An early geological disaster identification device based on InSAR technology and its usage method

Abstract

The present invention provides a geological disaster early identification device and a usage method based on InSAR technology. Aiming at the problems that the existing identification devices are not convenient for keeping the synthetic aperture radar always downward, providing shielding protection and shock absorption during landing, the following solution is proposed. It includes a fixing plate fixed to the bottom of a drone and a synthetic aperture radar. The synthetic aperture radar is located below the fixing plate. A spherical protective cover is fixedly connected to the bottom of the fixing plate. The inside of the spherical protective cover is provided with a rectangular groove with an open bottom. The present invention facilitates personnel to quickly remotely control and intelligently synchronously release the fixation and shielding of the synthetic aperture radar during the flight of the drone, facilitates keeping the synthetic aperture radar always downward automatically during the flight, and is convenient for fixing the synthetic aperture radar, shielding the bottom and providing shock absorption during landing, reducing the risk of damage caused by factors such as seismic force impact and ground protrusion collision during landing, improving its service life, and being beneficial for use.

Description

Technical Field

[0001] The present invention relates to the technical field of geological disaster early identification equipment, and particularly relates to a geological disaster early identification device and a using method based on InSAR technology. Background Technique

[0002] The identification of potential landslide disaster points is the basic work of landslide disaster warning. Traditional landslide monitoring technologies, such as geodetic surveying, GPS monitoring, and deep displacement monitoring, all have the disadvantage of a small monitoring range. When faced with widespread landslide disasters, they cannot efficiently identify potential landslide disaster points and can only deploy monitoring and warning systems for known dangerous slopes. In recent years, the continuously developed and improved InSAR technology has shown extremely remarkable effects in identifying potential landslide disaster points and detecting the spatio-temporal evolution characteristics of landslides. Its technical advantages such as large range and high resolution can better adapt to the spatio-temporal distribution characteristics of landslides and have become an effective technical means for detecting landslides.

[0003] Interferometric Synthetic Aperture Radar (InSAR) is a technology for obtaining high-precision ground deformation information. Its basic principle is to obtain elevation information and deformation information of the ground surface by performing phase interference on two SAR images of the same area. Compared with conventional measurements, InSAR technology has the characteristics of a wider measurement range, higher precision, all-weather, all-day, and high efficiency. It has become one of the commonly used geodetic measurement technologies. As a technology in the remote sensing field, compared with optical remote sensing measurement, InSAR technology can be unrestricted by climate conditions and is an ideal technical means for monitoring surface deformation. The AlongTrack Interferomety mode of InSAR technology is used to measure the speed of ground targets. InSAR is divided into SBAS-InSA, ps-InSA, and d-InSA. d-InSA and SBAS-InSA are more commonly used in geological disasters. The widely used differential interferometry technology d-InSA obtains surface deformation monitoring results by introducing external DEM or using multiple orbit data for differential interference. Common methods include two-track method, three-track method, and multi-track method. The ps-InSA technology is the multiple nested abbreviation of "Persistent Scatterer Synthetic Aperture Radar Interferometry". Among them, PS (Persistent Scatterer) refers to various ground targets with strong backscattering of radar waves and relatively stable temporally, such as the corners of buildings and structures, bridges, railings, exposed rocks and other targets. The Small Baseline Subset (SBAS) technology was proposed by scholars such as Berardina and Lanari in 2002. SBAS freely combines short-baseline SAR images to generate a series of time-series interferograms based on different master images, and then combines multiple short baselines through singular value decomposition method to solve, thus effectively reducing the spatio-temporal decorrelation effect. The finally obtained deformation map is also more continuous in time and space. All in all, using SBAS technology to solve the surface deformation model can obtain more stable results and has great advantages in large-scale geological disaster surveys.

