Detection device for unmanned aerial vehicle mounting

Abstract

The invention discloses a detection device for unmanned aerial vehicle mounting, and relates to the technical field of unmanned aerial vehicle detection, and the detection device comprises an unmanned aerial vehicle main body, fan blades, a support rod, a camera and a risk-avoiding landing unit; the danger-avoiding landing unit comprises a placing box, a fixed plate, a triggering mechanism, a parachute, a movable plate and a spring II; the containing box is of a cover-free box-shaped structure and is fixed to the middle of the top end of the unmanned aerial vehicle body in a clamped mode, and a cover plate used for sealing the containing box is arranged on the top of the containing box. The fixed plate is fixed in the middle of the placement box; the trigger mechanism is fixed in the placement box and is used for automatically triggering release of the parachute when the unmanned aerial vehicle is collided by external force; the movable plate is slidably connected into the containing box through the second spring and located above the fixed plate. The parachute is stacked above the moving plate and used for releasing the parachute after being triggered, and buffering power is provided for the unmanned aerial vehicle body; the technical effects of structure simplification, production difficulty reduction, risk avoiding operation simplification, safety performance improvement and detection efficiency improvement can be realized.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle detection, and in particular to a detection device for mounting an unmanned aerial vehicle. Background Art

[0002] With the rapid development of UAV technology, UAVs are increasingly used in various fields, especially in terrain detection, environmental monitoring, agricultural plant protection, power inspection, etc., showing great potential. However, UAVs still face many challenges when performing tasks, especially in complex and changing environments. Terrain detection is one of the important applications of UAVs, which requires UAVs to be able to perform efficient and accurate detection under various terrain conditions.

[0003] A Chinese invention patent with announcement number CN112776983B discloses an aerospace drone terrain detection device, including a drone body, a plurality of fan blades are arranged on the top of the drone body, a plurality of support rods are fixedly connected to the bottom of the drone body, and elastic support feet are installed at the bottom ends of the plurality of support rods; when the invention loses the ability to fly during use, it can slowly land by parachute to avoid direct crash, and the paint sprinkled in the air can be used to facilitate its positioning and recovery, and the airbag can be inflated synchronously during landing to protect the camera.

[0004] Although the above scheme improves the detection efficiency to a certain extent when detecting through drones, in actual use, since the risk avoidance components in the prior art are mainly embedded in the drone and have a complex structure, it is difficult to mass produce the drone. In addition, the drone cannot balance the weight on the left and right sides during the flight, resulting in uneven weight distribution, which affects the normal detection of the drone. At the same time, the existing parachute deployment method usually relies on manual remote operation or electric drive. The parachute deployment mechanism that relies on electric drive may not work properly due to circuit failure or insufficient battery power. In addition, in emergency situations such as drone collisions, the parachute may not be deployed in time due to operation delays or power outages, resulting in a direct crash of the drone, which increases the risk of drone failure and reduces detection efficiency. Summary of the invention

[0005] The present application solves the technical problems in the prior art of complex structure, great production difficulty, complex risk avoidance operation, reduced safety performance and low detection efficiency by providing a detection device for drone mounting, and achieves the technical effects of simplified structure, reduced production difficulty, simplified risk avoidance operation, improved safety performance and improved detection efficiency.

[0006] The present application provides a detection device for drone mounting, including a drone body, fan blades, a support rod, a camera and a risk avoidance landing unit; The risk avoidance landing unit comprises a placement box, a fixed plate, a trigger mechanism, a parachute, a movable plate and a spring 2; The placement box is a lidless box-shaped structure, which is fixed to the middle of the top of the drone body by snap-fitting, and has a cover plate on the top for closing the placement box, which is used to store the parachute; the fixed plate is fixed to the middle of the placement box, which is used to separate the trigger mechanism and the parachute; the trigger mechanism is fixed inside the placement box, which is used to automatically trigger the release of the parachute when the drone is hit by an external force; the movable plate is slidably connected to the inside of the placement box through spring 2 and is located above the fixed plate, which is used to eject the parachute; the parachute is stacked above the movable plate, which is used to release the parachute after being triggered, thereby providing a buffering force for the drone body.

[0007] Furthermore, a slide groove is provided on the top of the placement box, the slide groove is a tic-tac-toe structure and each intersection is provided with a groove that cooperates with the bottom of the cover plate through magnetic attraction, the slide groove is used to guide the movement of the cover plate, and the groove is used to position the cover plate and realize the closure of the parachute.

