic groove. The telescopic rod can move in the telescopic groove. A second spring is provided in the telescopic groove. One end of the second spring is connected to the end of the telescopic rod, and the other end is connected to the inner wall of the telescopic groove. The second spring exerts a pulling force on the telescopic rod, and the telescopic rod is inserted into the telescopic groove under the pull of the second spring.

[0008] Preferably, a fixing block is fixed to the surface of the telescopic rod, and buffer blocks are fixed to the top and bottom of the fixing block by a fixing structure. A through groove is opened inside the extension frame, and the telescopic rod is inserted into the inside of the through groove, so that the telescopic rod can move in the through groove.

[0009] Preferably, the buffer block and the fixing block move with the telescopic rod, and the buffer block and the fixing block can be inserted into the through groove and can be removed from the through groove.

[0010] Preferably, the end of the telescopic rod is provided with a screw hole, and an arc-shaped plate is fixed on the surface of the connecting rod. The arc-shaped plate is made of flexible material, and a screw is screwed onto the surface of the arc-shaped plate. The end of the screw can be screwed into the screw hole.

[0011] Preferably, a connecting rod is inserted into the surface of the telescopic rod, the connecting rod can extend and retract inside the telescopic rod, a top holding block is fixed at the end of the connecting rod, the top holding block moves with the connecting rod, and a first spring is provided on the surface of the connecting rod.

[0012] Preferably, one end of the first spring is connected to the surface of the top holding block, and the other end of the first spring is connected to the surface of the telescopic rod. The first spring exerts a pushing force on the top holding block, causing the top holding block to press against the inner wall of the through groove, and the top holding block moves with the telescopic rod.

[0013] Preferably, the top holding block is located in the through groove and can move in the through groove. There are two sets of top holding blocks, which respectively hold the top and bottom of the through groove.

[0014] Preferably, a camera is fixed to the end of the bracket, and a propeller and a drive device are fixed to the surface of the bracket.

[0015] A method for preparing a flame-retardant, high-temperature resistant carbon fiber composite drone fuselage includes the following steps: High-temperature resistant flame-retardant epoxy resin / phenolic resin and T700 / T800 carbon fiber are selected as raw materials, and phosphorus-nitrogen-based or nano flame-retardant additives are added to make a resin liquid. After impregnation and drying, a Class B flame-retardant prepreg is obtained. Then, according to the stress requirements, the layer design is carried out, and it is formed by autoclave or compression molding. It is cured under controlled temperature and pressure. Finally, after trimming and post-curing, a lightweight, high-strength drone airframe that meets the UL94 V-0 flame retardant and high-temperature use requirements is obtained.

[0016] Compared with the prior art, the beneficial effects of the present invention are: This invention proposes a buffer block fixed to the surface of a fixed block. The buffer block contacts the extension frame, thus reducing vibration for the camera fixed to the frame surface. When the buffer block needs replacement, the screw is tightened to unscrew it from the screw hole. After loosening the screw, the telescopic rod is inserted into the telescopic groove under the pull of the second spring. The buffer block and fixed block move out of the through groove, while the top holding block remains in the through groove. Both sets of top holding blocks are also held against the inner wall of the through groove by the first spring, stabilizing the position of the telescopic rod and thus stabilizing the position of the fixed frame. After the buffer block and fixed block are removed from the through groove, the buffer block on the surface of the fixed block can be replaced directly without dismantling other structures. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the present invention.

[0018] Figure 2 This is a schematic diagram of the structure of the present invention from another perspective.

[0019] Figure 3 This is a schematic diagram of the extension frame structure of the present invention.

[0020] Figure 4 This is a schematic diagram of the internal structure of the extension frame of the present invention.

[0021] Figure 5 for Figure 4 Enlarged schematic diagram of the structure at point A in the middle.

