Unmanned aerial vehicle with anti-impact function

Abstract

The invention discloses an unmanned aerial vehicle with an anti-impact function, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle comprises an unmanned aerial vehicle body, anti-impact mechanisms, a fixing rod, a detection mechanism and an adjusting mechanism, the anti-impact mechanisms are fixedly connected to the periphery of the outer wall of the unmanned aerial vehicle body, and the fixing rod is fixedly connected to the center of the top of the unmanned aerial vehicle body; a detection mechanism is fixedly connected to the top of the fixing rod, two adjusting mechanisms are fixedly connected to the bottom of the unmanned aerial vehicle body, an anti-impact mechanism is arranged, the shock resistance and impact resistance of a fuselage and propellers of the unmanned aerial vehicle body are improved, the influence of shock on internal precise elements is reduced, and stable operation of equipment is guaranteed; meanwhile, damage to the machine body and parts is reduced through deformation buffering and energy absorption, and the safety and survivability of the equipment are improved; the detection mechanism is arranged, the obstacles are detected in multiple directions through rotation of the four laser range finders, distance information is transmitted to an external display screen, data support is provided for obstacle avoidance decision making, and collision accidents are avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a UAV with an anti-shock function. Background Art

[0002] A drone is an aircraft that does not require a pilot on board and flies through remote control, autonomous program control or artificial intelligence decision-making.

[0003] Drones generate continuous vibrations during flight and takeoff and landing. Existing technologies have difficulty reducing the impact of vibrations on internal precision components and ensuring stable operation of the equipment. Furthermore, when drones experience takeoff and landing errors, collide with obstacles, or crash suddenly, some equipment struggles to reduce damage to the fuselage and components through deformation cushioning and energy absorption, thereby improving equipment safety and survivability. Consequently, their practicality is relatively limited. Finally: Existing technologies make it difficult to accurately perceive the distance and direction of obstacles around drones, making it difficult to provide data support for obstacle avoidance decisions and avoid collision accidents, and their practicality is relatively limited; during use, existing drones find it difficult to adapt to ground with different flatness, slopes or obstacle distributions, making it difficult to ensure the stability of the fuselage during takeoff and landing, increasing the risk of rollover or collision. Summary of the Invention

[0004] Therefore, in order to solve the above-mentioned shortcomings, the present invention provides a UAV with impact resistance function.

[0005] The present invention is achieved by constructing a drone with an impact resistance function, the device comprising a drone body, wherein the outer wall of the drone body is fixedly connected to an impact resistance mechanism on all four sides, a fixing rod is fixedly connected to the top center of the drone body, a detection mechanism is fixedly connected to the top of the fixing rod, and two sets of adjustment mechanisms are fixedly connected to the bottom of the drone body; The anti-shock mechanism includes a propeller mounting position, and the propeller mounting positions are fixedly connected to the outer wall of the UAV body on all four sides. The UAV body is fixedly connected to a fuselage pipe, and the fuselage pipe is fixedly connected to a fuselage connector.

[0006] Preferably, the propeller mounting position includes a first thin-walled sandwich tube, and the outer wall of the drone body is fixedly connected to the first thin-walled sandwich tube on all four sides, and the first thin-walled sandwich tube is filled with a first superchiral tube.

[0007] Preferably, the fuselage tube includes a second thin-walled sandwich tube, the second thin-walled sandwich tube is fixedly connected to the drone body, and the second thin-walled sandwich tube is filled with a second superchiral tube.

[0008] Preferably, the fuselage connector includes a positive-hand connector, and a negative-hand connector is fixedly connected to the side of the positive-hand connector, and the positive-hand connector and the negative-hand connector are both fixedly connected to the fuselage pipe.

[0009] Preferably, the detection mechanism includes an installation box, the top of the fixed rod is fixedly connected to the installation box, the top center of the installation box is fixedly connected to a motor, the bottom output shaft of the motor is fixedly connected to the front end of the top of the cam, the bottom rear end of the cam is fixedly connected to a connecting rod, the bottom of the connecting rod is fixedly connected to a connecting seat, four groups of rotating rods are rotatably connected in the connecting seat, the outer wall of the rotating rod is rotatably connected to a sliding block, the outer side of the sliding block is fixedly connected to the inner gear plate of the gear tooth plate, and the inner gear of the gear tooth plate is fixedly connected to a laser rangefinder through a gear rod.