[0008] Furthermore, the storage box is made of a light and strong material, such as aluminum alloy or carbon fiber composite material, to ensure sufficient strength and reduce weight.

[0009] Furthermore, the trigger mechanism includes a flap, a trigger ball, a spring 1, a squeeze plate, an airbag 1 and an airbag 2; There are four flaps, which are evenly arranged along the circumference of the fixed plate and are hinged to the bottom of the fixed plate by torsion springs; the trigger ball is placed in the placement box and on the inner sides of the four flaps; there are four groups of spring 1, which are respectively fixed on the four inner walls of the placement box, and are used to provide elastic force for the flap to reset; there are four extrusion plates, which correspond one-to-one to each group of springs and are respectively slidably connected in the placement box by corresponding spring 1, so that when the flap is opened by the trigger ball, the trigger ball hits the extrusion plate, so that the extrusion plate squeezes airbag 1; there are four airbags 1, which correspond one-to-one to the extrusion plates and are respectively fixed inside the four side walls of the placement box; there are four airbags 2, which correspond one-to-one to airbags 1, are respectively fixed at the upper ends of the four side walls of the placement box, and are connected to the corresponding airbags 1 through internal pipes, so as to push the cover plate out of the placement box after expansion.

[0010] Furthermore, the type of gas inside the airbag one is xenon, which is used to enable the airbag one to be quickly inflated into the airbag two through the internal airway after being squeezed, so that the airbag two expands; the volume of the airbag two after inflation is 4 to 6 times the initial volume.

[0011] Furthermore, the risk avoidance landing unit also includes a flipping and unfolding mechanism, which is provided with four groups and is rotatably connected to the four inner walls of the placement box and is located under the cover plate, so as to assist the parachute in unfolding.

[0012] Furthermore, the unfolding mechanism includes a first lever, which is an L-shaped structure and one end of its horizontal section is rotatably connected to the middle of the corresponding side wall of the placement box through a torsion spring, and the other end is detachably connected to the parachute canopy. When the cover falls off, the first lever drives the parachute to flip upward under the action of the torsion spring.

[0013] Furthermore, the unfolding mechanism further comprises two groups of levers arranged vertically, which are divided into a second lever and a third lever from top to bottom; The second lever and the third lever are provided in plurality and are evenly arranged along the length direction of the corresponding side wall of the placement box. The second lever and the third lever are rotatably connected to the side wall of the placement box by a hinged manner, and the second lever and the first lever located in the middle are connected to the second lever and the third lever located in the middle by a pull rope.

[0014] Furthermore, the lengths of the first lever, the second lever and the third lever decrease sequentially from top to bottom and the numbers of the first lever, the second lever and the third lever increase sequentially from top to bottom.

[0015] Furthermore, the first lever, the second lever and the third lever are all adhered to the parachute by means of dot-shaped Velcro, and the heights of the contact points between the first lever, the second lever and the third lever and the parachute surface decrease from top to bottom, so as to ensure that all parts of the parachute can be pulled evenly and effectively.

[0016] One or more technical solutions provided in this application have at least the following technical effects or advantages: By arranging the risk avoidance landing unit as a separate individual on the outside of the UAV body, the internal structure of the UAV is simplified, making it easier to mass produce the UAV, reducing production costs and complexity, and ensuring that the weight of the left and right sides of the UAV is evenly distributed during flight, so that the UAV can fly more stably during detection, reducing detection interruptions or delays caused by risk avoidance system problems; through the trigger mechanism, the UAV can take spontaneous risk avoidance measures when forced to land by external forces, without the need for human remote operation or reliance on electric drive, so that the UAV can respond quickly in emergencies such as collisions, avoiding the problem of being unable to deploy the parachute in time due to operational delays or power outages, effectively solving the technical problems of complex structure, greater production difficulty, complex risk avoidance operation, reduced safety performance and low detection efficiency in the prior art, and achieving the technical effects of simplified structure, reduced production difficulty, simplified risk avoidance operation, improved safety performance and improved detection efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The present invention is a schematic diagram of the overall structure of a detection device for mounting on a UAV.

[0018] Figure 2 The present invention is a partial three-dimensional structural cross-sectional view of a placement box for a detection device mounted on an unmanned aerial vehicle.

[0019] Figure 3 A detection device for drone mounting according to the present invention Figure 2 Front view of .

