Combination and locking structure of a cellular flying aircraft carrier

Abstract

The utility model provides a kind of combination and locking structure of honeycomb type flight aircraft carrier belongs to aircraft technical field, the combination and locking structure of this honeycomb type flight aircraft carrier includes honeycomb type aircraft body, the honeycomb type aircraft body includes flight platform, brushless motor and flight rotary wing, the flight platform is regular hexagon structure, four evenly distributed circular through holes are provided on flight platform, the lower bottom surface of flight platform is fixed with annular motor support, the center of circle of motor support coincides with the geometric center of flight platform, the diameter circle of annular motor support passes through the center of circle of circular through hole, brushless motor is fixed on motor support, flight rotary wing is connected on brushless motor, multiple honeycomb type aircraft bodies are connected by combination and locking structure to form modular, expandable honeycomb type aircraft carrier large platform in side and side mutual alignment mode;The utility model can solve the problem of poor adaptability to severe weather existing in current unmanned aerial vehicle.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft technology, specifically, it relates to a combination and locking structure for a honeycomb-type flying aircraft carrier. Background Technology

[0002] The applications of monolithic drones have expanded from logistics and agriculture to military, rescue, and surveillance. However, the monolithic design makes it difficult to adapt to these complex scenarios, leading to inefficiency and amplified risks. The advantages of monolithic drones include self-decision-making, autonomous flight, automatic rescue capabilities, and wide deployment. For example, in streets, communities, towns, and villages, any "pole" (power pole, base station, streetlight, traffic light, camera) with mains power can be deployed to mount a monolithic drone, enabling 24 / 7 surveillance of the area. However, monolithic drones are small and cannot carry large amounts of rescue supplies, which is a disadvantage. Furthermore, monolithic drones exhibit significant sensitivity and instability in adverse weather conditions such as wind, rain, snow, and fog, making them prone to loss of control or crashes, limiting their effectiveness in complex environments. Monolithic drones typically struggle to cope with strong winds, such as wind speeds exceeding 8 m / s, as airflow disturbances can cause attitude instability, leading to deviations from their intended flight path or crashes. Utility Model Content

[0003] In view of this, the present invention provides a combination and locking structure for a honeycomb-type flying carrier, which can solve the problem of poor adaptability of existing UAVs to severe weather.

[0004] This utility model is implemented as follows: This utility model provides a combination and locking structure for a honeycomb-type flying aircraft carrier, including a honeycomb-type aircraft body. The honeycomb-type aircraft body includes a flight platform, a brushless motor, and a flight rotor. The flight platform has a regular hexagonal structure with four evenly distributed circular through holes. A circular motor bracket is fixed on the lower surface of the flight platform, with the center of the motor bracket coinciding with the geometric center of the flight platform. The median diameter of the circular motor bracket passes through the center of the circular through holes. A brushless motor is fixed on the motor bracket, and a flight rotor is connected to the brushless motor. Multiple honeycomb-type aircraft bodies are assembled and locked together in a side-to-side alignment manner through the combination and locking structure to form a modular and expandable honeycomb-type aircraft carrier platform.

[0005] The technical advantages of the honeycomb-type flying aircraft carrier assembly and locking structure provided by this utility model are as follows: The regular hexagonal structure facilitates honeycomb splicing, improving the overall platform's stability and expandability. Similar to the natural structure of a honeycomb, it can evenly distribute weight and stress, avoiding single-point failures. The four evenly distributed through holes and the circular motor bracket optimize the center of gravity balance, ensuring stable flight of the aircraft and reducing vibration and energy consumption.

[0006] The regular hexagon is a classic shape found in natural honeycombs, offering the highest space utilization and structural stability. By aligning and splicing edge-to-edge, multiple hexagonal aircraft form a honeycomb-like two-dimensional network, maximizing contact area and evenly distributing weight and stress. This geometric optimization ensures that the aircraft carrier platform possesses superior torsional and shear resistance during flight, similar to how a honeycomb withstands external pressures in nature. The honeycomb concept allows for the combination of an unlimited number of aircraft, with each aircraft acting as a "cell" within the honeycomb, dynamically added or removed according to mission requirements.

[0007] Honeycomb splicing integrates the power of each aircraft into a unified output through a combination and locking structure. A single aircraft may have limited load capacity, but multiple aircraft spliced ​​together can accumulate a large lifting force. This synergistic effect is similar to the collective cooperation of bees in a honeycomb; the individual capabilities of each bee are limited, but the collective forms a powerful whole.