[0010] Preferably, the adjustment mechanism includes a shock-absorbing rubber pad, two groups of shock-absorbing rubber pads are fixedly connected to the bottom of the drone body, the bottom of the shock-absorbing rubber pad is fixedly connected to a mounting rod, the bottom of the mounting rod is slidably connected to the outer wall of the sliding rod, the bottom of the sliding rod is fixedly connected to a fixing seat, a roller is rotatably connected in the fixing seat, and five groups of electromagnetic blocks are fixedly connected in the mounting rod.

[0011] Preferably, the bottom of the sliding block is slidably connected to the bottom of the installation box, the bottom of the inner gear plate of the gear tooth plate is slidably connected to the bottom of the installation box, and the laser rangefinder is electrically connected to an external display screen.

[0012] Preferably, the bottom of the gear inside the gear plate is rotatably connected to the bottom of the installation box, and the gear rod inside the gear plate passes through the top of the installation box and is rotatably connected to the inside thereof.

[0013] Preferably, the electromagnetic block is electrically connected to an external current output device, and the electromagnetic block is magnetically attracted to the sliding rod.

[0014] Preferably, propeller mounting positions are fixedly connected to the outer wall of the fuselage tube on all four sides, and there are eight groups of fuselage connecting parts.

[0015] The present invention has the following advantages: The present invention provides a UAV with impact resistance through improvement, which has the following improvements compared with similar devices: The present invention provides a drone with an impact resistance function. The drone is provided with an impact resistance mechanism. By improving the seismic and impact resistance of the drone body and propellers, the impact of vibration on internal precision components is reduced, thereby ensuring stable operation of the equipment. At the same time, damage to the fuselage and components is reduced through deformation buffering and energy absorption, thereby improving the safety and survivability of the equipment. A detection mechanism is provided. By rotating four sets of laser rangefinders, obstacles are detected from all directions, and the distance information is transmitted to an external display screen to provide data support for obstacle avoidance decisions and avoid collision accidents. An adjustment mechanism is provided. By moving the rollers upward or downward to adapt to ground surfaces with different flatness, slopes or obstacle distributions, the drone is ensured to be stable during takeoff and landing, thereby reducing the risk of rollover or collision. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the three-dimensional structure of the drone body of the present invention; Figure 2 It is a schematic diagram of the three-dimensional structure of the anti-impact mechanism of the present invention; Figure 3 This is a schematic diagram of the three-dimensional exploded structure of the propeller installation position of the present invention; Figure 4 This is a schematic diagram of the three-dimensional exploded structure of the fuselage pipe of the present invention; Figure 5 It is an enlarged structural diagram of point A in the fuselage connecting member of the present invention; Figure 6 It is a schematic diagram of the exploded structure of the fuselage connecting member of the present invention; Figure 7 It is a schematic diagram of the three-dimensional decomposition structure of the detection mechanism of the present invention; Figure 8 This is a schematic diagram of the three-dimensional exploded structure of the adjustment mechanism of the present invention; Figure 9 It is a schematic diagram of the internal three-dimensional exploded structure of the mounting rod of the present invention.

[0017] The components include: drone body 1, impact-resistant mechanism 2, propeller mounting position 21, fuselage pipe 22, fuselage connector 23, first thin-walled sandwich tube 211, first superchiral tube 212, second thin-walled sandwich tube 221, second superchiral tube 222, positive chiral connector 231, negative chiral connector 232, fixing rod 3, detection mechanism 4, mounting box 41, motor 42, cam 43, connecting rod 44, connecting seat 45, rotating rod 46, sliding block 47, gear plate 48, laser rangefinder 49, adjustment mechanism 5, shock-absorbing rubber pad 51, mounting rod 52, sliding rod 53, fixing seat 54, roller 55, and electromagnetic block 56. DETAILED DESCRIPTION

[0018] The following is combined with Figures 1 to 9The principles and features of the present invention are described, and the examples given are only for the purpose of explaining the present invention and are not intended to limit the scope of the present invention. The following paragraphs describe the present invention in more detail by way of example with reference to the accompanying drawings. It should be noted that the drawings are all in a very simplified form and are not to exact scale, and are only used for the purpose of conveniently and clearly assisting in illustrating the embodiments of the present invention.