[0020] Figure 4 The present invention is a full cross-sectional view of a placement box for a detection device mounted on an unmanned aerial vehicle.

[0021] Figure 5 The present invention is a schematic diagram of the three-dimensional structure of a placement box for a detection device mounted on an unmanned aerial vehicle.

[0022] Figure 6 A detection device for drone mounting according to the present invention Figure 5 A partial enlarged schematic diagram in the middle.

[0023] Figure 7 The present invention is a top view of a placement box for a detection device mounted on an unmanned aerial vehicle and its internal parts.

[0024] Figure 8 A detection device for drone mounting according to the present invention Figure 7 Full section view along the BB axis.

[0025] Fig. 9 The present invention is a schematic diagram of a state of a detection device mounted on a drone when a parachute is triggered to land when hit by an external object.

[0026] In the figure: 100, drone body; 110, fan blades; 120, support rod; 130, camera; 200, risk avoidance landing unit; 210, placement box; 211, slide groove; 212, groove; 213, cover plate; 201, fixed plate; 220, trigger mechanism; 222, flip plate; 223, trigger ball; 224, spring one; 225, squeeze plate; 226, airbag one; 227, airbag two; 230, parachute; 240, spring two; 250, moving plate; 260, flipping mechanism; 261, first lever; 262, second lever; 263, third lever; 264, pull rope. DETAILED DESCRIPTION

[0027] To facilitate the understanding of the present invention, the present application will be described more comprehensively below with reference to the relevant drawings; the drawings show preferred embodiments of the present invention, but the present invention can be implemented in many different forms and is not limited to the embodiments described herein; on the contrary, the purpose of providing these embodiments is to enable a more thorough and comprehensive understanding of the disclosed content of the present invention.

[0028] It should be noted that the terms “vertical”, “horizontal”, “up”, “down”, “left”, “right” and similar expressions used in this document are only for illustrative purposes and do not represent the only implementation method.

[0029] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which the present invention belongs; the terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention; the term "and / or" used herein includes any and all combinations of one or more related listed items.

[0030] See also Figure 1 , which is a schematic diagram of the overall structure of a detection device for drone mounting of the present invention; the detection device for drone mounting of the present application simplifies the internal structure of the drone by setting the risk avoidance landing unit 200 on the outside and above the drone body 100; through the mutual cooperation of the trigger ball 223, the flap 222, the squeeze plate 225, the airbag 1 226 and the airbag 2 227 in the trigger mechanism 220, the drone can take spontaneous risk avoidance measures when forced to land by external force, without the need for human remote operation or reliance on electric drive, avoiding the problem of failure to deploy the parachute 230 in time due to operation delay or power interruption; the technical effects of simplified structure, reduced production difficulty, simplified risk avoidance operation, improved safety performance and improved detection efficiency are achieved.

[0031] Embodiment 1: Figures 1 to 8 As shown, the present application discloses a detection device for drone mounting, including a drone body 100, a fan blade 110, a support rod 120, a camera 130 and a risk avoidance landing unit 200; The risk avoidance landing unit 200 includes a placement box 210, a fixed plate 201, a trigger mechanism 220, a parachute 230, a moving plate 250 and a second spring 240; The storage box 210 is a box-shaped structure without a cover, fixed to the middle of the top of the drone body 100 by snap-fitting, and has a cover plate 213 on the top for closing the storage box 210, for storing the parachute 230; The fixing plate 201 is fixed to the middle of the placement box 210 and is used to separate the trigger mechanism 220 and the parachute 230; The trigger mechanism 220 is fixed inside the placement box 210 and is used to automatically trigger the release of the parachute 230 when the drone is hit by an external force; The movable plate 250 is slidably connected to the inside of the placement box 210 through the spring 240 and is located above the fixed plate 201, and is used to eject the parachute 230; The parachute 230 is stacked on the movable plate 250 to release the parachute 230 after being triggered, thereby providing a buffer force for the drone body 100 .

[0032] A slide groove 211 is provided on the top of the placement box 210. The slide groove 211 is a tic-tac-toe structure and each intersection is provided with a groove 212 that cooperates with the bottom of the cover plate 213 through magnetic attraction. The slide groove 211 is used to guide the movement of the cover plate 213, and the groove 212 is used to position the cover plate 213 and realize the closure of the parachute 230.

[0033] The placement box 210 is made of a light and strong material, such as aluminum alloy or carbon fiber composite material, to ensure sufficient strength and reduce weight.

