An anti-weightlessness protection device for UAV remote sensing mapping

Abstract

The present invention discloses a weightlessness protection device for UAV remote sensing mapping, which relates to the field of UAV protection. It includes a protection block. A fireproof layer is fixed to the inner wall of the protection block. An installation frame is installed at the top of the protection block. A lighter is installed at the top inside the protection block. A one-way valve is installed on the lower surface of the protection block. Gliding components are symmetrically arranged on both sides of the protection block. Buffer components are symmetrically arranged on both sides of the protection block. The gliding component includes a rubber hose. The rubber hoses are located at the front and rear ends on both sides of the protection block. One end of each rubber hose is fixedly connected and communicated with the protection block. The buffer component includes a buffer head. The number and position of the buffer heads correspond to those of the rubber hoses. It simulates the gliding of a bird and makes the UAV fall in a parabolic shape, so that when the UAV lands, it rubs against the ground obliquely instead of hitting the ground vertically, converting the impact force of the impact into frictional force, greatly reducing the damage caused when the UAV contacts the ground.

Description

Technical Field

[0001] The present invention relates to the technical field of UAV protection, and specifically to a weightlessness protection device for UAV remote sensing mapping. Background Technique

[0002] According to existing information: UAVs are a commonly used tool in current mapping operations. However, during field mapping operations, UAVs are easily damaged by various factors and thus lose weight and fall. Generally, UAVs falling from a high altitude will be completely damaged and cannot be repaired anymore;

[0003] Existing authorized patents, as well as existing equipment with the same technology and similar equipment of the same type, still have the following problems in daily use:

[0004] 1: Common protection devices are generally protective frames, but they only protect the propellers from colliding with external objects, and the protective frame cannot protect the propellers under the huge impact force generated during a fall. Additionally, the fuselage is wrapped by an airbag to protect the fuselage through the airbag's buffering, but the propellers will still be damaged irreparably;

[0005] 2: Currently, installing a parachute on the fuselage is used to reduce the falling speed and reduce the damage to the fuselage caused by the impact force. However, when a UAV loses weight and falls, it must be because the UAV is damaged and cannot work. At this time, the UAV will continuously flip during the fall, and the parachute may be entangled by the propellers or branches in the wild when it pops out, unable to complete the function of buffering the fall. Summary of the Invention

[0006] To achieve the above object, the present invention provides the following technical solution: A weightlessness protection device for UAV remote sensing mapping, including a protection block, a fireproof layer is fixed on the inner wall of the protection block, an installation frame is installed at the top of the protection block, a lighter is installed at the top inside the protection block, a one-way valve is installed on the lower surface of the protection block, gliding components are symmetrically arranged on both sides of the protection block, and buffer components are symmetrically arranged on both sides of the protection block;

[0007] The gliding components include rubber hoses, the rubber hoses are located at the four top corners on both sides of the protection block, and one end of each rubber hose is fixedly connected and communicated with the protection block;

[0008] The buffer components include buffer heads, and the number and positions of the buffer heads correspond to those of the rubber hoses.

[0009] Preferably, connection heads are fixedly connected and communicated to the ends of the rubber hoses away from the protection block. Four mounting blocks are fixedly connected to both the upper and lower ends of the protection block. One end of each mounting block away from the protection block is rotatably connected to a mounting plate, and the other end of each mounting plate is fixedly connected to the end of the connection head.

[0010] Preferably, buffer grooves are uniformly and penetratingly formed on the surface of the mounting plate, and the buffer grooves are semi-circular arches.

[0011] Preferably, conduits are fixedly communicated with one ends of the connecting heads away from the protective blocks, buffer heads are fixedly communicated with the other ends of the conduits away from the protective blocks, magnets are fixedly connected to the opposite side surfaces of the buffer heads on the same side, and the magnets on the same side attract each other.

[0012] Preferably, gliding cloths are arranged at the middle positions of the conduits on the same side, and both ends of the gliding cloths are fixedly connected to the surfaces of the conduits on the same side.

