A drone with impact resistance

Abstract

This invention discloses an impact-resistant drone, relating to the field of drone technology. It includes a drone body, an impact-resistant mechanism, a fixing rod, a detection mechanism, and an adjustment mechanism. The impact-resistant mechanism is fixedly connected to all four sides of the drone body's outer wall. A fixing rod is fixedly connected to the center of the top of the drone body, and a detection mechanism is fixedly connected to the top of the fixing rod. Two sets of adjustment mechanisms are fixedly connected to the bottom of the drone body. The impact-resistant mechanism improves the shock and impact resistance of the drone body and propellers, reducing the impact of vibration on internal precision components and ensuring stable operation. Simultaneously, it reduces damage to the fuselage and components through deformation buffering and energy absorption, improving equipment safety and survivability. The detection mechanism uses four sets of rotating laser rangefinders to perform multi-directional obstacle detection and transmits distance information to an external display screen, providing data support for obstacle avoidance decisions and preventing collisions.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV with impact resistance capabilities. Background Technology

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

[0003] Drones generate continuous vibrations during flight and takeoff and landing. Existing technologies make it difficult to reduce the impact of vibrations on internal precision components and ensure stable operation of the equipment. Furthermore, in the event of takeoff and landing errors, collisions with obstacles, or sudden crashes, it is difficult for some equipment to reduce damage to the fuselage and components through deformation buffering and energy absorption, thereby improving equipment safety and survivability. The practicality of drones is relatively limited.

[0004] Finally, existing technologies have difficulty accurately sensing the distance and location of obstacles around drones, making it difficult to provide data support for obstacle avoidance decisions and avoid collision accidents, thus limiting their practicality. During use, existing drones have difficulty adapting to ground with different flatness, slope, or obstacle distribution, making it difficult to ensure the stability of the drone during takeoff and landing, increasing the risk of tipping over or collisions. Summary of the Invention

[0005] Therefore, in order to overcome the above-mentioned shortcomings, the present invention provides a drone with impact resistance.

[0006] The present invention is implemented as follows: a drone with impact resistance is constructed. The device includes a drone body, and impact resistance mechanisms are fixedly connected to all four sides of the outer wall of the drone body. A fixed rod is fixedly connected to the center of the top of the drone body, and a detection mechanism is fixedly connected to the top of the fixed rod. Two sets of adjustment mechanisms are fixedly connected to the bottom of the drone body.

[0007] The impact-resistant mechanism includes a propeller mounting position. Propeller mounting positions are fixedly connected to all four sides of the outer wall of the drone body. A fuselage tube is fixedly connected inside the drone body, and a fuselage connector is fixedly connected inside the fuselage tube.

[0008] Preferably, the propeller mounting position includes a first thin-walled sandwich tube, and the first thin-walled sandwich tube is fixedly connected to all four sides of the outer wall of the UAV body, and the first thin-walled sandwich tube is filled with a first superchiral tube.

[0009] Preferably, the fuselage tubing includes a second thin-walled sandwich tube, which is fixedly connected to the UAV body, and the second thin-walled sandwich tube is filled with a second superchiral tube.

[0010] Preferably, the body connector includes a positive-hand connector, and a negative-hand connector is fixedly connected to the side of the positive-hand connector. Both the positive-hand connector and the negative-hand connector are fixedly connected to the body tubing.

[0011] Preferably, the detection mechanism includes a mounting box, with the mounting box fixedly connected to the top of the fixing rod. A motor is fixedly connected to the center of the top of the mounting box, the bottom output shaft of the motor is fixedly connected to the front end of the top of the cam, and a connecting rod is fixedly connected to the rear end of the bottom of the cam. A connecting seat is fixedly connected to the bottom of the connecting rod, and four sets of rotating rods are rotatably connected inside the connecting seat. A sliding block is rotatably connected to the outer wall of the rotating rod, and the outer side of the sliding block is fixedly connected to the inner gear plate of the gear plate component. A laser rangefinder is fixedly connected to the inner gear of the gear plate component through a gear rod.

[0012] Preferably, the adjustment mechanism includes shock-absorbing rubber pads, two sets of shock-absorbing rubber pads are fixedly connected to the bottom of the drone body, a mounting rod is fixedly connected to the bottom of the shock-absorbing rubber pads, the bottom of the mounting rod is slidably connected to the outer wall of the sliding rod, a fixed seat is fixedly connected to the bottom of the sliding rod, a roller is rotatably connected inside the fixed seat, and five sets of electromagnetic blocks are fixedly connected inside the mounting rod.

[0013] Preferably, the bottom of the sliding block is slidably connected to the bottom of the mounting box, the bottom of the inner tooth plate of the gear tooth plate is slidably connected to the bottom of the mounting box, and the laser rangefinder is electrically connected to the external display screen.