[0034] The trigger mechanism 220 includes a flap 222, a trigger ball 223, a spring 1 224, a pressing plate 225, an airbag 1 226 and an airbag 2 227; There are four flaps 222, which are evenly arranged along the circumference of the fixed plate 201 and are hinged to the bottom of the fixed plate 201 through torsion springs respectively; The trigger ball 223 is placed in the placement box 210 and is located inside the four flaps 222; when the drone is hit by an external force, the trigger ball 223 will open the flap 222 in the corresponding direction due to inertia; The spring 1 224 is provided in four groups, which are respectively fixed on the four inner side walls of the placement box 210, and are used to provide elastic force for the flap 222 to return to its original position; The squeezing plates 225 are provided with four, corresponding to each set of springs 224, and are slidably connected in the placement box 210 through the corresponding springs 224, so that when the flap 222 is opened by the trigger ball 223, the trigger ball 223 hits the squeezing plate 225, so that the squeezing plate 225 squeezes the airbag 226; The airbags 226 are provided in four numbers, corresponding to the extrusion plates 225 one by one, and are fixed inside the four side walls of the placement box 210 respectively; There are four airbags 227, which correspond to airbags 1 226 one by one, and are respectively fixed to the upper ends of the four side walls of the placement box 210, and are connected to the corresponding airbags 1 226 through internal pipes, so as to push the cover plate 213 out of the placement box 210 after expansion.

[0035] The type of gas inside the airbag 1 226 is xenon, which is used to enable the airbag 1 226 to be quickly inflated into the airbag 2 227 through the internal airway after being squeezed, so that the airbag 2 227 expands; the volume of the airbag 2 227 after inflation is 4 to 6 times the initial volume.

[0036] In actual operation, the steps of the embodiment of the present application are as follows: when the drone body 100 is flying normally, the trigger mechanism 220 is in a stationary state, the parachute 230 is folded and closed inside the placement box 210, and the cover plate 213 is tightly matched with the groove 212 through magnetic attraction; when the drone body 100 is hit by an external force, the trigger ball 223 opens the flap 222 in the corresponding direction due to inertia, and at this time the flap 222 violently hits the squeezing plate 225, and the squeezing plate 225 squeezes the airbag 226 after being hit, and the airbag 226 is pressed. The gas inside 26 moves to the airbag 227 through the internal pipeline and expands it. After the airbag 227 expands rapidly, it pushes the cover 213 to slide to the right along the slide groove 211, and at the same time overcomes the magnetic attraction between the cover 213 and the groove 212; finally, when the cover 213 is completely separated from the placement box 210, the spring 240 is not squeezed, and the parachute 230 bounces upward under the action of the spring 240 to achieve release. After the parachute 230 is deployed, it provides a buffer force for the drone body 100 to achieve a safe landing.

[0037] Assumption: When the obstacle hits the drone at a minimum speed of 5m / s and within a very short time of 0.01s, the impact force F of the trigger ball 223 on the flap 222 due to its own inertia = = = 50N, at this time, the trigger ball 223 pushes open the flap 222 with a force of 50N, and the flap 222 starts to rotate under the impact force, while being resisted by the torsion spring; Initially, the torsion spring constant of the flap 222 is k1 = 0.5 N·m / rad, and the torsion spring force T1 = 0; as the flap 222 rotates, the torsion spring force T1 gradually increases. Assuming that the maximum rotation angle is 30°, the torsion spring force T1 (maximum value) = k1 * 30° = 0.26 N·m. After conversion to force, considering that the length of the lever arm L is 50mm, the torsion spring force F= ≈ 5.2N, at this time the torsion spring force is about 5.2N; Assuming that the impact force transmission efficiency is 80%, the force F = 0.8 * F = 0.8 * 50N = 40N is applied to the extrusion plate 225, and a force of about 40N is transmitted. At this time, the extrusion plate 225 squeezes the airbag 226; the initial volume V1 of the airbag 226 is 100cm³, and the pressure area A is 50cm². After the airbag 226 is squeezed, the squeezing force P = = = 8000Pa, the xenon gas in airbag 1 226 quickly fills into airbag 2 27, and airbag 2 227 expands to 4 times of the initial volume (then the force-bearing area A' is expanded four times), and airbag 227 generates a thrust F = P * A' = 320N on the cover 213. The thrust of airbag 227 can overcome the magnetic force between the cover 213 and the placement box 210 (the given maximum parameter is about 0.98N), so that the cover 213 slides along the slide groove 211 and falls off.

