An unmanned aerial vehicle with automatic structure righting

Abstract

The utility model provides a structure automatic right -handed unmanned plane, including unmanned plane body, the top fixed mounting of unmanned plane body has the support column, the top fixed mounting of support column has the support pad, the inside of unmanned plane body is provided with drive power, the outside of unmanned plane body is provided with through -hole, the outside of unmanned plane body is provided with right -handed subassembly, the outside fixed mounting of right -handed subassembly has the connecting rod. That structure automatic right -handed unmanned plane, through setting right -handed subassembly, has guaranteed no matter unmanned plane turns over to which direction right -handed, can start corresponding right -handed subassembly to carry out attitude adjustment rapidly, has improved the success rate and response speed of automatic right -handed greatly, has improved operation efficiency and reliability, the support column of inclined structure provides the stable support foundation with annular triangle distribution and symmetric setting mode, can effectively disperse fuselage weight, strengthens the stability of ground contact, guarantees normal operation of each component.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV with an automatic structural uprighting mechanism. Background Technology

[0002] With the continuous development of drone technology, drones have been widely used in aerial photography, logistics delivery, environmental monitoring, and agricultural plant protection. Today, drones demonstrate outstanding value in many fields. In aerial photography, their flexible and maneuverable flight characteristics allow them to reach locations that are difficult for traditional shooting equipment to access. In logistics delivery, they improve delivery efficiency and reduce logistics costs. In environmental monitoring, drones can collect multi-dimensional data on air, water quality, and soil in real time, helping environmental protection departments to keep abreast of environmental changes. In agricultural plant protection, drones can accurately spray pesticides, sow seeds, and apply fertilizers, effectively improving agricultural production efficiency. In actual use, drones may be affected by factors such as airflow disturbances, collisions with obstacles, and power system failures, leading to loss of flight attitude or even rollover. Therefore, there is a particular need for a drone with an automatic tilting mechanism.

[0003] However, existing drones lack effective automatic righting mechanisms when they encounter sudden changes in airflow, collisions with obstacles, or power system failures that cause them to lose control or even flip over. They can only rely on manual remote control or waiting for the drone to crash, which not only increases the difficulty and risk of operation, but also easily causes equipment damage, mission interruption, and economic losses. Traditional drones mostly use simple upright support columns or tripods, which are prone to tipping over when encountering uneven ground or minor external impacts. It is difficult to effectively reduce the shaking of the fuselage, which may cause damage to internal components due to vibration, affecting the service life and flight safety of the drone. This results in low righting efficiency and low success rate, making it difficult to meet the needs of complex and ever-changing actual application scenarios, and causing serious damage to the fuselage and onboard equipment. Utility Model Content

[0004] The purpose of this invention is to provide a drone with an automatic tilting mechanism to solve the problem mentioned in the background art. When existing drones encounter sudden changes in airflow, collisions with obstacles, or power system failures that cause loss of attitude control or even rollover, they lack an effective automatic tilting mechanism. They can only rely on manual remote control or waiting for the drone to crash, which not only increases the difficulty and risk of operation, but also easily causes equipment damage, mission interruption, and economic losses. Traditional drones mostly use simple upright support columns or tripods. When encountering uneven ground or slight external impacts, the drone is prone to tipping over, making it difficult to effectively reduce the shaking of the fuselage. This may cause damage to internal components due to vibration, affecting the service life and flight safety of the drone, resulting in low tilting efficiency and low success rate, making it difficult to meet the needs of complex and ever-changing actual application scenarios, and causing serious damage to the fuselage and onboard equipment.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an automatically uprighting drone, comprising a drone body, a support column fixedly mounted on the top of the drone body, a support pad fixedly mounted on the top of the support column, a drive power supply provided inside the drone body, a through hole opened on the outer side of the drone body, an uprighting component provided on the outer side of the drone body, a connecting rod fixedly mounted on the outer side of the uprighting component, the uprighting component including a mounting arm, the mounting arm mounted on the outer side of the drone body, a mounting hole opened on the outer side of the mounting arm, a rotating shaft rotatably mounted on the inner side of the mounting arm, a connecting power block fixedly mounted on the outer side of the rotating shaft, a rotating column rotatably connected to the top of the connecting power block, and an mounting wing fixedly mounted on the outer side of the rotating column.