[0019] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0020] In the description of the present invention, it should be noted that, unless otherwise clearly specified or limited, the terms "installed," "connected," "connected," and "set" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium, or they can refer to internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances. The following describes an embodiment of the present invention based on its overall structure.

[0021] Example 1:

[0022] See also Figures 1 to 6 The present invention provides a drone with anti-impact function, including a drone body 1, with anti-impact mechanisms 2 fixedly connected to the outer wall of the drone body 1 on all four sides, a fixing rod 3 fixedly connected to the top center of the drone body 1, a detection mechanism 4 fixedly connected to the top of the fixing rod 3, and two sets of adjustment mechanisms 5 fixedly connected to the bottom of the drone body 1.

[0023] The anti-impact mechanism 2 includes a propeller mounting position 21, and the propeller mounting positions 21 are fixedly connected to the outer wall of the drone body 1 on all four sides. A fuselage pipe 22 is fixedly connected inside the drone body 1, and a fuselage connector 23 is fixedly connected inside the fuselage pipe 22. The fuselage pipe 22 facilitates the installation and fixation of the fuselage connector 23.

[0024] A first thin-walled sandwich tube 211 is fixedly connected to the outer wall of the drone body 1 on all sides. The first thin-walled sandwich tube 211 is filled with a first superchiral tube 212. A second thin-walled sandwich tube 221 is fixedly connected to the drone body 1. The first thin-walled sandwich tube 211 facilitates the installation and fixation of the first superchiral tube 212.

[0025] The second thin-walled sandwich tube 221 is filled with a second superchiral tube 222. The side of the positive chiral connector 231 is fixedly connected to the reverse chiral connector 232. The positive chiral connector 231 and the reverse chiral connector 232 are both fixedly connected to the fuselage tube 22. The outer wall of the fuselage tube 22 is fixedly connected to the propeller mounting position 21 on all four sides. There are eight groups of fuselage connectors 23.

[0026] The working principle of the UAV with impact resistance function according to the first embodiment is as follows: First, when using this device, first place the device in the working area, then connect the device to an external power source to provide the power required for the device to work; Second, during use of the drone body 1, the first superchiral tube 212 filled in the first thin-walled sandwich tube 211 in the propeller mounting position 21 has light weight and is resistant to shock and vibration, thereby improving the vibration and vibration resistance of the propeller of the drone body 1. Furthermore, the second superchiral tube 222 filled in the second thin-walled sandwich tube 221 in the fuselage tube 22 has light weight and is resistant to shock and vibration, thereby improving the vibration and vibration resistance of the drone body 1. Finally, the light weight and vibration and vibration resistance of the positive and negative chiral connectors 231 and 232 further improve the vibration and vibration resistance of the drone body 1, reducing the impact of vibration on internal precision components and ensuring stable operation of the equipment. At the same time, deformation buffering and energy absorption reduce damage to the fuselage and components, thereby improving the safety and survivability of the equipment.

[0027] Example 2:

[0028] See also Figure 7 Compared with the first embodiment, the present invention provides a drone with an impact resistance function. The present embodiment further includes: a detection mechanism 4, which includes an installation box 41. The top of the fixing rod 3 is fixedly connected to the installation box 41. The center of the top of the installation box 41 is fixedly connected to a motor 42. The output shaft at the bottom of the motor 42 is fixedly connected to the top front end of the cam 43. The motor 42 is convenient for driving the cam 43 to rotate.

[0029] The rear end of the bottom of the cam 43 is fixedly connected to a connecting rod 44, and the bottom of the connecting rod 44 is fixedly connected to a connecting seat 45. Four groups of rotating rods 46 are rotatably connected in the connecting seat 45, and the outer wall of the rotating rod 46 is rotatably connected to a sliding block 47. The connecting rod 44 facilitates driving the connecting seat 45 to swing.

[0030] The outer side of the sliding block 47 is fixedly connected to the inner gear plate of the gear tooth plate part 48, and the inner gear of the gear tooth plate part 48 is fixedly connected to the laser rangefinder 49 through a gear rod. The bottom of the sliding block 47 is slidably connected to the bottom of the installation box 41, and the bottom of the inner gear plate of the gear tooth plate part 48 is slidably connected to the bottom of the installation box 41. The laser rangefinder 49 facilitates the detection of the distance to obstacles.