[0013] Preferably, connecting cylinders are fixedly communicated with the upper and lower ends of the buffer heads, transmission blocks are arranged inside the connecting cylinders, the transmission blocks are slidably and sealingly connected to the inner walls of the connecting cylinders, connecting rods are inserted into one ends of the connecting cylinders away from the buffer heads, and guide wheels are rotatably connected to the other ends of the connecting rods away from the buffer heads.

[0014] Preferably, the rubber hose is made of soft rubber, the guide wheel is made of hard rubber, and the gliding cloth is made of oilcloth.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0016] 1. The device is installed on the drone through the mounting frame. After 1 gram of gunpowder is completely burned, 70 liters of gas are generated. The amount of gunpowder filled in the protective block 1 is 0.1 gram. When the drone loses weight and falls, the igniter is powered on through the remote control to ignite the gunpowder inside the protective block. A large amount of generated gas is filled into the rubber hose, the connecting head and the conduit. The air pressure impacts and tightens the rubber hose, the connecting head and the conduit, and unfolds the gliding cloth. Using the conduit as the framework and the gliding cloth as the surface, the drone is glided, greatly reducing the falling speed of the drone, so that the drone will not fall rapidly under the action of gravitational acceleration. Simulating the gliding of birds, the drone falls in a parabolic shape, so that when the drone lands, it rubs against the ground obliquely instead of hitting the ground vertically, converting the impact force into frictional force, greatly reducing the damage caused when the drone contacts the ground.

[0017] 2. When the device lands, if the guide wheel lands directly, the guide wheel drives the connecting rod and the transmission block to move into the connecting cylinder. The transmission block squeezes the air inside the connecting cylinder, and buffers the impact force of the guide wheel hitting the ground through the air pressure, thereby discharging part of the impact force. Moreover, the guide wheel is made of rubber, and it is also deformed by the impact and rebounds quickly, driving the entire device to bounce up from the ground and then land, continuously discharging the impact force to complete the landing, so that the impact force received by the drone is small and relatively serious damage will not be caused.

[0018] 3. When the device is affected by branches and ends the glide and lands directly, when the buffer head contacts the ground directly, a part of the impact force is discharged through the guide wheel in the first step, and then the impact force acts on the conduit. If the height is relatively high, the impact force is conducted by the conduit to the mounting plate. The mounting plate is provided with buffer grooves, and the mounting plate deforms and compresses, providing a space for discharging the impact force. A large part of the impact force is buffered and discharged through the deformation and compression of the mounting plate, and the propeller is separated from the ground through the buffer head and the conduit, so that no matter what state the drone lands in, the propeller will not directly contact the ground and bear the impact force. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 is a front view schematic diagram of the structure of the present invention;

[0020] Figure 2 is a three-dimensional sectional schematic diagram of the structure of the protective block in the present invention;

[0021] Figure 3 is a three-dimensional connection schematic diagram of the structure of the mounting plate, conduit and buffer head in the present invention;

[0022] Figure 4 is a three-dimensional partial sectional schematic diagram of the structure of the buffer head and the connecting cylinder in the present invention;

[0023] Figure 5 is a schematic diagram of the unfolded state of the structure of the present invention.

[0024] In the figure: 1. Protective block; 2. Mounting frame; 3. Lighter; 4. Check valve; 5. Rubber hose; 6. Connector; 7. Mounting block; 8. Mounting plate; 9. Buffer groove; 10. Conduit; 11. Buffer head; 12. Magnet; 13. Glide cloth; 14. Connecting cylinder; 15. Transmission block; 16. Connecting rod; 17. Guide wheel; 18. Fireproof layer. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0025] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0026] The present invention will be further described below in conjunction with the embodiments.