[0006] Preferably, the support column has an inclined structure, and the support column and support pad are provided in three identical sets, with the three sets of support columns and support pads arranged in a ring-shaped triangular distribution on the top of the UAV body.

[0007] Preferably, two of the three sets of support columns and support pads are identical, and the two sets of support columns and support pads are symmetrically distributed about the horizontal center line of the UAV body.

[0008] Preferably, the righting components and through holes are provided in multiple identical sets, and the multiple sets of righting components and through holes are located on the outside of the UAV body in a ring distribution.

[0009] Preferably, both the through hole and the mounting hole are adapted to the rotating shaft, and the drive power supply is fixedly connected to the rotating shaft.

[0010] Preferably, multiple identical sets of connecting rods are provided, the connecting rods are located between two sets of mounting arms, and the connecting rods are fixedly connected to the mounting arms.

[0011] Preferably, the mounting wings are provided in multiple identical sets, and the multiple sets of mounting wings are arranged in a ring outside the rotating column.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows: The UAV with automatic flipping structure is equipped with a flipping component. When the UAV flips, the drive power supply can control the rotating shaft to rotate, thereby driving the connecting power block, rotating column and mounting wing to rotate. This ensures that no matter which direction the UAV flips, the corresponding flipping component can be quickly activated to adjust the attitude, greatly improving the success rate and response speed of automatic flipping. In the event of sudden weather conditions such as strong winds, once the UAV flips, it can achieve rapid automatic flipping by its own structure, greatly reducing the need for manual intervention and improving operational efficiency and reliability. At the same time, the inclined support column, distributed in a ring-triangular pattern and symmetrically arranged, provides a stable support foundation, which can effectively distribute the weight of the fuselage, enhance the stability of contact with the ground, avoid tipping over due to uneven ground or slight external impact, reduce fuselage sway, ensure the normal operation of each component, and reduce the risk of failure caused by attitude instability. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the three-dimensional structure of the present invention. Figure 1 ;

[0014] Figure 2 This is a schematic diagram of the three-dimensional structure of the present invention. Figure 2 ;

[0015] Figure 3 This is a schematic diagram of the three-dimensional disassembled structure of this utility model;

[0016] Figure 4 This is a schematic diagram of the disassembled structure of the uprighting component of this utility model.

[0017] In the diagram: 1. UAV body; 2. Support column; 3. Support pad; 4. Drive power supply; 5. Through hole; 6. Flip-up assembly; 601. Mounting arm; 602. Mounting hole; 603. Rotating shaft; 604. Connecting power block; 605. Rotating column; 606. Mounting wing; 7. Connecting rod. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] Please see Figure 1-4This utility model provides a technical solution: an automatically uprighting drone, comprising a drone body 1, a support column 2 fixedly mounted on the top of the drone body 1, a support pad 3 fixedly mounted on the top of the support column 2, a drive power supply 4 disposed inside the drone body 1, a through hole 5 opened on the outer side of the drone body 1, an uprighting component 6 disposed on the outer side of the drone body 1, a connecting rod 7 fixedly mounted on the outer side of the uprighting component 6, the uprighting component 6 including a mounting arm 601, the mounting arm 601 being mounted on the outer side of the drone body 1, a mounting hole 602 opened on the outer side of the mounting arm 601, a rotating shaft 603 rotatably mounted on the inner side of the mounting arm 601, and a connecting rod 7 fixedly mounted on the outer side of the rotating shaft 603. A power supply block 604 is connected to a rotating column 605, which is rotatably connected to the top of the power supply block 604. An mounting wing 606 is fixedly installed on the outer side of the rotating column 605. By setting up a righting component 6, when the drone flips, the drive power supply can control the rotating shaft to rotate, thereby driving the power supply block, rotating column and mounting wing to rotate. This ensures that no matter which direction the drone flips, the corresponding righting component can be quickly activated to adjust its attitude, which greatly improves the success rate and response speed of automatic righting. In the event of sudden weather conditions such as strong winds, once the drone flips, it can achieve rapid automatic righting by its own structure, which greatly reduces the need for manual intervention and improves operational efficiency and reliability.

