A landing-safe carbon fiber drone

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology, and proposes a landing collision-resistant carbon fiber UAV for solving the landing collision problem. The UAV includes a fuselage, a hollow upper support, a hollow lower support, and a flight control system. The hollow upper support is located at the upper part of the fuselage and extends outwards with branches. A lifting motor is located at the end of each branch, and a lifting propeller is mounted on the rotating shaft of the lifting motor. The flight control system is located on the upper surface of the hollow upper support, which has an upper cover for enclosing the flight control system. The hollow lower support is located at the lower end of the fuselage and has rotatable landing gear. Buffer cylinders are located on the left and right sides of the hollow lower support, with their front and rear ends attached to the free ends of the landing gear. The buffer cylinders have spiral openings to facilitate side deformation buffering and front-to-back compression deformation buffering.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle technology, and in particular to a landing and collision-resistant carbon fiber unmanned aerial vehicle. Background Technology

[0002] In today's rapidly evolving technological landscape, drone technology, as a prime example of innovative technology, is flourishing at an astonishing pace. It is now widely integrated into all aspects of social life, playing an indispensable role in numerous industries thanks to its unique advantages. When a drone finishes its flight mission and descends slowly to prepare for landing, the process should be smooth and stable. However, the reality is often less than ideal. At the moment of descent, improper deceleration or external wind forces can cause the drone to lose control of its descent speed and attitude, resulting in a noticeable impact jolt and violent vibration of the fuselage, much like an out-of-control object suddenly crashing heavily to the ground. This jolt not only produces a loud noise upon landing but also allows for clear visual observation of the drone's swaying and deviation.

[0003] The physical impact of a drone's landing not only damages its delicate components but also harms the circuitry and solder joints of its electrical systems. The circuit boards inside a drone are densely packed with electronic components connected by solder joints, forming a complex circuit system. The impact of a landing causes the circuit boards to vibrate violently, leading to relative displacement between the electronic components and the solder joints. With increased usage time and the accumulation of landing impacts, the drone's operational precision gradually suffers. Over time, the solder joints on the circuit boards may crack or loosen. Once a solder joint fails, an open circuit or short circuit occurs, preventing the electrical components from functioning properly. Ultimately, this leads to a loss of flight control, and in severe cases, even causes the drone to lose contact, resulting in a flight accident.

[0004] To address the aforementioned issues, this paper proposes a collision-resistant drone that can physically buffer the impact shock force generated during landing. Summary of the Invention

[0005] Therefore, in view of the above problems, the present invention proposes a landing collision-resistant carbon fiber UAV to solve the landing collision problem.

[0006] To solve the above-mentioned technical problems, the solution adopted by the present invention is as follows: a landing and impact-resistant carbon fiber unmanned aerial vehicle (UAV), comprising a fuselage, a hollow upper support, a hollow lower support, and a flight control system, characterized in that: the hollow upper support is disposed at the upper part of the fuselage, the hollow upper support extends outward with at least four branches, the end of each branch is provided with a lifting motor, the rotating shaft of the lifting motor is provided with a lifting propeller, the flight control system is disposed on the upper surface of the hollow upper support, the hollow upper support is provided with an upper cover for enclosing the flight control system, the hollow lower support is disposed at the lower end of the fuselage, the four corners of the hollow lower support are respectively provided with rotatable feet, the left and right sides of the hollow lower support are respectively provided with buffer cylinders, the front and rear ends of the buffer cylinders are disposed on the free ends of the feet, and the buffer cylinders are spirally opened with spiral buffer openings to facilitate side deformation buffering and front and rear compression deformation buffering.

[0007] A further improvement is that the front end of the buffer cylinder is provided with a front mounting seat and the rear end is provided with a rear mounting seat. The front mounting seat and the rear mounting seat are integrally formed with the leg. The front mounting seat is provided with a front anti-collision head. The front end of the front anti-collision head is provided with a buffer protrusion. The front anti-collision head is provided with a front buffer structure that provides a front-to-back elastic deformation force to the buffer protrusion.

[0008] A further improvement is that: the outer wall of the buffer cylinder is provided with a spiral mounting groove along the spiral trajectory, a rubber buffer strip is provided in the spiral mounting groove, the inner side of the rubber buffer strip is embedded in the spiral mounting groove, and the outermost protrusion of the spiral mounting groove exceeds the protrusion of the front mounting seat and the rear mounting seat.

[0009] A further improvement is made to the buffer structure, which includes a mounting cylinder, a spring, and a front compression plate. The mounting cylinder is fixedly mounted on the front bumper, the spring is movably mounted inside the mounting cylinder, and the front compression plate is located at the front end of the spring and movably mounted inside the mounting cylinder. The buffer protrusion penetrates the front bumper and is fixedly mounted on the front compression plate at the front end face of the mounting cylinder.