[0038] The technical solutions in the above embodiments of the present application have at least the following technical effects or advantages: The present application simplifies the internal structure of the drone by arranging the risk avoidance landing unit 200 as a separately detachable individual on the outside of the drone body 100, making it easier to mass-produce the drone, reducing production costs and complexity, and ensuring that the weight of the left and right sides of the drone is evenly distributed during flight, so that the drone can fly more stably during detection, reducing detection interruptions or delays caused by risk avoidance system problems. Timely risk avoidance measures also protect the drone and the detection equipment it carries, ensuring the integrity and accuracy of the detection data, thereby improving the overall detection efficiency.

[0039] By triggering the mechanism 220, the UAV can take spontaneous risk avoidance measures when it is forced to land by external forces, without the need for remote human operation or reliance on electric power, so that the UAV can respond quickly to emergencies such as collisions, avoiding the problem of failure to deploy the parachute 230 in time due to operational delays or power outages, and avoiding the problem that the deployment mechanism of the parachute 230 that relies on electric power may not work normally due to circuit failure or insufficient battery power, thereby improving the reliability of the risk avoidance system and reducing the risk of failure of the UAV; solving the technical problems of complex structure, greater production difficulty, complex risk avoidance operation, reduced safety performance and low detection efficiency in the prior art, and achieving the technical effects of simplified structure, reduced production difficulty, simplified risk avoidance operation, improved safety performance and improved detection efficiency.

[0040] Embodiment 2: Considering the need to detect different detection scenarios, it is possible that when the drone is forced to land, due to changes in the environment, external uncontrollable factors (tree branches, wires, etc.) may hinder the normal deployment or incomplete deployment of the parachute 230, reducing the buffering effect of the parachute 230 on slowing down the descent speed of the drone. It may cause the drone to hit the ground or other objects at a higher speed when landing, causing damage to the body structure, affecting the data recording of the camera 130, resulting in data loss or unreadable, increasing costs and time consumption. Therefore, this application proposes the following technical solutions for the above technical problems, specifically: like Figures 7 to 9As shown, the risk avoidance landing unit 200 also includes a flipping and unfolding mechanism 260 , which is provided with four groups, and is rotatably connected to the four inner walls of the placement box 210 and is located below the cover plate 213 , for assisting the parachute 230 in unfolding.

[0041] The unfolding mechanism 260 includes a first lever 261, which is an L-shaped structure and one end of its horizontal section is rotatably connected to the middle of the corresponding side wall of the placement box 210 through a torsion spring, and the other end is detachably connected to the parachute 230 umbrella. When the cover plate 213 falls off, the first lever 261 drives the parachute 230 to flip upward under the action of the torsion spring.

[0042] This embodiment provides a circumferentially arranged first lever 261, which can effectively clear obstacles around the parachute 230 before it is released (that is, when the cover 213 is separated from the placement box 210), effectively solving the problem that the parachute 230 may be hindered by external environmental factors during the deployment process. The first lever 261 of the unfolding mechanism 260 is designed to actively clear obstacles while driving the parachute 230 to perform initial deployment, thereby improving the deployment speed of the parachute 230, thereby improving the stability, safety and risk avoidance ability of the drone landing, reducing the risk of the drone being unable to continue to perform the detection mission due to a malfunction, and ensuring the continuity of the detection mission.

[0043] Embodiment 3: Considering that the accuracy of triggering the parachute 230 is a key factor in determining whether the parachute 230 can be released in time, it determines whether the trigger mechanism can be activated in time and accurately when the drone encounters an emergency and needs to land, and the completeness of the opening of the parachute 230 is whether the parachute 230 can be smoothly and completely deployed after the trigger mechanism is activated to provide sufficient buffering force for the drone. These two processes are continuous in time and logically interdependent. The complete opening of the parachute 230 is a direct result of the successful activation of the trigger mechanism, which further ensures that the drone can land at a stable speed and attitude. If the parachute 230 is not fully opened, even if the trigger mechanism works normally, it may not provide sufficient buffering force for the drone, causing the drone to hit the ground at a faster speed and cause damage; therefore, in order to further improve the efficiency and stability of the safe landing of the drone when avoiding risks, the present application proposes the following technical solutions for the above-mentioned technical problems, specifically: like Figures 7 to 9 As shown, the unfolding mechanism 260 further includes two groups of levers arranged in an upper and lower manner, which are respectively divided into a second lever 262 and a third lever 263 from top to bottom; The second lever 262 and the third lever 263 are provided in plurality and are evenly arranged along the length direction of the side wall of the corresponding placement box 210. The second lever 262 and the third lever 263 are rotatably connected to the side wall of the placement box 210 by a hinged manner. The second lever 262 and the first lever 261 located in the middle are connected to the second lever 262 and the third lever 263 located in the middle by a pull rope 264.