[0014] Preferably, the bottom of the gear inside the gear plate is rotatably connected to the bottom of the mounting box, and the gear rod inside the gear plate passes through the top of the mounting box and is rotatably connected to its interior.

[0015] Preferably, the electromagnetic block is electrically connected to an external current output device, and the electromagnetic block is magnetically attracted to the sliding rod.

[0016] Preferably, the outer wall of the fuselage tube is fixedly connected with propeller mounting positions on all four sides, and the fuselage connector is provided with eight sets.

[0017] The present invention has the following advantages: The present invention provides an improved drone with impact resistance, which, compared with similar devices, has the following improvements:

[0018] This invention discloses an unmanned aerial vehicle (UAV) with shock resistance. It incorporates an shock-resistant mechanism to enhance the vibration and impact resistance of the UAV's fuselage and propellers, reducing the impact of vibrations on internal precision components and ensuring stable operation. Simultaneously, deformation buffering and energy absorption reduce damage to the fuselage and components, improving equipment safety and survivability. A detection mechanism is also included, using four sets of rotating laser rangefinders to perform multi-directional obstacle detection and transmit distance information to an external display screen, providing data support for obstacle avoidance decisions and preventing collisions. Finally, an adjustment mechanism is provided, using rollers to move up or down to adapt to different ground surfaces, slopes, or obstacle distributions, ensuring stability during takeoff and landing and reducing the risk of tipping over or collisions. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the three-dimensional structure of the UAV body of the present invention;

[0020] Figure 2 This is a three-dimensional structural diagram of the impact-resistant mechanism of the present invention;

[0021] Figure 3 This is a three-dimensional exploded view of the propeller mounting position of the present invention;

[0022] Figure 4 This is a three-dimensional exploded structural diagram of the fuselage tubing of the present invention;

[0023] Figure 5 This is an enlarged structural diagram of point A in the fuselage connector of the present invention;

[0024] Figure 6 This is an exploded structural diagram of the fuselage connector of the present invention;

[0025] Figure 7 This is a three-dimensional exploded view of the detection mechanism of the present invention;

[0026] Figure 8 This is a three-dimensional exploded view of the adjustment mechanism of the present invention;

[0027] Figure 9 This is a three-dimensional exploded view of the internal structure of the mounting rod of the present invention.

[0028] The components include: UAV body-1, impact-resistant mechanism-2, propeller mounting position-21, fuselage tubing-22, fuselage connector-23, first thin-walled sandwich tube-211, first super-chiral tube-212, second thin-walled sandwich tube-221, second super-chiral 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 tooth 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 Implementation

[0029] The following is in conjunction with the appendix Figures 1-9 The principles and features of the present invention are described below. The examples given are for illustrative purposes only and are not intended to limit the scope of the invention. The invention is described more specifically in the following paragraphs by way of example with reference to the accompanying drawings. It should be noted that the drawings are in a very simplified form and use non-precise proportions, and are only used to facilitate and clarify the illustration of the embodiments of the invention.

[0030] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the 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.

[0031] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. The embodiments of this invention will now be described according to its overall structure.

[0032] Example 1:

[0033] Please see Figures 1-6The present invention provides an anti-impact drone, comprising a drone body 1, an anti-impact mechanism 2 fixedly connected to all four sides of the outer wall of the drone body 1, a fixed rod 3 fixedly connected to the center of the top of the drone body 1, a detection mechanism 4 fixedly connected to the top of the fixed rod 3, and two sets of adjustment mechanisms 5 fixedly connected to the bottom of the drone body 1.

[0034] The impact-resistant mechanism 2 includes a propeller mounting position 21. Propeller mounting positions 21 are fixedly connected to all four sides of the outer wall of the UAV body 1. A fuselage tube 22 is fixedly connected inside the UAV body 1. A fuselage connector 23 is fixedly connected inside the fuselage tube 22. The fuselage tube 22 facilitates the installation and fixation of the fuselage connector 23.

[0035] The outer walls of the drone body 1 are all fixedly connected with a first thin-walled sandwich tube 211, and the first thin-walled sandwich tube 211 is filled with a first super-chiral tube 212. The drone body 1 is fixedly connected with a second thin-walled sandwich tube 221. The first thin-walled sandwich tube 211 facilitates the installation and fixation of the first super-chiral tube 212.

[0036] The second thin-walled sandwich tube 221 is filled with a second super-chiral tube 222. The positive-chiral connector 231 is fixedly connected to the side of the negative-chiral connector 232. Both the positive-chiral connector 231 and the negative-chiral connector 232 are 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. The fuselage connector 23 is provided with eight sets.

[0037] The working principle of an impact-resistant drone based on Embodiment 1 is as follows:

[0038] First, when using this device, place it in the work area, and then connect it to an external power source to provide the power required for its operation.