[0010] A further improvement is that the buffer structure also includes a rear extrusion plate, which is located at the rear end of the spring and movably disposed within the mounting cylinder. A connecting rod is fixedly disposed on the front end face of the buffer cylinder, and the connecting rod passes through the rear end face of the mounting cylinder and is fixedly disposed on the rear extrusion plate.

[0011] A further improvement is that a propulsion motor is horizontally mounted on the rear mounting base, and a propulsion propeller is mounted on the rotating shaft of the propulsion motor.

[0012] A further improvement is that: the four corners of the hollowed-out lower support are integrally provided with leg mounting protrusions, and the front or rear face of the leg mounting protrusion is provided with a rotating mounting groove extending horizontally towards the middle of the side of the machine body, and the fixed end of the leg is rotatably disposed in the rotating mounting groove.

[0013] A further improvement is that the body is an annular shell with a wiring cavity inside. The lower support has a positioning protrusion that protrudes upward in the middle for embedding into the middle of the annular shell, and the left and right sides of the lower support form arc-shaped sidewalls that fit against the outer wall of the annular shell.

[0014] A further improvement is that the hollow upper support is in the shape of a ring, the hollow upper support is attached to the upper end of the outer wall of the ring shell, and a hollow mounting platform is provided in the middle of the hollow support. The flight control system and the upper cover are mounted on the mounting platform.

[0015] A further improvement is that the number of branches is six.

[0016] By adopting the aforementioned technical solution, the beneficial effects of the present invention are:

[0017] 1. The buffer cylinder in this case can provide both vertical impact protection during landing and frontal impact protection during flight, forming a full-scenario protection system. It not only solves the most prominent landing damage problem of traditional drones, but also makes up for the shortcomings in protection against sudden collisions during flight, achieving dual protection of "landing + flight".

[0018] 2. Through the buffer design of rubber buffer strips, TPU elastic buffer cylinders, and spiral buffer openings, the impact shock force during landing is absorbed, transmitted, and dissipated layer by layer, completely changing the impact transmission path of traditional "hard landing" of drones. This avoids the fuselage and internal structure directly bearing severe physical impact, reducing the risk of collision and damage to parts from the source, ensuring operational accuracy, and extending service life.

[0019] Furthermore, the combination of rubber buffer strips and elastic buffer cylinders allows for landing in various scenarios, including flat ground and slightly uneven terrain. Even in complex terrain or environments with slight wind interference, it can still achieve a smooth landing, improving the drone's environmental adaptability. The spiral buffer opening design also reduces lateral wind resistance, which helps maintain the drone's flight stability.

[0020] 3. Through the buffer design of the front anti-collision head, buffer protrusion, and front buffer structure, the axial deformation of the buffer protrusion, spring, and buffer cylinder of the front anti-collision head can effectively absorb the front impact force, avoid damage to the propulsion motor due to impact, and avoid the impact force being transmitted to the electronic components on the machine body.

[0021] The front bumper's buffer protrusion provides the first line of protection against frontal impacts. Its protruding design prioritizes contact with obstacles, pushing the front compression plate to compress the spring through the buffer protrusion. The spring further cushions the impact through its own elastic deformation. If the impact force is large, it further compresses the buffer cylinder, forming "double emergency protection." Even if operational errors lead to untimely avoidance, it can effectively protect the machine body and core components, reduce the probability of equipment damage, increase the user's fault tolerance during operation, and enhance the user's sense of security.

[0022] 4. The fuselage is a ring-shaped shell with a wiring cavity inside, which reduces the weight of the fuselage. The ring-shaped shell can guide airflow to both sides in all directions. The middle part works with the hollow upper and lower brackets to reduce wind resistance during the take-off and landing of the drone.

[0023] 5. The carbon fiber fuselage and hollow support structure enhance protection while effectively controlling the overall weight of the fuselage, avoiding problems such as shortened flight endurance and power loss caused by adding a buffer structure, thus ensuring the original flight performance of the drone. Attached Figure Description

[0024] Figure 1 This is a three-dimensional structural diagram of a landing and impact-resistant carbon fiber UAV according to an embodiment of the present invention.

[0025] Figure 2 This is a top view structural diagram of a landing and collision-resistant carbon fiber UAV according to an embodiment of the present invention.

[0026] Figure 3 This is a top-view structural diagram of a landing and collision-resistant carbon fiber UAV according to an embodiment of the present invention.

[0027] Figure 4 This is a side view structural diagram of a landing and collision-resistant carbon fiber UAV according to an embodiment of the present invention.