[0020] Furthermore, the support column 2 has an inclined structure, and there are three identical sets of support columns 2 and support pads 3. The three sets of support columns 2 and support pads 3 are located on the top of the UAV body 1 in a ring-triangular distribution. By setting three sets of support columns 2 and support pads 3 on the top of the UAV body 1 in a ring-triangular distribution, the force can be evenly transmitted to each support point, effectively avoiding tipping due to excessive local force. The ring-triangular distribution support structure can automatically adapt to the ground undulation by adjusting the force on each support column 2, maintaining the balance of the fuselage. Even when encountering a slight collision or wind, it can maintain its own attitude by relying on this stable structure, which greatly enhances the stability and safety of the UAV when parked on the ground.

[0021] Furthermore, two identical sets of the three sets of support columns 2 and support pads 3 are provided, and the two sets of support columns 2 and support pads 3 are symmetrically distributed about the horizontal center line of the UAV body 1. By setting two sets of support columns 2 and support pads 3 symmetrically distributed about the horizontal center line of the UAV body 1, it can be ensured that the fuselage is subjected to uniform force, effectively reducing the swaying and displacement of the fuselage caused by uneven force. The symmetrical support structure can also provide additional support force for the fuselage, helping the UAV to maintain a stable attitude for inspection, replacement and debugging, thereby improving the maintenance efficiency and service life of the UAV.

[0022] Furthermore, the same multiple sets of the righting component 6 and the through hole 5 are provided, and the multiple sets of righting component 6 and through hole 5 are arranged in a ring on the outside of the UAV body 1. By setting multiple sets of righting component 6 and through hole 5 in a ring on the outside of the UAV body 1, and the number of through holes 5 is the same as that of righting component 6 and they are arranged in a ring, sufficient space and support points are provided for the installation and rotation of the rotating shaft 603, ensuring the stability and reliability of the righting component 6 during the rotation process, and greatly improving the success rate and fault tolerance of the UAV's automatic righting.

[0023] Furthermore, both the through hole 5 and the mounting hole 602 are adapted to the rotating shaft 603. The drive power supply 4 is fixedly connected to the rotating shaft 603. By setting the through hole 5 and the mounting hole 602, the drive power supply 4 is fixedly connected to the rotating shaft 603, enabling the drive power supply 4 to directly provide power to the rotating shaft 603. This reduces energy loss and delay during power transmission and improves the response speed of the righting component 6. When the UAV attitude detection system detects a flip signal, the drive power supply 4 can quickly transmit power to the rotating shaft 603, enabling the righting component 6 to start and function in the shortest possible time. This ensures that the UAV can restore its normal attitude as soon as possible and enhances the UAV's self-rescue capability in emergency situations.

[0024] Furthermore, multiple identical sets of connecting rods 7 are provided. The connecting rods 7 are located between two sets of mounting arms 601, and the connecting rods 7 are fixedly connected to the mounting arms 601. By setting the connecting rods 7 between two sets of mounting arms 601, and connecting multiple sets of connecting rods 7 to adjacent mounting arms 601, the overall strength and rigidity of the uprighting component 6 are greatly enhanced, the accuracy of the uprighting operation is improved, the structural integrity and reliability of the uprighting component 6 are guaranteed, and a solid structural guarantee is provided for the automatic uprighting function of the UAV.

[0025] Furthermore, the mounting wings 606 are provided in multiple identical sets, and these multiple sets of mounting wings 606 are arranged in a ring on the outside of the rotating column 605. By setting multiple sets of mounting wings 606 in a ring on the outside of the rotating column 605, the mounting wings 606 can assist the main flight wing in providing lift, optimize the aerodynamic performance of the UAV, improve flight efficiency and stability, realize the organic combination of the righting function and flight performance, and improve the overall performance and practicality of the UAV.