[0004] Existing geological disaster early identification devices based on InSAR technology mostly use the air-space-ground (Interferometric Synthetic Aperture Radar (InSAR), Unmanned Aerial Vehicle (UAV), and Ground Penetrating Radar (GPR)) integration method for early identification of landslide geological disasters. The synthetic aperture radar system mostly performs interferometric measurements by being suspended at the bottom of the UAV by a suspension rope. The existing method of performing interferometric measurements and identification by suspending a synthetic aperture radar at the bottom of the UAV still has some deficiencies:

[0005] 1. The way of directly hanging it is prone to large swings of the synthetic aperture radar antenna due to factors such as wind blowing, which affects measurement. Although there is a way of direct fixation in the prior art, the way of direct fixation has the disadvantage of being inconvenient to always keep the synthetic aperture radar detecting vertically downward, and it is easy to tilt following factors such as slight tilting of the UAV flight, affecting measurement;

[0006] 2. It has the disadvantage of being inconvenient to shield and protect the synthetic aperture radar during landing. The synthetic aperture radar is installed below the UAV and is easily directly collided with. Although most UAV bottoms are provided with brackets, when there are protrusions on the ground, the objects protruding upward from the ground during landing are likely to directly impact the synthetic aperture radar, resulting in a relatively high risk of damage to it, and the protection effect is not comprehensive;

[0007] 3. It has the disadvantage of being inconvenient to shock-absorb the synthetic aperture radar during landing. When the UAV touches the ground during landing, a large impact force will be generated. Under the hard resonance force generated by the impact force, the hard shock damage to the synthetic aperture radar is relatively large.

[0008] In order to solve the problems of being inconvenient to always keep the synthetic aperture radar downward, shield and protect it during landing, and shock-absorb it, we propose a geological disaster early identification device and usage method based on InSAR technology. Summary of the Invention

[0009] The geological disaster early identification device and usage method based on InSAR technology proposed by the present invention solve the problems of being inconvenient to always keep the synthetic aperture radar downward, shield and protect it during landing, and shock-absorb it.

[0010] In order to achieve the above object, the present invention adopts the following technical solutions:

[0011] A geological disaster early identification device based on InSAR technology, comprising a fixing plate fixed to the bottom of a drone and a synthetic aperture radar. The synthetic aperture radar is located below the fixing plate. A spherical shield is fixedly connected to the bottom of the fixing plate. The interior of the spherical shield is provided with a rectangular groove with an open bottom. The synthetic aperture radar is located in the rectangular groove. A rectangular seat is arranged in the rectangular groove. A universal ball is movably nested on the top of the rectangular seat. The bottom of the universal ball is fixedly connected with a connecting seat. The bottom of the connecting seat is fixedly connected with a counterweight block. A spherical cavity is formed in the counterweight block. A spherical ball is movably contacted with the inner wall of the bottom of the spherical cavity. The bottom of the counterweight block is slidably connected with an elastic guiding mechanism thread-fixed to the top of the synthetic aperture radar. A rectangular box with an open bottom is fixedly connected between the front inner wall and the rear inner wall of the rectangular groove. A rectangular block with an arc-shaped bottom is slidably sleeved in the rectangular box. The bottom of the rectangular block is adhesively fixed with an anti-slip rubber sheet that is in close contact with the top of the universal ball. A plurality of compression springs in a compressed state are fixedly connected between the top of the rectangular block and the inner wall of the top of the rectangular box. The two sides of the rectangular seat are fixedly connected with the same intelligent thread driving mechanism that is rotatably connected to the inner wall of the top of the rectangular groove. The intelligent thread driving mechanism is fixedly installed on the top of the rectangular box. Rectangular grooves are formed on the inner walls of both sides of the rectangular groove. A force-assisted linkage driving mechanism is fixedly connected to the inner wall of one side of the rectangular groove away from its opening. On one side of the two force-assisted linkage driving mechanisms close to each other, a shielding plate located below the synthetic aperture radar is fixedly connected. The two shielding plates are symmetrically arranged obliquely. On one side of the two force-assisted linkage driving mechanisms close to each other, they are fixedly connected to the outer side of the intelligent thread driving mechanism.

[0012] Preferably, the elastic guiding mechanism includes a mounting plate arranged below the counterweight block. The synthetic aperture radar is thread-fixed to the bottom of the mounting plate. Guide rods are fixedly connected to both sides of the top of the mounting plate. The counterweight block is slidably sleeved on the two guide rods. Two short damping springs are fixedly connected between the top of the mounting plate and the bottom of the counterweight block. The short damping springs are movably sleeved on the corresponding guide rods.