[0028] Figure 5 This is a rear-view structural diagram of a landing and collision-resistant carbon fiber UAV according to an embodiment of the present invention.

[0029] Figure 6 This is a three-dimensional structural diagram of the fuselage, hollow upper support, and hollow lower support of a carbon fiber UAV with anti-collision landing capability according to an embodiment of the present invention.

[0030] Figure 7 This is a three-dimensional structural diagram of the fuselage and hollowed-out lower support of a carbon fiber unmanned aerial vehicle (UAV) designed for landing and collision protection, according to an embodiment of the present invention.

[0031] Figure 8 This is a three-dimensional structural diagram of a hollowed-out lower support frame in a carbon fiber UAV that is designed for landing and collision protection, according to an embodiment of the present invention.

[0032] Figure 9This is a rear view schematic diagram of the hollowed-out lower support structure in a carbon fiber UAV with anti-collision landing according to an embodiment of the present invention.

[0033] Figure 10 This is a schematic diagram of the internal structure of the buffer cylinder and front buffer structure in a carbon fiber UAV that is designed for landing and collision protection according to an embodiment of the present invention. Detailed Implementation

[0034] The present invention will now be further described in conjunction with the accompanying drawings and specific embodiments.

[0035] refer to Figures 1 to 10 This invention discloses a landing-safe carbon fiber unmanned aerial vehicle (UAV) with collision protection, comprising a fuselage 10, a hollow upper support 11, a hollow lower support 12, and a flight control system 13. The fuselage 10, hollow upper support 11, and hollow lower support 12 are all made of lightweight, high-strength carbon fiber material. The flight control system 13 in this invention can be configured differently according to the functions required by the UAV. This solution focuses on improving the hardware structure of the UAV. The hollow upper support 11 is disposed on the upper end of the fuselage 10. The hollow upper support 11 extends outward with six branches 14. A lifting motor 15 is embedded at the end of each branch 14. A lifting propeller 16 is disposed on the rotating shaft of the lifting motor 15. The flight control system 13 is disposed on the upper surface of the hollow upper support 11. The hollow upper support 11 is provided with an upper cover (not shown in the figure) for covering the flight control system 13. The hollow lower support 12 is disposed on the lower end of the fuselage 10. A rotatable landing gear 17 is disposed at each of the four corners of the hollow lower support 12. A landing gear mounting protrusion 18 is integrally provided at each of the four corners of the hollow lower support 12. A rotating mounting groove 19 extending horizontally towards the middle of the side of the fuselage 10 is opened on the front or rear face of the landing gear mounting protrusion 18. The fixed end of the landing gear 17 is rotatably disposed in the rotating mounting groove 19.

[0036] Buffer cylinders 20 are respectively provided on the left and right sides of the hollowed-out lower support 12. The buffer cylinders 20 are made of thermoplastic polyurethane (TPU), which has the advantages of good elasticity, fast rebound and wear and scratch resistance. The front and rear ends of the buffer cylinders 20 are provided on the free ends of the legs 17. The buffer cylinders 20 are spirally opened with spiral buffer openings 21 to facilitate the side deformation buffer and front and rear compression deformation buffer. The outer wall of the buffer cylinders 20 is provided with a spiral mounting groove 22 along the spiral trajectory. A rubber buffer strip (not shown in the figure) is provided in the spiral mounting groove 22. The inner side of the rubber buffer strip is embedded in the spiral mounting groove 22. The outermost protrusion of the spiral mounting groove 22 exceeds the protrusion of the front mounting seat 23 and the rear mounting seat 24.

[0037] The buffer cylinder 20 has a front mounting base 23 at its front end and a rear mounting base 24 at its rear end, and the front mounting base 23 and the rear mounting base 24 are integrally formed with the stand 17. A propulsion motor 25 is horizontally mounted on the rear mounting base 24, and a propulsion propeller 26 is mounted on the rotating shaft of the propulsion motor 25. A front bumper head 27 is mounted on the front mounting base 23, and a buffer protrusion 28 is provided at the front end of the front bumper head 27. A front buffer structure is provided inside the front bumper head 27 to provide a front-to-back elastic deformation force to the buffer protrusion 28. The buffer structure includes a mounting cylinder 29, a spring 30, a front compression plate 31, and a rear compression plate 32. The mounting cylinder 29 is fixedly mounted on the front bumper 27. The spring 30 is movably mounted inside the mounting cylinder 29. The front compression plate 31 is located at the front end of the spring 30 and is movably mounted inside the mounting cylinder 29. The buffer protrusion 28 penetrates the front bumper 27 and is fixedly mounted on the front compression plate 31. The rear compression plate 32 is located at the rear end of the spring 30 and is movably mounted inside the mounting cylinder 29. A connecting rod 33 is fixedly mounted on the front end of the buffer cylinder 20 and is fixedly mounted on the rear compression plate 32 through the rear end of the mounting cylinder 29.