[0026] Working Principle: First, the operator places the drone body 1 stably on a clean, flat workbench, ensuring there are no obstructions. Using specialized tools, the three sets of inclined support columns 2 are bolted to the top of the drone body 1 in a ring-triangular arrangement. During installation, the angles must be strictly calibrated to ensure consistent inclination of the support columns 2, guaranteeing subsequent support stability. Support pads 3 are then installed on top of the support columns 2, ensuring they are secure and have a flat surface. Multiple connecting rods 7 are then securely connected between adjacent sets of mounting arms 601, ensuring a firm connection. An open, unobstructed area with few people is selected as the flight zone to ensure flight safety. The ground condition is checked, avoiding areas that are too soft or... Taking off and landing on uneven ground, a comprehensive inspection of the drone's appearance is conducted. This includes checking for damage or loosening of support columns 2 and support pads 3, ensuring the connections of all components in the righting assembly 6 are secure, and verifying the connecting rod 7 is not deformed. The power supply 4 is checked to ensure sufficient charge to meet the expected flight time requirements. Using professional testing equipment, a rapid test of the drone's flight control and attitude detection systems is performed to ensure normal system operation. The drone is then placed smoothly at the takeoff point, ensuring full contact between support columns 2 and support pads 3 and the ground. A takeoff command is sent via the ground control terminal, activating the drone's power system and starting the propellers. Once the drone has stably ascended to a safe altitude, it begins its flight mission along the preset route. When the drone encounters turbulence... When a sudden change or collision with an obstacle causes the drone to flip, its attitude detection system quickly transmits a signal to the drive power supply 4. The drive power supply 4 immediately controls the rotation of the rotating shaft 603, causing the connecting power block 604, rotating column 605, and mounted wing 606 to rotate. The mounted wing 606 interacts with the air to generate a righting torque. During the righting process, the attitude detection system continuously monitors the drone's attitude. When it detects that the drone has returned to a normal attitude, it sends a stop signal to the drive power supply 4. The drive power supply 4 then controls the righting assembly 6 to stop working. When the drone completes its flight mission or needs to land early, it sends a landing command through the ground control terminal. The drone then reduces its altitude and slowly descends to the ground. During the landing process... Support column 2 and support pad 3 serve as buffers and stabilizers to ensure a smooth landing of the drone. After landing, turn off the drone's power and conduct a comprehensive inspection. Check for wear or damage to support column 2 and support pad 3, looseness, deformation, or damage to each component of the righting assembly 6, and the firmness of the connecting rod 7. Clean the drone's surface of dust and debris to prevent dust accumulation from affecting component performance. Charge or replace the drive power supply 4 to ensure sufficient power for the next flight. If any faulty or damaged components are found during the inspection, repair or replace them promptly to ensure normal performance after repair. After repair, perform system debugging and flight testing again to ensure the drone can operate normally.

[0027] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model.

Claims

1. A type of unmanned aerial vehicle (UAV) with automatic structural uprighting, comprising a UAV body (1), characterized in that: A support column (2) is fixedly installed on the top of the drone body (1), and a support pad (3) is fixedly installed on the top of the support column (2). A drive power supply (4) is provided inside the drone body (1). A through hole (5) is opened on the outside of the drone body (1). A flipping component (6) is provided on the outside of the drone body (1), and a connecting rod (7) is fixedly installed on the outside of the flipping component (6). The righting assembly (6) includes a mounting arm (601), which is mounted on the outside of the UAV body (1). The mounting arm (601) has a mounting hole (602) on its outside. A rotating shaft (603) is rotatably mounted on the inside of the mounting arm (601). A power connection block (604) is fixedly mounted on the outside of the rotating shaft (603). A rotating column (605) is rotatably connected to the top of the power connection block (604). A mounting wing (606) is fixedly mounted on the outside of the rotating column (605).

2. The UAV with automatic structural uprighting according to claim 1, characterized in that: The support column (2) has an inclined structure. The support column (2) and the support pad (3) are provided in three identical sets, and the three sets of support columns (2) and support pads (3) are located on the top of the UAV body (1) in a ring-shaped triangular distribution.

3. The UAV with automatic structural uprighting according to claim 2, characterized in that: The three sets of support columns (2) and support pads (3) are provided in two identical sets, and the two sets of support columns (2) and support pads (3) are symmetrically distributed about the horizontal center line of the UAV body (1).

4. The UAV with automatic structural uprighting according to claim 1, characterized in that: The righting component (6) and the through hole (5) are provided in multiple sets, and the multiple sets of the righting component (6) and the through hole (5) are located on the outside of the UAV body (1) in a ring distribution.

5. The UAV with automatic structural uprighting according to claim 1, characterized in that: The through hole (5) and the mounting hole (602) are both adapted to the rotating shaft (603), and the driving power supply (4) is fixedly connected to the rotating shaft (603).

6. The UAV with automatic structural uprighting according to claim 1, characterized in that: The connecting rod (7) is provided in multiple identical sets, and the connecting rod (7) is located between two sets of mounting arms (601). The connecting rod (7) and the mounting arms (601) are fixedly connected.

7. The UAV with automatic structural uprighting according to claim 1, characterized in that: The mounting wings (606) are provided in multiple identical sets, and the multiple sets of mounting wings (606) are located in a ring distribution outside the rotating column (605).

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