[0031] The laser rangefinder 49 is electrically connected to the external display screen, the bottom of the gear in the gear plate 48 is rotatably connected to the bottom of the installation box 41, and the gear rod in the gear plate 48 passes through the top of the installation box 41 and is rotatably connected to the inside thereof.

[0032] In this embodiment: When it is necessary to detect an obstacle, the motor 42 is started, and the motor 42 drives the cam 43 to rotate. The cam 43 drives the connecting seat 45 to swing through the connecting rod 44. The connecting seat 45 drives the four sets of sliding blocks 47 to move through the rotation connection with the four sets of rotating rods 46. The four sets of sliding blocks 47 drive the four sets of inner gear plates of the gear tooth plate parts 48 to move. The four sets of inner gear plates of the gear tooth plate parts 48 drive the four sets of inner gears of the gear tooth plate parts 48 to rotate. The four sets of inner gears of the gear tooth plate parts 48 drive the four sets of laser rangefinders 49 to rotate through the four sets of gear rods. The obstacles are detected in multiple directions through the rotation of the four sets of laser rangefinders 49, and the distance information is transmitted to the external display screen to provide data support for obstacle avoidance decisions and avoid collision accidents.

[0033] Example 3:

[0034] See also Figures 8 and 9 Compared with the first embodiment, the present invention provides a drone with an impact resistance function. The present embodiment further includes: an adjustment mechanism 5, which includes a shock-absorbing rubber pad 51. Two groups of shock-absorbing rubber pads 51 are fixedly connected to the bottom of the drone body 1. The bottom of the shock-absorbing rubber pad 51 is fixedly connected to a mounting rod 52. The bottom of the mounting rod 52 is slidably connected to the outer wall of the sliding rod 53. The bottom of the sliding rod 53 is fixedly connected to a fixing seat 54. A roller 55 is rotatably connected to the fixing seat 54. Five groups of electromagnetic blocks 56 are fixedly connected to the mounting rod 52. The electromagnetic blocks 56 are electrically connected to the external current output device. The electromagnetic blocks 56 are magnetically adsorbed to the sliding rod 53.

[0035] In this embodiment: During use, the drone body 1 drives the five groups of electromagnetic blocks 56 to work step by step through an external current output device, so that the sliding rod 53 moves upward or downward under the influence of the magnetic adsorption of the five groups of electromagnetic blocks 56, and the sliding rod 53 drives the fixing seat 54 to move upward or downward, and the fixing seat 54 drives the roller 55 to move upward or downward. The upward or downward movement of the roller 55 adapts to the ground with different flatness, slope or obstacle distribution, ensuring the stability of the fuselage during take-off and landing, reducing the risk of rollover or collision, and the roller 55 absorbs vibration during use through the shock-absorbing rubber pad 51.

[0036] The present invention provides an improved drone with an impact-resistant function. An impact-resistant mechanism 2 is provided to improve the seismic and impact resistance of the drone body 1 and propellers, reduce the impact of vibration on internal precision components, ensure stable operation of the equipment, and reduce damage to the fuselage and components through deformation buffering and energy absorption, thereby improving the safety and survivability of the equipment; a detection mechanism 4 is provided to perform multi-directional detection of obstacles through the rotation of four groups of laser rangefinders 49, and transmit the distance information to an external display screen, providing data support for obstacle avoidance decisions and avoiding collision accidents; an adjustment mechanism 5 is provided to adapt to ground surfaces of different flatness, slopes or obstacle distributions through the upward or downward movement of a roller 55, thereby ensuring the stability of the fuselage during takeoff and landing and reducing the risk of rollover or collision.

[0037] The above shows and describes the basic principles, main features and advantages of the present invention, and the standard parts used in the present invention can be purchased from the market, and special-shaped parts can be customized according to the description in the specification and the drawings. The specific connection methods of each part adopt conventional means such as mature bolts, rivets, welding, etc. in the existing technology. The machinery, parts and equipment all adopt conventional models in the existing technology, and the circuit connection adopts the conventional connection method in the existing technology, which will not be described in detail here.