[0022] In the diagram: 1. Bracket; 2. Support frame; 3. Connecting rod; 4. Through groove; 5. Arc plate; 6. Screw; 7. Telescopic rod; 8. Extension frame; 9. Connecting pipe; 10. Fixing frame; 11. First spring; 12. Insertion rod; 13. Buffer block; 14. Fixing block; 15. Second spring; 16. Telescopic groove; 17. Top support block; 18. Screw hole. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the present invention clear and complete, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some, not all, embodiments of the present invention, and are merely illustrative of the embodiments of the present invention. They are not intended to limit the embodiments of the present invention. All other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] Please see Figures 1 to 5 The present invention provides a technical solution: Example 1: A flame-retardant and high-temperature resistant carbon fiber composite material drone fuselage, comprising: a bracket 1, a support frame 2 fixed to the bottom of the bracket 1, a connecting rod 3 fixed to the surface of the support frame 2, an extension frame 8 fixed to the surface of the connecting rod 3, a telescopic rod 7 disposed inside the extension frame 8, a fixing block 14 and a top holding block 17 disposed on the surface of the telescopic rod 7, a buffer block 13 fixed to the surface of the fixing block 14, a connecting pipe 9 disposed at the end of the telescopic rod 7, a fixing frame 10 fixed to the other end of the connecting pipe 9, a screw hole 18 opened at the end of the telescopic rod 7, and the surface of the connecting rod 3... An arc-shaped plate 5 is fixed to the surface of the bracket 10. The arc-shaped plate 5 is made of flexible material. A screw rod 6 is screwed to the surface of the arc-shaped plate 5. The end of the screw rod 6 can be screwed into the screw hole 18. A camera is fixed to the end of the bracket 10. A propeller and a drive device are fixed to the surface of the bracket 1. The buffer block 13 and the fixed block 14 are stabilized in the through groove 4 by screwing the screw rod 6 into the screw hole 18 at the end of the telescopic rod 7. The buffer block 13 can play a buffering role. The arc-shaped plate 5 is flexible. When the telescopic rod 7 vibrates, the arc-shaped plate 5 can deform slightly against the telescopic rod 7.

[0025] Example 2: Based on Example 1, a telescopic groove 16 is provided inside the connecting pipe 9. The telescopic rod 7 is inserted into the telescopic groove 16 and can move within it. A second spring 15 is provided in the telescopic groove 16. One end of the second spring 15 is connected to the end of the telescopic rod 7, and the other end is connected to the inner wall of the telescopic groove 16. The second spring 15 exerts a pulling force on the telescopic rod 7, causing it to insert into the telescopic groove 16. A connecting rod 12 is inserted into the surface of the telescopic rod 7 and can extend and retract within it. A supporting block 17 is fixed to the end of the connecting rod 12 and moves with it. A first spring 11 is provided on the surface of the 2. One end of the first spring 11 is connected to the surface of the top holding block 17, and the other end of the first spring 11 is connected to the surface of the telescopic rod 7. The first spring 11 exerts a pushing force on the top holding block 17, so that the top holding block 17 is held against the inner wall of the through groove 4. The top holding block 17 moves with the telescopic rod 7. The top holding block 17 is located in the through groove 4 and can move in the through groove 4. There are two sets of top holding blocks 17, which are held against the top and bottom of the through groove 4 respectively. The top holding block 17 is always located in the through groove 4, and the two sets of top holding blocks 17 are also held against the inner wall of the through groove 4 under the support of the first spring 11, so as to stabilize the position of the telescopic rod 7 and realize the position stability of the fixing frame 10.

[0026] A fixing block 14 is fixed to the surface of the telescopic rod 7. A buffer block 13 is fixed to the top and bottom of the fixing block 14 via a fixing structure. A through slot 4 is provided inside the extension frame 8. The telescopic rod 7 is inserted into the through slot 4 and can move within it. The buffer block 13 and the fixing block 14 move with the telescopic rod 7. They can be inserted into and removed from the through slot 4. After the buffer block 13 and the fixing block 14 are removed from the through slot 4, the buffer block 13 on the surface of the fixing block 14 can be directly replaced without dismantling other structures. After replacement, the buffer block 13 and the fixing block 14 are simply pushed back into the through slot 4.

[0027] The buffer block 13 is fixed to the surface of the fixing block 14. The buffer block 13 contacts the extension frame 8, thus reducing the vibration of the camera fixed to the surface of the fixing frame 10. When the buffer block 13 needs to be replaced, screw 6 is turned out of the screw hole 18. After loosening the screw 6, the telescopic rod 7 is inserted into the telescopic groove 16 under the pull of the second spring 15. The buffer block 13 and the fixing block 14 are removed from the through groove 4, while the top holding block 17 remains in the through groove 4. Both sets of top holding blocks 17 are also held against the inner wall of the through groove 4 by the first spring 11, stabilizing the position of the telescopic rod 7. The position of the fixed frame 10 is stabilized. After the buffer block 13 and the fixed block 14 are removed from the through groove 4, the buffer block 13 on the surface of the fixed block 14 can be replaced directly without dismantling other structures. After replacement, the buffer block 13 and the fixed block 14 are simply pushed into the through groove 4 and screwed into the screw hole 18 at the end of the telescopic rod 7 by the screw 6 to stabilize the buffer block 13 and the fixed block 14 in the through groove 4. The buffer block 13 can play a buffering role. Moreover, the arc plate 5 is flexible. When the telescopic rod 7 vibrates, the arc plate 5 can deform slightly against the telescopic rod 7.