[0044] The lengths of the first lever 261 , the second lever 262 , and the third lever 263 decrease from top to bottom, and the numbers of the first lever 261 , the second lever 262 , and the third lever 263 increase from top to bottom.

[0045] The first lever 261, the second lever 262, and the third lever 263 are all attached to the parachute 230 by means of dotted Velcro, and the heights of the contact points between the first lever 261, the second lever 262, and the third lever 263 and the parachute 230 surface decrease from top to bottom, so as to ensure that each part of the parachute 230 can be pulled evenly and effectively.

[0046] In the actual use of this embodiment: Fig. 9 As shown, when the cover plate 213 is released from the placement box 210, the first lever 261 is not pressed by the cover plate 213 and under the action of its own torsion spring, the first lever 261 drives the contact point at the highest position of the parachute 230 to flip upward, and at the same time, the second lever 262 is driven in sequence by the pulling of the pull rope 264, and the second lever 262 drives the third lever 263 to rotate upward, so that the contact points at different heights and positions on the parachute 230 that are adhered to it are gradually lifted up by the corresponding levers. The force exerted by the first lever 261, the second lever 262, and the third lever 263 on the parachute 230 is much greater than the fixing force of the first lever 261, the second lever 262, and the third lever 263 on the parachute 230. Therefore, during the process from the initial deployment to the complete deployment of the parachute 230, the first lever 261, the second lever 262, and the third lever 263 are out of contact with the parachute 230. Under the action of the airflow, the parachute 230 is gradually and quickly released completely. At the same time, the deployment area and speed per unit time of the parachute 230 after being triggered are increased, so that during the rapid fall, it can be quickly released and deployed to the maximum extent, and the impact of the drone falling is reduced more quickly.

[0047] The present application makes the deployment process of the parachute 230 faster by setting up multi-level levers, ensuring that the drone can quickly obtain sufficient buffering force in an emergency. The levers of different lengths and numbers are arranged at different heights and positions, which can ensure that all parts of the parachute 230 can be pulled evenly and effectively during the deployment process. Since the deployment of the parachute 230 is carried out at multiple points at the same time, this fast and comprehensive deployment method can quickly clear the surrounding obstacles, reduce the interference of external factors on the deployment of the parachute 230, and avoid the situation where some areas are not fully deployed. At the same time, faster deployment speed and higher deployment integrity mean that the parachute 230 can generate sufficient air resistance faster, thereby more effectively slowing down the descent speed of the drone and protecting the drone and its internal equipment from damage; by optimizing the deployment process of the parachute 230, the risk of the drone being damaged due to improper landing is reduced, thereby ensuring the continuity of the detection mission and the integrity of the data.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A detection device for drone mounting, characterized in that: It comprises a drone body (100), fan blades (110), a support rod (120), a camera (130) and a risk avoidance landing unit (200); The risk avoidance landing unit (200) comprises a placement box (210), a fixing plate (201), a trigger mechanism (220), a parachute (230), a movable plate (250) and a second spring (240); The placement box (210) is a box-shaped structure without a cover and is fixed to the middle of the top of the drone body (100) by means of a snap connection. The top of the placement box (210) is provided with a cover plate (213) for closing the placement box (210) and for storing the parachute (230). The fixing plate (201) is fixed to the middle of the placement box (210) and is used to separate the trigger mechanism (220) and the parachute (230). The trigger mechanism (220) is fixed inside the placement box (210) and is used to automatically trigger the release of the parachute (230) when the drone is hit by an external force. The moving plate (250) is slidably connected to the inside of the placement box (210) by means of a second spring (240) and is located above the fixing plate (201) and is used to eject the parachute (230). The parachute (230) is stacked above the moving plate (250) and is used to release the parachute (230) after being triggered, thereby providing a buffering force for the drone body (100).