[0013] Preferably, the intelligent thread driving mechanism includes two screw rods rotatably connected to the inner wall of the top of the rectangular groove. An internally threaded sleeve with a sealing structure at the bottom is sleeved on the screw rods. The two sides of the rectangular base are fixedly connected to the mutually approaching sides of the two internally threaded sleeves respectively. A driving motor fixedly installed on the top of the rectangular box is arranged between the two screw rods. The top end of the output shaft of the driving motor is fixedly connected with a first sprocket. A second sprocket is fixedly sleeved on the screw rod. The same chain is drivingly connected to the two second sprockets and the first sprocket. A controller electrically connected to the driving motor is fixedly connected to the top of the rectangular box. A first touch switch in close contact with the top of the rectangular block is embedded in the top of the rectangular box. The touch end of the first touch switch is in movable contact with the top of the rectangular block. A second touch switch is fixedly installed on the right side of the rectangular box. A pressing block fixedly connected to the left side of the right internally threaded sleeve is arranged above the second touch switch in a matching manner. Both the first touch switch and the second touch switch are electrically connected to the controller. A wireless remote control switch is fixedly connected and electrically connected to the front side of the driving motor. The wireless remote control switch is matched with an external remote controller.

[0014] Preferably, the force - assisting linkage driving mechanism includes two rectangular sleeves fixedly connected to the inner wall of the corresponding rectangular groove far from its opening. The same rectangular rod is slidably sleeved in the two rectangular sleeves located in the same rectangular groove. The first transmission components rotatably connected to the front and rear inner walls of the rectangular groove are embedded on the mutually approaching sides of the two rectangular rods. The mutually approaching sides of the two first transmission components are fixedly connected to the mutually remote sides of the two internally threaded sleeves respectively. The second transmission components rotatably connected to the front and rear inner walls of the rectangular groove are embedded at the bottoms of the mutually approaching sides of the two rectangular rods. The mutually approaching sides of the two second transmission components are fixedly connected to the mutually remote sides of the two shielding plates respectively.

[0015] Preferably, the first transmission component includes a first rack embedded on the side of the corresponding rectangular rod close to the internally threaded sleeve. The first gears rotatably connected between the front and rear inner walls of the rectangular groove are meshed with the mutually approaching sides of the two first racks. The second racks are meshed with the mutually approaching sides of the two first gears. The mutually approaching sides of the two second racks are fixedly connected to the mutually remote sides of the two internally threaded sleeves respectively.

[0016] Preferably, the second transmission component includes a third rack embedded on the side of the corresponding rectangular rod close to the shielding plate. The second gears are meshed with the mutually approaching sides of the two third racks. Two rotating shafts are rotatably installed between the front and rear inner walls of the rectangular groove. The two second gears are fixedly sleeved on the corresponding rotating shafts respectively. Fixed seats fixedly sleeved on the corresponding rotating shafts are arranged on the front and rear sides of the second gears. The side of the fixed seat close to the corresponding shielding plate is fixedly connected to the shielding plate.

[0017] Preferably, two guiding grooves are formed in the bottom of the counterweight block and are respectively slidably connected to the outer sides of the corresponding guiding rods. Limiting through holes are formed in one sides of the two guiding grooves far away from each other, and limiting sliding blocks respectively slidably connected to the corresponding limiting through holes are fixedly connected to one sides of the two guiding rods far away from each other.

[0018] Preferably, limiting holes are formed in the inner walls of two sides of the rectangular box, and limiting blocks respectively slidably connected to the corresponding limiting holes are fixedly connected to two sides of the rectangular block.

[0019] Preferably, a hemispherical hole is formed in the top of the rectangular seat, and two groups of ball bearings are nested in an annular shape on the inner wall of the hemispherical hole. The number of ball bearings in each group is six and they are arranged at equal intervals.