[0038] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A drone with an anti-shock function, comprising a drone body (1), wherein the outer wall of the drone body (1) is fixedly connected to anti-shock mechanisms (2) on all sides, a fixing rod (3) is fixedly connected to the center of the top of the drone body (1), a detection mechanism (4) is fixedly connected to the top of the fixing rod (3), and two sets of adjustment mechanisms (5) are fixedly connected to the bottom of the drone body (1); Its characteristics are: The anti-shock mechanism (2) includes a propeller mounting position (21), the propeller mounting positions (21) are fixedly connected to the outer wall of the UAV body (1) on all sides, the UAV body (1) is fixedly connected to a fuselage pipe (22), and the fuselage pipe (22) is fixedly connected to a fuselage connector (23).

2. The UAV with shock resistance according to claim 1, characterized in that: The propeller mounting position (21) comprises a first thin-walled sandwich tube (211), and the outer wall of the drone body (1) is fixedly connected to the first thin-walled sandwich tube (211) on all four sides, and the first thin-walled sandwich tube (211) is filled with a first superchiral tube (212).

3. The UAV with shock resistance according to claim 2, characterized in that: The fuselage tube (22) comprises a second thin-walled sandwich tube (221), the second thin-walled sandwich tube (221) is fixedly connected to the inside of the drone body (1), and the second thin-walled sandwich tube (221) is filled with a second superchiral tube (222).

4. The UAV with shock resistance according to claim 3, characterized in that: The fuselage connecting member (23) comprises a positive chirality connecting member (231), a negative chirality connecting member (232) is fixedly connected to the side of the positive chirality connecting member (231), and both the positive chirality connecting member (231) and the negative chirality connecting member (232) are fixedly connected to the fuselage pipe (22).

5. The UAV with shock resistance according to claim 4, characterized in that: The detection mechanism (4) comprises a mounting box (41), the top of the fixed rod (3) is fixedly connected to the mounting box (41), the center of the top of the mounting box (41) is fixedly connected to a motor (42), the bottom output shaft of the motor (42) is fixedly connected to the front end of the top of the cam (43), the bottom rear end of the cam (43) is fixedly connected to a connecting rod (44), the bottom of the connecting rod (44) is fixedly connected to a connecting seat (45), four groups of rotating rods (46) are rotatably connected in the connecting seat (45), the outer wall of the rotating rod (46) is rotatably connected to a sliding block (47), the outer side of the sliding block (47) is fixedly connected to the inner gear plate of the gear tooth plate member (48), and the inner gear of the gear tooth plate member (48) is fixedly connected to a laser rangefinder (49) through a gear rod.

6. The UAV with shock resistance according to claim 5, characterized in that: The adjustment mechanism (5) includes a shock-absorbing rubber pad (51), two groups of shock-absorbing rubber pads (51) are fixedly connected to the bottom of the drone body (1), a mounting rod (52) is fixedly connected to the bottom of the shock-absorbing rubber pad (51), the bottom of the mounting rod (52) is slidably connected to the outer wall of the sliding rod (53), the bottom of the sliding rod (53) is fixedly connected to a fixing seat (54), a roller (55) is rotatably connected inside the fixing seat (54), and five groups of electromagnetic blocks (56) are fixedly connected inside the mounting rod (52).

7. The UAV with shock resistance according to claim 6, characterized in that: The bottom of the sliding block (47) is slidably connected to the bottom of the installation box (41), the bottom of the inner tooth plate of the gear tooth plate member (48) is slidably connected to the bottom of the installation box (41), and the laser rangefinder (49) is electrically connected to an external display screen.

8. The UAV with shock resistance according to claim 7, characterized in that: The bottom of the gear inside the gear tooth plate (48) is rotatably connected to the bottom inside the installation box (41), and the gear rod inside the gear tooth plate (48) passes through the top of the installation box (41) and is rotatably connected to the inside thereof.

9. The UAV with shock resistance according to claim 8, characterized in that: The electromagnetic block (56) is electrically connected to an external current output device, and the electromagnetic block (56) is magnetically attracted to the sliding rod (53).

10. The UAV with shock resistance according to claim 9, characterized in that: The outer wall of the fuselage pipe (22) is fixedly connected with propeller mounting positions (21) on all four sides, and the fuselage connecting parts (23) are provided with eight groups.

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