[0008] The honeycomb-like hexagonal array forms a rigid structure, similar to the hexagonal grid of a honeycomb, which resists deformation. This design can withstand severe weather such as strong winds and heavy rain in the air. Compared to single drones, which are more susceptible to environmental influences, the honeycomb platform maintains flight stability through distributed power and multi-point locking.

[0009] Based on the above technical solution, the combination and locking structure of the honeycomb-type flying aircraft carrier of this utility model can be further improved as follows: The combination and locking structure includes a guide component and an energized coil. The guide component is located on the side wall of the flight platform and includes a guide block and a docking slot. The guide block and docking slot are alternately arranged on the six sides of the flight platform.

[0010] The beneficial effects of adopting the above-mentioned improved scheme are as follows: the alternating arrangement of guide blocks and docking slots simplifies the docking process, ensures that each aircraft side has a complementary interface, and improves the docking success rate and efficiency. Combined with energized coils, mechanical guidance and electromagnetic locking are integrated, enhancing locking strength. The alternating arrangement ensures the relative weight balance of various parts of the cellular aircraft body.

[0011] Furthermore, the guide block has a frustum-shaped structure and is compatible with the docking groove.

[0012] The beneficial effects of adopting the above-mentioned improvement scheme are: the guide block and the docking groove are compatible with each other, so as to achieve precise matching of the guide block insertion into the docking groove.

[0013] Furthermore, a silicone buffer pad is installed at the entrance of the docking groove to absorb the impact force during aerial docking and prevent metal collision damage.

[0014] The beneficial effects of adopting the above-mentioned improved solution are as follows: the silicone buffer pad has high elasticity and temperature resistance, which can effectively buffer high-speed docking impacts, extend component life, and reduce maintenance costs. It also prevents damage and ensures the reliability of the aircraft during repeated assembly and deployment. Furthermore, the entrance of the docking groove is designed with an arc shape to guide the guide block in.

[0015] The beneficial effects of adopting the above-mentioned improvement scheme are as follows: the arc-shaped entrance expands the entrance's fault tolerance range, making aerial docking smoother and reducing the probability of jamming or failure. Combined with a silicone buffer pad, safety is further enhanced.

[0016] Furthermore, the guiding components are made of ferromagnetic materials.

[0017] The beneficial effects of adopting the above-mentioned improved scheme are as follows: the guide cone is made of ferromagnetic material such as iron or nickel alloy, which will be attracted and fixed by the magnetic field after entering the docking groove. The high magnetic permeability of the ferromagnetic material enhances the electromagnetic locking effect, ensuring a firm fixation after insertion. At the same time, the material has high strength and corrosion resistance, making it suitable for outdoor environments.

[0018] Furthermore, an energized coil is provided in the inner wall of the docking groove. The energized coil includes a first coil and a second coil, which are symmetrically arranged. Both the first coil and the second coil are located at the groove opening.

[0019] The beneficial effects of adopting the above-mentioned improved scheme are: the symmetrical layout forms a uniform closed magnetic field, improving the stability of the adsorption force; combined with ferromagnetic materials, rapid locking can be achieved.

[0020] Furthermore, both the first and second coils are made of copper wire.

[0021] The beneficial effects of adopting the above-mentioned improvement scheme are: the copper wire has low resistance, high conductivity, good heat resistance and can withstand 10-20A current, ensuring that the coil generates a strong magnetic field efficiently, reducing energy consumption, and the winding design can optimize the magnetic force output.

[0022] Furthermore, a resistive touch sensor is installed at the bottom of the docking groove, and the resistive touch sensor is electrically connected to the energized coil.

[0023] The advantages of adopting the above-mentioned improvement scheme are: the resistive sensor has high sensitivity, a response time of less than 0.1 seconds, low cost, and resistance to environmental interference, ensuring automatic locking without the need for complex control.

[0024] Furthermore, a mechanical micro-motion touch sensor is installed at the bottom of the docking groove, and the mechanical micro-motion touch sensor is electrically connected to the energized coil.

[0025] The advantages of adopting the above-mentioned improved scheme are as follows: the mechanical micro-motion sensor is simple and reliable, with a lifespan of >100,000 cycles, no energy consumption dependence, and resistance to electromagnetic interference, ensuring that it can still be triggered in power outages or harsh environments. Compared with resistive sensors, it provides a backup option and improves system redundancy.