2. A detection device for drone mounting as claimed in claim 1, characterized in that: A slide groove (211) is provided on the top of the placement box (210). The slide groove (211) is a tic-tac-toe structure and each intersection is provided with a groove (212) that cooperates with the bottom of the cover plate (213) through magnetic attraction. The slide groove (211) is used to guide the movement of the cover plate (213), and the groove (212) is used to position the cover plate (213) and realize the closure of the parachute (230).

3. A detection device for drone mounting as claimed in claim 2, characterized in that: The placement box (210) is made of a light and strong material, such as aluminum alloy or carbon fiber composite material, to ensure sufficient strength and reduce weight.

4. A detection device for drone mounting as claimed in claim 3, characterized in that: The trigger mechanism (220) comprises a flap (222), a trigger ball (223), a first spring (224), a pressing plate (225), a first airbag (226), and a second airbag (227); Four flaps (222) are provided, evenly arranged along the circumference of the fixed plate (201), and are respectively hinged to the bottom of the fixed plate (201) via torsion springs; the trigger ball (223) is placed in the placement box (210) and is located on the inner side of the four flaps (222); four groups of springs (224) are provided, respectively fixed on the four inner side walls of the placement box (210), and are used to provide elastic force for the flaps (222) to return to their original position; four squeezing plates (225) are provided, corresponding one to one with each group of springs (224), and are respectively slidably connected to the placement box (210) via corresponding springs (224), and are used to When the flap (222) is pushed open by the trigger ball (223), the trigger ball (223) hits the squeezing plate (225), causing the squeezing plate (225) to squeeze the airbag 1 (226); four airbags 1 (226) are provided, corresponding one-to-one to the squeezing plates (225), and are respectively fixed inside the four side walls of the placement box (210); four airbags 2 (227) are provided, corresponding one-to-one to the airbags 1 (226), and are respectively fixed at the upper ends of the four side walls of the placement box (210), and are connected to the corresponding airbags 1 (226) through internal pipes, and are used to push the cover plate (213) out of the placement box (210) after expansion.

5. A detection device for drone mounting as claimed in claim 4, characterized in that: The gas type inside the airbag 1 (226) is xenon, which is used to enable the airbag 1 (226) to be quickly inflated into the airbag 2 (227) through the internal airway after being squeezed, so that the airbag 2 (227) expands; the volume of the airbag 2 (227) after inflation is 4 to 6 times the initial volume.

6. A detection device for drone mounting as claimed in claim 4, characterized in that: The risk avoidance landing unit (200) further comprises a flipping and unfolding mechanism (260), wherein four groups of the flipping and unfolding mechanisms (260) are respectively rotatably connected to four inner side walls of the placement box (210) and located below the cover plate (213), and are used to assist the parachute (230) in unfolding.

7. A detection device for drone mounting as claimed in claim 6, characterized in that: The unfolding mechanism (260) comprises a first lever (261), the first lever (261) being an L-shaped structure, one end of a horizontal section of which is rotatably connected to the middle of a corresponding side wall of the placement box (210) via a torsion spring, and the other end of which is detachably connected to the parachute (230) canopy. When the cover plate (213) is detached, the first lever (261) drives the parachute (230) to flip upwards under the action of the torsion spring.

8. A detection device for drone mounting as claimed in claim 7, characterized in that: The unfolding mechanism (260) further comprises two groups of levers arranged in an upper and lower manner, which are respectively divided into a second lever (262) and a third lever (263) from top to bottom; The second lever (262) and the third lever (263) are provided in plurality and are evenly arranged along the length direction of the side wall of the corresponding placement box (210); the second lever (262) and the third lever (263) are rotatably connected to the side wall of the placement box (210) by means of hinges; the second lever (262) and the first lever (261) located in the middle are connected to the second lever (262) and the third lever (263) located in the middle by means of pull ropes (264).

9. A detection device for drone mounting as claimed in claim 8, characterized in that: The lengths of the first shift rod (261), the second shift rod (262), and the third shift rod (263) decrease sequentially from top to bottom, and the number of the first shift rod (261), the second shift rod (262), and the third shift rod (263) increases sequentially from top to bottom.

10. A detection device for drone mounting as claimed in claim 9, characterized in that: The first lever (261), the second lever (262), and the third lever (263) are all adhered to the parachute (230) via point-shaped Velcro tapes, and the heights of the contact points between the first lever (261), the second lever (262), and the third lever (263) and the parachute (230) surface are successively reduced from top to bottom, so as to ensure that each part of the parachute (230) can be pulled evenly and effectively.

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