[0027] Embodiment 1

[0028] For this embodiment, please refer to Figures 1 to 5 the accompanying drawings shown;

[0029] In this embodiment, to solve the problem in the background art that currently, by installing a parachute on the fuselage to reduce the falling speed and minimize the damage to the fuselage caused by the impact force, however, when the UAV is in free-fall, it must be because the UAV is damaged and unable to work. At this time, the UAV will continuously flip during the falling process, and when the parachute pops out, it may be entangled by the propeller or branches in the wild, etc., and cannot complete the function of buffering the fall;

[0030] A fireproof layer 18 is fixed to the inner wall of the protection block 1. An installation frame 2 is installed at the top end of the protection block 1. A lighter 3 is installed at the top end inside the protection block 1. A one-way valve 4 is installed on the lower surface of the protection block 1. Gliding components are symmetrically arranged on both sides of the protection block 1, and buffer components are symmetrically arranged on both sides of the protection block 1;

[0031] The gliding components include rubber hoses 5, and the rubber hoses 5 are located at the four top corners on both sides of the protection block 1. One end of each rubber hose 5 is fixedly connected and communicated with the protection block 1;

[0032] The end of each rubber hose 5 far away from the protection block 1 is fixedly connected and communicated with a connection head 6. Four mounting blocks 7 are fixedly connected to both the upper and lower ends of the protection block 1. The end of each mounting block 7 far away from the protection block 1 is rotatably connected to a mounting plate 8, and the other end of each mounting plate 8 is fixedly connected to the end of the connection head 6;

[0033] Buffer grooves 9 are uniformly formed through the surface of the mounting plate 8, and the buffer grooves 9 are semi-circular arches;

[0034] The end of each connection head 6 far away from the protection block 1 is fixedly connected and communicated with a conduit 10. The end of each conduit 10 far away from the protection block 1 is fixedly connected and communicated with a buffer head 11. A magnet 12 is fixedly connected to the opposite side surface of the buffer heads 11 on the same side, and the magnets 12 on the same side attract each other;

[0035] A gliding cloth 13 is arranged at the middle of each conduit 10 on the same side, and both ends of the gliding cloth 13 are fixedly connected to the surface of the conduit 10 on the same side;

[0036] The above-mentioned embodiment achieves the following effects compared with the existing authorized patents, the equipment with the same technology, and the equipment with similar technologies of the same type:

[0037] The device is installed on the drone through the mounting bracket 2. When one gram of gunpowder burns completely, it generates 70 liters of gas. The amount of gunpowder loaded in the protective block 1 is 0.1 gram. When the drone loses weight and falls, the igniter 3 is powered on through the remote control to ignite the gunpowder inside the protective block 1. A large amount of generated gas is filled into the rubber hose 5, the connector 6 and the conduit 10. The air pressure impacts and tightens the rubber hose 5, the connector 6 and the conduit 10, and unfolds the gliding cloth 13. Using the conduit 10 as the framework and the gliding cloth 13 as the surface, it glides with the drone, greatly reducing the falling speed of the drone, so that the drone will not fall rapidly under the action of gravitational acceleration. It simulates the gliding of birds and makes the drone fall in a parabolic shape. When the drone lands, it rubs against the ground obliquely instead of hitting the ground vertically, converting the impact force into friction force and greatly reducing the damage caused when the drone contacts the ground.

[0038] Embodiment 2

[0039] Please refer to Figures 1 to 5 the accompanying drawings shown;

[0040] In this embodiment, to solve the problem in the background technology, common protection devices are generally protective frames, but they only protect the propellers from colliding with external objects, and the protective frames cannot complete the protection of the propellers under the huge impact force generated during falling. Moreover, the fuselage is wrapped by airbags to protect the fuselage through the buffering of the airbags, but the propellers will still be damaged irreparably;

[0041] The buffer assembly includes buffer heads 11, and the number and positions of the buffer heads 11 correspond to those of the rubber hose 5;

[0042] Both the upper and lower ends of the buffer head 11 are fixedly connected and communicated with connecting cylinders 14. Transmission blocks 15 are arranged inside the connecting cylinders 14. The transmission blocks 15 are slidably and sealingly connected with the inner walls of the connecting cylinders 14. Connecting rods 16 are inserted into one ends of the connecting cylinders 14 away from the buffer heads 11. Guide wheels 17 are rotatably connected to the ends of the connecting rods 16 away from the buffer heads 11;