[0028] Although specific embodiments of this application have been described above to enable those skilled in the art to understand this application, this application is not limited to the scope of the specific embodiments. For those skilled in the art, all applications utilizing the concept of this application are protected as long as various variations are within the spirit and scope of this application as defined and determined by the appended claims.

Claims

1. A flame-retardant, high-temperature resistant carbon fiber composite material unmanned aerial vehicle (UAV) fuselage, characterized in that: include: The bracket (1) has a support frame (2) fixed at its bottom. A connecting rod (3) is fixed on the surface of the support frame (2). An extension frame (8) is fixed on the surface of the connecting rod (3). A telescopic rod (7) is provided inside the extension frame (8). A fixing block (14) and a top holding block (17) are provided on the surface of the telescopic rod (7). A buffer block (13) is fixed on the surface of the fixing block (14). A connecting pipe (9) is provided at the end of the telescopic rod (7). A fixing frame (10) is fixed at the other end of the connecting pipe (9).

2. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 1, characterized in that: The connecting pipe (9) has an internal telescopic groove (16), and the telescopic rod (7) is inserted into the telescopic groove (16). The telescopic rod (7) can move in the telescopic groove (16). A second spring (15) is provided in the telescopic groove (16). One end of the second spring (15) is connected to the end of the telescopic rod (7), and the other end is connected to the inner wall of the telescopic groove (16). The second spring (15) has a pulling force on the telescopic rod (7). Under the pull of the second spring (15), the telescopic rod (7) is inserted into the telescopic groove (16).

3. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 2, characterized in that: The surface of the telescopic rod (7) is fixed with a fixing block (14), and the top and bottom of the fixing block (14) are fixed with a buffer block (13) by a fixing structure. The extension frame (8) has a through groove (4) inside, and the telescopic rod (7) is inserted into the through groove (4). The telescopic rod (7) can move in the through groove (4).

4. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 3, characterized in that: The buffer block (13) and the fixing block (14) move with the telescopic rod (7), and the buffer block (13) and the fixing block (14) can be inserted into the through groove (4) and can be removed from the through groove (4).

5. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 4, characterized in that: The telescopic rod (7) has a screw hole (18) at its end. An arc plate (5) is fixed on the surface of the connecting rod (3). The arc plate (5) is made of flexible material. A screw rod (6) is screwed onto the surface of the arc plate (5). The end of the screw rod (6) can be screwed into the screw hole (18).

6. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 5, characterized in that: The telescopic rod (7) has a connecting rod (12) inserted into its surface. The connecting rod (12) can extend and retract inside the telescopic rod (7). A top holding block (17) is fixed at the end of the connecting rod (12). The top holding block (17) moves with the connecting rod (12). A first spring (11) is provided on the surface of the connecting rod (12).

7. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 6, characterized in that: One end of the first spring (11) is connected to the surface of the top holding block (17), and the other end of the first spring (11) is connected to the surface of the telescopic rod (7). The first spring (11) exerts a thrust on the top holding block (17), causing the top holding block (17) to press against the inner wall of the through groove (4), and the top holding block (17) moves with the telescopic rod (7).

8. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 7, characterized in that: The top holding block (17) is located in the through groove (4) and can move in the through groove (4). There are two sets of top holding blocks (17), which are respectively held on the top and bottom of the through groove (4).

9. The flame-retardant and high-temperature resistant carbon fiber composite material unmanned aerial vehicle body according to claim 8, characterized in that: A camera is fixed to the end of the bracket (10), and a propeller and a drive device are fixed to the surface of the bracket (1).

10. A method for preparing a flame-retardant, high-temperature resistant carbon fiber composite unmanned aerial vehicle (UAV) fuselage, characterized in that: Includes the following steps: High-temperature resistant flame-retardant epoxy resin / phenolic resin and T700 / T800 carbon fiber are selected as raw materials, and phosphorus-nitrogen-based or nano flame-retardant additives are added to make a resin liquid. After impregnation and drying, a Class B flame-retardant prepreg is obtained. Then, according to the stress requirements, the layer design is carried out, and it is formed by autoclave or compression molding. It is cured under controlled temperature and pressure. Finally, after trimming and post-curing, a lightweight, high-strength drone airframe that meets the UL94 V-0 flame retardant and high-temperature use requirements is obtained.

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