[0039] Secondly, during use, the first super-chiral tube 212, filled with the first thin-walled sandwich tube 211 inside the propeller mounting position 21, improves the shock and impact resistance of the propeller of the UAV body 1. Then, the second super-chiral tube 222, filled with the second thin-walled sandwich tube 221 inside the fuselage tube 22, improves the shock and impact resistance of the fuselage of the UAV body 1. Finally, the light weight, shock resistance, and impact resistance of the positive-chiral connector 231 and the negative-chiral connector 232 further improve the shock and impact resistance of the fuselage of the UAV 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, improving the safety and survivability of the equipment.

[0040] Example 2:

[0041] Please see Figure 7 The present invention provides an anti-impact drone, which, compared with the first embodiment, further includes a detection mechanism 4. The detection mechanism 4 includes a mounting box 41. The mounting box 41 is fixedly connected to the top of the fixing rod 3. A motor 42 is fixedly connected to the center of the top of the mounting box 41. The bottom output shaft of the motor 42 is fixedly connected to the front end of the top of the cam 43. The motor 42 can easily drive the cam 43 to rotate.

[0042] A connecting rod 44 is fixedly connected to the bottom rear end of the cam 43. A connecting seat 45 is fixedly connected to the bottom of the connecting rod 44. Four sets of rotating rods 46 are rotatably connected inside the connecting seat 45. A sliding block 47 is rotatably connected to the outer wall of the rotating rod 46. The connecting rod 44 facilitates the swinging of the connecting seat 45.

[0043] The outer side of the sliding block 47 is fixedly connected to the inner gear plate of the gear tooth plate 48. The inner gear of the gear tooth plate 48 is fixedly connected to the laser rangefinder 49 through the gear rod. The bottom of the sliding block 47 is slidably connected to the bottom of the mounting box 41. The bottom of the inner gear plate of the gear tooth plate 48 is slidably connected to the bottom of the mounting box 41. The laser rangefinder 49 facilitates the detection of the distance to obstacles.

[0044] The laser rangefinder 49 is electrically connected to an external display screen. The bottom of the gear inside the gear plate 48 is rotatably connected to the bottom of the mounting box 41. The gear rod inside the gear plate 48 passes through the top of the mounting box 41 and is rotatably connected to its interior.

[0045] In this embodiment:

[0046] When obstacle detection is required, motor 42 is started, which drives cam 43 to rotate. Cam 43 drives connecting seat 45 to swing through connecting rod 44. Connecting seat 45 drives four sets of sliding blocks 47 to move through rotational connection with four sets of rotating rods 46. The four sets of sliding blocks 47 drive the internal gear plates of four sets of gear plates 48 to move. The internal gear plates of four sets of gear plates 48 drive the internal gears of four sets of gear plates 48 to rotate. The internal gears of four sets of gear plates 48 drive the four sets of laser rangefinders 49 to rotate through four sets of gear rods. The rotation of the four sets of laser rangefinders 49 performs multi-directional detection of obstacles and transmits distance information to an external display screen, providing data support for obstacle avoidance decisions and avoiding collision accidents.

[0047] Example 3:

[0048] Please see Figures 8-9The present invention provides an anti-impact drone, which, compared to embodiment one, further includes an adjustment mechanism 5. The adjustment mechanism 5 includes shock-absorbing rubber pads 51. Two sets of shock-absorbing rubber pads 51 are fixedly connected to the bottom of the drone body 1. An installation rod 52 is fixedly connected to the bottom of the shock-absorbing rubber pads 51. The bottom of the installation rod 52 is slidably connected to the outer wall of the sliding rod 53. A fixed seat 54 is fixedly connected to the bottom of the sliding rod 53. A roller 55 is rotatably connected inside the fixed seat 54. Five sets of electromagnetic blocks 56 are fixedly connected inside the installation rod 52. The electromagnetic blocks 56 are electrically connected to an external current output device. The electromagnetic blocks 56 are magnetically attracted to the sliding rod 53.

[0049] In this embodiment:

[0050] During use, the UAV body 1 drives five sets of electromagnetic blocks 56 to work in stages through an external current output device. This causes the sliding rod 53 to move up or down due to the magnetic attraction of the five sets of electromagnetic blocks 56. The sliding rod 53 drives the fixed base 54 to move up or down, and the fixed base 54 drives the roller 55 to move up or down. The upward or downward movement of the roller 55 adapts to different flatness, slope or obstacle distribution on the ground, ensuring the stability of the aircraft during takeoff and landing and reducing the risk of tipping over or collision. In addition, the roller 55 absorbs vibration through the shock-absorbing rubber pad 51 during use.