[0026] Compared with existing technologies, the beneficial effects of the honeycomb-type flying carrier assembly and locking structure provided by this utility model are as follows: through edge-to-edge alignment and splicing, multiple hexagonal aircraft form a honeycomb-like two-dimensional network, maximizing the contact area and evenly distributing weight and stress. This geometric optimization ensures that the large aircraft carrier platform has excellent torsional and shear resistance during flight, similar to how a honeycomb withstands external pressure in nature. The honeycomb concept allows for the combination of an unlimited number of aircraft, with each aircraft acting as a "cell" in the honeycomb, which can be dynamically added or removed according to mission requirements. The honeycomb splicing integrates the power of each aircraft into a unified output through the assembly and locking structure. While a single aircraft may have a limited load, the splicing of multiple aircraft can accumulate a large lifting force. The hexagonal array of the honeycomb splicing forms a rigid structure, similar to the deformation resistance of the hexagonal grid in a honeycomb. This design can withstand severe weather interference such as strong winds and heavy rain in the air. Compared with single unmanned aerial vehicles that are easily affected by the environment, the honeycomb platform maintains flight stability through distributed power and multi-point locking. Attached Figure Description

[0027] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments of this utility model 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.

[0028] Figure 1 A schematic diagram of the combination and locking structure of a honeycomb-type flying aircraft carrier; Figure 2 This is a schematic diagram of a honeycomb-type flying aircraft carrier platform with a combination and locking structure. Figure 3 A schematic diagram of the docking slot for a honeycomb-type flying aircraft carrier's combination and locking structure; The attached diagram lists the components represented by each number as follows: 10. Cellular aircraft body; 11. Flight platform; 12. Brushless motor; 13. Flight rotor; 20. Guiding assembly; 21. Guiding block; 22. Docking slot; 30. Powered coil; 31. First coil; 32. Second coil. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings.

[0030] like Figure 1-3 The illustration shows an embodiment of the combination and locking structure of a honeycomb-type flying aircraft carrier provided by this utility model. In this embodiment, it includes a honeycomb-type aircraft body 10, which includes a flight platform 11, a brushless motor 12, and a flight rotor 13. The flight platform 11 has a regular hexagonal structure and four evenly distributed circular through holes. A circular motor bracket is fixed on the bottom surface of the flight platform 11, with the center of the motor bracket coinciding with the geometric center of the flight platform 11. The middle diameter of the circular motor bracket passes through the center of the circular through holes. A brushless motor 12 is fixed on the motor bracket, and a flight rotor 13 is connected to the brushless motor 12. Multiple honeycomb-type aircraft bodies 10 are spliced ​​together in a side-to-side alignment manner through the combination and locking structure to form a modular and expandable honeycomb-type aircraft carrier platform.

[0031] In the above technical solution, the combination and locking structure includes a guide component 20 and an energized coil 30. The guide component 20 is disposed on the side wall of the flight platform 11. The guide component 20 includes a guide block 21 and a docking groove 22. The guide block 21 and the docking groove 22 are alternately disposed on the six sides of the flight platform 11.

[0032] Furthermore, in the above technical solution, the guide block 21 has a frustum-shaped structure and is adapted to the docking groove 22.

[0033] Furthermore, in the above technical solution, a silicone buffer pad is provided at the inlet of the docking groove 22 to absorb the impact force during aerial docking and prevent metal collision damage.

[0034] Furthermore, in the above technical solution, the entrance of the docking groove 22 is set with an arc-shaped structure to guide the guide block 21 into the groove.

[0035] Furthermore, in the above technical solution, the guiding component 20 is made of ferromagnetic material. Furthermore, in the above technical solution, an energized coil 30 is disposed in the inner wall of the docking groove 22. The energized coil 30 includes a first coil 31 and a second coil 32, which are symmetrically arranged. Both the first coil 31 and the second coil 32 are located at the groove opening.

[0036] The energized coil 30 is electrically connected to the battery integrated inside the flight platform 11.

[0037] Furthermore, in the above technical solution, both the first coil 31 and the second coil 32 are made of copper wire.

[0038] Furthermore, in the above technical solution, a resistive touch sensor is provided at the bottom of the docking groove 22, and the resistive touch sensor is electrically connected to the energized coil 30.

[0039] Furthermore, in the above technical solution, a mechanical micro-motion touch sensor is provided at the bottom of the docking groove 22, and the mechanical micro-motion touch sensor is electrically connected to the energized coil 30.