[0038] The fuselage 10 is an annular shell with a wiring cavity inside. The lower support has a positioning protrusion 34 that protrudes upward in the middle for embedding into the middle of the annular shell. The left and right sides of the lower support form arc-shaped sidewalls 35 that fit against the outer wall of the annular shell. The hollow upper support 11 is annular and fits against the upper end of the outer wall of the annular shell. The hollow support has a hollow mounting platform 36 in the middle. The flight control system 13 and the upper cover are mounted on the mounting platform 36.

[0039] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions above are merely illustrative of the principles of the present invention. Various changes and modifications can be made to the present invention without departing from its spirit and scope. All such changes and modifications fall within the scope of the present invention as claimed, which is defined by the appended claims and their equivalents.

Claims

1. A carbon fiber unmanned aerial vehicle for landing and taking off, comprising a fuselage, a hollow upper support, a hollow lower support, a flight control system, characterized in that: The hollow upper support is arranged at the upper end of the fuselage, and at least four branches are arranged outwardly from the hollow upper support. A lifting motor is arranged at the end of each branch, and a lifting propeller is arranged on the rotating shaft of the lifting motor. The flight control system is arranged on the upper surface of the hollow upper support, and an upper cover is arranged on the hollow upper support to cover the flight control system. The hollow lower support is arranged at the lower end of the fuselage, and a foot support capable of rotating forward and backward is arranged at each corner of the hollow lower support. A buffer cylinder is arranged on the left side and the right side of the hollow lower support, and the front end and the rear end of the buffer cylinder are arranged on the free end of the foot support. A spiral buffer opening is spirally arranged on the buffer cylinder to facilitate the side deformation and the front and rear extrusion deformation of the buffer cylinder. The front end of the buffer cylinder is provided with a front mounting seat, and the rear end is provided with a rear mounting seat. The front mounting seat and the rear mounting seat are integrally arranged with the foot support. A front anti-collision head is arranged on the front mounting seat. A buffer protrusion is arranged at the front end of the front anti-collision head. A front buffer structure is arranged in the front anti-collision head to provide the buffer protrusion with a front and rear elastic deformation force. The buffer structure comprises a mounting cylinder, a spring and a front extrusion plate. The mounting cylinder is fixedly arranged on the front anti-collision head. The spring is movably arranged in the mounting cylinder. The front extrusion plate is movably arranged in the mounting cylinder at the front end of the spring. The buffer protrusion penetrates the front end surface of the front anti-collision head and the mounting cylinder and is fixedly arranged on the front extrusion plate. The buffer structure further comprises a rear extrusion plate. The rear extrusion plate is movably arranged in the mounting cylinder at the rear end of the spring. A connecting rod is fixedly arranged on the front end surface of the buffer cylinder. The connecting rod penetrates the rear end surface of the mounting cylinder and is fixedly arranged on the rear extrusion plate. The fuselage is in the form of a ring-shaped housing. A wiring cavity is formed in the ring-shaped housing. A positioning protrusion is arranged on the middle part of the lower support to be embedded in the middle part of the ring-shaped housing. The left and right sides of the lower support are in the form of arc-shaped side walls which are attached to the outer wall of the ring-shaped housing. The hollow upper support is in the form of a circular ring. The hollow upper support is attached to the outer wall of the ring-shaped housing at the upper end. The hollow upper support is provided with a hollow mounting platform in the middle part. The flight control system and the upper cover are arranged on the mounting platform.

2. The crash-avoiding carbon fiber drone of claim 1, wherein: A spiral mounting groove is arranged on the outer wall of the buffer cylinder along a spiral track. A rubber buffer strip is arranged in the spiral mounting groove. The inner side of the rubber buffer strip is embedded in the spiral mounting groove. The outer side of the spiral mounting groove is provided with a protrusion which is higher than the protrusion of the front mounting seat and the rear mounting seat.

3. The crash-avoiding carbon fiber UAV of claim 1 or 2, wherein: A propelling motor is horizontally arranged on the rear mounting seat. A propelling propeller is arranged on the rotating shaft of the propelling motor.

4. The crash-avoiding carbon fiber UAV of claim 1 or 2, wherein: A foot support mounting protrusion is integrally arranged at each corner of the hollow lower support. A rotating mounting groove is arranged on the front end surface or the rear end surface of the foot support mounting protrusion to extend horizontally to the middle part of the side surface of the fuselage. The fixed end of the foot support is rotatably arranged in the rotating mounting groove.

5. The crash-avoiding carbon fiber UAV of claim 1 or 2, wherein: The number of branches is six.

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