[0051] This invention provides an improved drone with impact resistance. An impact-resistant mechanism 2 enhances the shock and impact resistance of the drone body 1 and propellers, reducing the impact of vibrations on internal precision components and ensuring stable operation. Simultaneously, deformation buffering and energy absorption reduce damage to the body and components, improving equipment safety and survivability. A detection mechanism 4 uses four sets of rotating laser rangefinders 49 to perform multi-directional obstacle detection and transmit distance information to an external display screen, providing data support for obstacle avoidance decisions and preventing collisions. An adjustment mechanism 5 uses rollers 55 to move up or down to adapt to different flatness, slope, or obstacle distribution on the ground, ensuring stability during takeoff and landing and reducing the risk of tipping over or collisions.

[0052] The above description shows and illustrates the basic principles, main features, and advantages of the present invention. Standard parts used in the present invention can be purchased from the market, and irregular parts can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts, and equipment adopt conventional models in the prior art, and the circuit connection adopts conventional connection methods in the prior art, which will not be described in detail here.

[0053] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those 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 invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An unmanned aerial vehicle (UAV) with impact resistance function, comprising a UAV body (1), wherein an impact resistance mechanism (2) is fixedly connected to all four sides of the outer wall of the UAV body (1), a fixed rod (3) is fixedly connected to the center of the top of the UAV body (1), a detection mechanism (4) is fixedly connected to the top of the fixed rod (3), and two sets of adjustment mechanisms (5) are fixedly connected to the bottom of the UAV body (1). Its features are: The impact-resistant mechanism (2) includes a propeller mounting position (21). Propeller mounting positions (21) are fixedly connected to all four sides of the outer wall of the UAV body (1). A fuselage tube (22) is fixedly connected inside the UAV body (1). A fuselage connector (23) is fixedly connected inside the fuselage tube (22). The propeller mounting position (21) includes a first thin-walled sandwich tube (211). The first thin-walled sandwich tube (211) is fixedly connected to the outer wall of the UAV body (1) on all four sides. The first thin-walled sandwich tube (211) is filled with a first super-chiral tube (212). The fuselage tube (22) includes a second thin-walled sandwich tube (221), and the second thin-walled sandwich tube (221) is fixedly connected inside the UAV body (1). The second thin-walled sandwich tube (221) is filled with a second super-chiral tube (222). The fuselage connector (23) includes a positive-hand connector (231), and a negative-hand connector (232) is fixedly connected to the side of the positive-hand connector (231). Both the positive-hand connector (231) and the negative-hand connector (232) are fixedly connected to the fuselage tube (22).

2. The unmanned aerial vehicle with impact resistance according to claim 1, characterized in that: The detection mechanism (4) includes a mounting box (41). The mounting box (41) is fixedly connected to the top of the fixing rod (3). A motor (42) is fixedly connected to the center of the top of the mounting box (41). The bottom output shaft of the motor (42) is fixedly connected to the front end of the top of the cam (43). A connecting rod (44) is fixedly connected to the rear end of the bottom of the cam (43). A connecting seat (45) is fixedly connected to the bottom of the connecting rod (44). Four sets of rotating rods (46) are rotatably connected inside the connecting seat (45). A sliding block (47) is rotatably connected to the outer wall of the rotating rod (46). The outer side of the sliding block (47) is fixedly connected to the inner gear plate of the gear plate component (48). A laser rangefinder (49) is fixedly connected to the gear inside the gear plate component (48) through a gear rod.

3. The unmanned aerial vehicle with impact resistance according to claim 2, characterized in that: The adjustment mechanism (5) includes shock-absorbing rubber pads (51). Two sets of shock-absorbing rubber pads (51) are fixedly connected to the bottom of the UAV body (1). An installation rod (52) is fixedly connected to the bottom of the shock-absorbing rubber pads (51). The bottom of the installation rod (52) is slidably connected to the outer wall of the sliding rod (53). A fixed seat (54) is fixedly connected to the bottom of the sliding rod (53). A roller (55) is rotatably connected inside the fixed seat (54). Five sets of electromagnetic blocks (56) are fixedly connected inside the installation rod (52).

4. The unmanned aerial vehicle with impact resistance according to claim 3, characterized in that: The bottom of the sliding block (47) is slidably connected to the bottom of the mounting box (41), the bottom of the gear plate (48) is slidably connected to the bottom of the mounting box (41), and the laser rangefinder (49) is electrically connected to the external display screen.

5. The unmanned aerial vehicle with impact resistance according to claim 4, characterized in that: The bottom of the gear inside the gear plate (48) is rotatably connected to the bottom of the mounting box (41), and the gear rod inside the gear plate (48) passes through the top of the mounting box (41) and is rotatably connected to its interior.

6. The unmanned aerial vehicle with impact resistance according to claim 5, 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).

7. The unmanned aerial vehicle with impact resistance according to claim 6, characterized in that: The outer wall of the fuselage tube (22) is fixedly connected with propeller mounting positions (21) on all four sides, and the fuselage connector (23) is provided with eight sets.

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