[0043] The rubber hose 5 is made of soft rubber material, the guide wheels 17 are made of hard rubber material, and the gliding cloth 13 is made of oilcloth material;

[0044] The above embodiments achieve the following effects compared with the existing authorized patents, devices with the same technology, and similar devices with similar technologies:

[0045] When the device lands, if the guide wheel 17 lands directly on the ground, the guide wheel 17 drives the connecting rod 16 and the transmission block 15 to move inside the connecting cylinder 14. The transmission block 15 squeezes the air inside the connecting cylinder 14, and the impact force of the guide wheel 17 hitting the ground is buffered by the air pressure, thereby discharging part of the impact force. Moreover, the guide wheel 17 is made of rubber material, and it is also deformed by the impact and rebounds quickly, driving the entire device to bounce up from the ground and then land again, continuously discharging the impact force to complete the landing, so that the impact force received by the drone is small and will not cause serious damage;

[0046] When the device ends its glide and lands directly due to being affected by a tree branch and the buffer head 11 comes into direct contact with the ground, part of the impact force is discharged by the guide wheel 17 in the first step, and then the impact force acts on the conduit 10. Because the tree branch causes the device to end its glide, and the height from the ground is not too high at this time, the impact force is conducted from the conduit 10 to the mounting plate 8. There is a buffer groove 9 on the mounting plate 8, and the mounting plate 8 deforms and compresses, giving space for discharging the impact force. A large part of the impact force is buffered and discharged through the deformation and compression of the mounting plate 8, and the propeller is separated from the ground through the buffer head 11 and the conduit 10, so that no matter what state the drone lands in, the propeller will not directly contact the ground and bear the impact force.

[0047] The complete working principle and working process of the above-mentioned Embodiments 1-2 are as follows:

[0048] The user fixedly installs the mounting bracket 2 on the drone, thereby fixing this device on the drone, and fills the protective block 1 with gunpowder powder. One gram of gunpowder produces 70 liters of gas after complete combustion, and the amount of gunpowder filled in the protective block 1 is 0.1 gram. Connect the igniter 3 to the electronic control system of the drone. Under normal circumstances, the buffer heads 11 on the same side attract each other, so that the conduits 10 on the same side are close together. When the drone loses weight and falls, the user remotely controls the ignition of the igniter 3. The igniter 3 ignites the gunpowder, and the gunpowder burns to produce a large amount of gas, causing the air pressure inside the protective block 1 to rise rapidly, and the spark and heat generated by the gunpowder are protected by the fireproof layer 18. The gas inside the protective block 1 quickly enters the protective block 1, the conduit 10 and the buffer head 11. The rubber hose 5 is made of soft rubber material, and the air pressure impacts the rubber hose 5 to straighten the rubber hose 5, driving the conduit 10 and the buffer head 11 to rotate. At this time, the four groups of rubber hoses 5 and conduits 10 are at a 45-degree state with the protective block 1, and the conduit 10 drives the gliding cloth 13 to unfold. Refer to Figure 5 ., and the rubber hose 5 and the conduit 10 are maintained in the unfolded state by the air pressure during weightlessness. The conduit 10 serves as the framework and the gliding cloth 13 serves as the surface, driving the drone to simulate the gliding of a bird, greatly reducing the falling speed and the falling direction of the drone, so that the drone falls in a parabolic shape. When falling, the drone and this device will not directly hit the ground in a vertical state, but will contact the ground obliquely;