[0040] Two adjacent honeycomb-shaped aircraft approach each other, their targets assembling to form a honeycomb platform, with initial side alignment. A guide block enters the docking slot; the guide ramp and buffer layer absorb the impact. Once fully inserted into the bottom of the contact slot, the guide block triggers the touch sensor, closing the coil circuit and initiating a lock. The first coil, acting as the positive terminal, and the second coil, acting as the negative terminal, are energized, generating a closed magnetic field that attracts the ferromagnetic guide block, completing the lock. Sensors ensure automatic triggering, and the coils provide strong locking force to prevent detachment due to air vibrations or wind. Multiple aircraft repeat this process, assembling side-to-side to form a small honeycomb platform. After the mission is completed, the aircraft separate and are redeployed. Control disconnects the sensor circuit, de-energizes the coils, and the magnetic force disappears. The aircraft then separate from each other.

[0041] Here is a specific implementation 2: A forest fire breaks out and spreads rapidly, requiring the urgent evacuation of trapped personnel and rescue equipment. Traditional drones are inefficient at lifting due to limited payload and strong winds. The aircraft are grouped and coordinated via wireless communication. Adjacent aircraft adjust their attitudes to align the guide blocks with corresponding docking slots. The brushless motor and rotor maintain a relative speed of <3m / s, the circular motor bracket ensures stable flight, and through-holes reduce weight and energy consumption. Once the guide block is fully inserted, it triggers a resistive touch sensor, closing the circuit. The first and second coils are energized, generating a 20N magnetic force that attracts the ferromagnetic guide block, locking it in less than 0.5 seconds. Ten aircraft are sequentially assembled to form a small honeycomb platform. The honeycomb structure withstands strong winds, allowing the platform to fly to a safe area.

[0042] Specifically, the principle of this invention is as follows: the combination and locking structure of the honeycomb flying carrier is based on a comprehensive principle of hexagonal geometry, mechanical guidance, and electromagnetic locking. The hexagonal platform supports modular assembly, the guiding components achieve highly fault-tolerant alignment, and the energized coils and sensors provide rapid locking. The overall structure forms a stable and expandable platform similar to a natural honeycomb, accumulating load capacity and resisting harsh environments, making it particularly suitable for emergency rescue and overcoming the limitations of traditional UAVs in terms of limited payload and remote control delay.

[0043] 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 scope of the claims.

Claims

1. A combination and locking structure for a honeycomb-type flying aircraft carrier, comprising a honeycomb-type aircraft body (10), the honeycomb-type aircraft body (10) comprising a flight platform (11), a brushless motor (12) and a flight rotor (13), the flight platform (11) being a regular hexagonal structure, having four evenly distributed circular through holes on the flight platform (11), a circular motor bracket fixed on the lower surface of the flight platform (11), the center of the motor bracket coinciding with the geometric center of the flight platform (11), the median diameter of the circular motor bracket passing through the center of the circular through holes, a brushless motor (12) fixed on the motor bracket, and a flight rotor (13) connected to the brushless motor (12); characterized in that, Multiple honeycomb aircraft bodies (10) are spliced ​​together in a side-to-side alignment manner through a combination and locking structure to form a modular and expandable honeycomb aircraft carrier platform; the combination and locking structure includes a guide component (20) and an energized coil (30). The guide component (20) is set on the side wall of the flight platform (11). The guide component (20) includes a guide block (21) and a docking slot (22). The guide block (21) and the docking slot (22) are alternately arranged on the six sides of the flight platform (11); An energized coil (30) is provided in the inner wall of the docking groove (22). The energized coil (30) includes a first coil (31) and a second coil (32). The first coil (31) and the second coil (32) are symmetrically arranged, and both the first coil (31) and the second coil (32) are located at the groove opening.

2. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 1, characterized in that, The guide block (21) has a frustum-shaped structure and is compatible with the docking groove (22).

3. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 2, characterized in that, A silicone buffer pad is provided at the entrance of the docking groove (22) to absorb the impact force during aerial docking and prevent metal collision damage.

4. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 3, characterized in that, The entrance of the docking groove (22) is set with an arc-shaped structure to guide the guide block (21) into the groove.

5. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 4, characterized in that, The guide component (20) is made of ferromagnetic material.

6. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 5, characterized in that, Both the first coil (31) and the second coil (32) are made of copper wire.

7. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 6, characterized in that, A resistive touch sensor is provided at the bottom of the docking groove (22), and the resistive touch sensor is electrically connected to the energized coil (30).

8. The combination and locking structure of a honeycomb-type flying aircraft carrier according to claim 6, characterized in that, A mechanical micro-motion touch sensor is provided at the bottom of the docking groove (22), and the mechanical micro-motion touch sensor is electrically connected to the energized coil (30).

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