[0049] When the device lands, if the guide wheel 17 lands directly, the guide wheel 17 drives the connecting rod 16 and the transmission block 15 to move inside the connecting cylinder 14. The transmission block 15 squeezes the air inside the connecting cylinder 14. At this time, the buffer head 11 is filled with the gas generated by gunpowder combustion, and the air pressure is higher than the normal pressure. The transmission block 15 cannot move freely inside the connecting cylinder 14 normally. By simulating the principle of air suspension, the force received by the guide wheel 17 is buffered, and part of the impact force and friction force are discharged. Moreover, the guide wheel 17 is made of rubber material, and it is also deformed by impact and rebounds quickly by itself, driving the whole device to bounce up from the ground and then land, continuously discharging the impact force to complete the landing, so that the impact force received by the drone is small and will not cause serious damage. When the device collides with a mountain or the like during gliding, it contacts through the guide wheel 17. After the guide wheel 17 contacts, it rotates and drives the device to turn to avoid falling. When the device ends gliding due to the influence of objects such as branches, the height from the ground is not too high at this time. After the gliding ends, the device falls vertically to the ground, and the buffer head 11 contacts the ground directly. The drone is separated from the ground through the guide wheel 17 and the conduit 10 to avoid direct impact and damage of the propeller with the ground. After the buffer head 11 impacts the ground, the impact force acts on the mounting plate 8. Buffer grooves 9 are provided on the mounting plate 8. When the impact force reaches a certain level, the mounting plate 8 is compressed and deformed from each buffer groove 9 to provide space for buffering and discharging the impact force to complete a safe landing.

[0050] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claimed claims.

Claims

1. An anti-gravity protection device for UAV remote sensing mapping, characterized in that, Comprising: A protective block (1), a fireproof layer (18) is fixed to the inner wall of the protective block (1), a mounting bracket (2) is installed at the top end of the protective block (1), a lighter (3) is installed at the top end inside the protective block (1), a check valve (4) is installed on the lower surface of the protective block (1), gliding components are symmetrically arranged on both sides of the protective block (1), and buffer components are symmetrically arranged on both sides of the protective block (1); The gliding components include rubber hoses (5), the rubber hoses (5) are located at the four top corners of the protective block (1), and one end of each rubber hose (5) is fixedly connected and communicated with the protective block (1); The buffer components include buffer heads (11), and the number and positions of the buffer heads (11) correspond to those of the rubber hoses (5); One end of each rubber hose (5) far from the protective block (1) is fixedly connected and communicated with a connecting head (6), four mounting blocks (7) are fixedly connected to both the upper and lower ends of the protective block (1), one end of each mounting block (7) far from the protective block (1) is rotatably connected to a mounting plate (8), and the other end of each mounting plate (8) is fixedly connected to the end of the corresponding connecting head (6); One end of each connecting head (6) far from the protective block (1) is fixedly connected and communicated with a conduit (10), one end of each conduit (10) far from the protective block (1) is fixedly connected and communicated with a buffer head (11), a magnet (12) is fixedly connected to the opposite side surfaces of the buffer heads (11) on the same side, and the magnets (12) on the same side attract each other.

2. The anti-gravity protection device for UAV remote sensing mapping according to claim 1, characterized in that: Buffer grooves (9) are uniformly formed through the surface of the mounting plate (8), and the buffer grooves (9) are semi-circular arches.

3. The anti-gravity protection device for UAV remote sensing mapping according to claim 1, characterized in that: A gliding cloth (13) is arranged at the middle of each conduit (10) on the same side, and both ends of the gliding cloth (13) are fixedly connected to the surface of the corresponding conduit (10) on the same side.

4. The anti-gravity protection device for UAV remote sensing mapping according to claim 3, characterized in that: Both the upper and lower ends of each buffer head (11) are fixedly connected and communicated with a connecting cylinder (14), a transmission block (15) is arranged inside each connecting cylinder (14), the transmission block (15) is slidably and sealingly connected to the inner wall of the connecting cylinder (14), a connecting rod (16) is inserted into one end of each connecting cylinder (14) far from the buffer head (11), and a guide wheel (17) is rotatably connected to the end of each connecting rod (16) far from the buffer head (11).

5. The anti-gravity protection device for UAV remote sensing mapping according to claim 4, characterized in that: The rubber hoses (5) are made of soft rubber material, the guide wheels (17) are made of hard rubber material, and the gliding cloth (13) is made of oilcloth material.

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