[0020] The present invention also provides a using method of a geological disaster early recognition device based on InSAR technology, including the following steps:

[0021] S1: During use, fix the fixing plate to the bottom of the unmanned aerial vehicle through bolts. When the unmanned aerial vehicle drives the device to fly, personnel use an external remote controller to control the wireless remote control switch to positively start the driving motor. The driving motor drives the first sprocket to rotate, the first sprocket drives two second sprockets to rotate through a chain, and the two second sprockets drive two screw rods to rotate;

[0022] S2: When the two screw rods described in S1 rotate, they drive two internally threaded sleeves to move downward. The two internally threaded sleeves drive the rectangular seat to move downward, the rectangular seat drives the universal ball to move downward, and the universal ball gradually relaxes the extrusion force on the anti-slip rubber sheet and separates from the anti-slip rubber sheet. At this time, the elastic force of the compression spring in the compressed state drives the rectangular block to slide downward in the rectangular box and separate from the first touch switch. The rectangular block drives two limiting blocks to move downward;

[0023] S3: When the internally threaded sleeve described in S2 moves downward, it also drives the corresponding second rack to move downward. The second rack drives the corresponding first gear to rotate, the first gear drives the first rack engaged with it to move upward, and the first rack drives the corresponding rectangular rod to slide upward in the two rectangular sleeves;

[0024] S4: When the rectangular rod moves upward in S3, it drives the corresponding third rack to move upward. The third rack drives the corresponding second gear to rotate, and the second gear drives two fixing seats to rotate downward through the corresponding rotating shafts. The fixing seats drive the corresponding shielding plates to rotate downward and open, removing the shielding of the synthetic aperture radar;

[0025] S5: After the universal ball described in S2 is separated from the anti-slip rubber downward and the pressing and fixing state is released, when the drone tilts during flight, it will drive the whole device to tilt. At this time, under the action of the self-gravity of the counterweight, it will always remain vertically downward. Therefore, when tilting, the counterweight will drive the universal ball to rotate adaptively among the multiple ball bearings in the hemispherical hole through the connecting seat. Therefore, it will not be affected by external tilting. At this time, the counterweight drives the synthetic aperture radar to always remain vertically downward through two guide rods and the mounting plate in sequence. When tilting occurs during flight, the ball will also move in the spherical cavity and quickly return to the bottom of the spherical cavity under the action of its own gravity, which can assist the counterweight to quickly maintain verticality, and cooperate with the effect of removing the occlusion of the synthetic aperture radar described in S4, so that the occlusion of the synthetic aperture radar can be automatically removed quickly while the fixation is released quickly during use;

[0026] S6: When the internal thread sleeve described in S2 moves downward, it also drives the pressing block to move downward. When the pressing block moves downward to squeeze and contact the second touch switch, it touches the second touch switch, and at this time, the second touch switch transmits a closing signal to the controller, and the controller controls the driving motor to close, which can automatically and intelligently control the driving motor to close in time, preventing personnel from failing to grasp the closing timing in time;

[0027] S7: After use, when landing is required, the personnel use the external remote controller to operate the wireless remote control switch to reverse-start the driving motor. Similarly, the movement direction is completely opposite to that of the above-mentioned forward-starting driving motor. At this time, the rectangular seat and the internal thread sleeve change to move upward. The rectangular seat drives the universal ball to move upward and contact and squeeze the anti-slip rubber. Under the squeezing force, the anti-slip rubber moves upward and drives the rectangular block to move upward. The rectangular block compresses the compression spring. At this time, under the squeezing friction force between the universal ball and the anti-slip rubber, the universal ball is locked to prevent it from swinging back and forth when not in use or during landing;

[0028] S8: When the internal thread sleeve described in S7 moves upward, it also drives the corresponding first rack to move upward. Similarly, the movement direction is completely opposite to that of the above-mentioned first rack moving downward. At this time, the two shielding plates change to rotate upward and close, and shield the bottom of the synthetic aperture radar. At this time, the two shielding plates and the spherical shield can form a comprehensive shielding protection for the synthetic aperture radar, and due to the shielding formed by the two shielding plates at the bottom, it can avoid the phenomenon that the ground protrusion directly hits the synthetic aperture radar during landing, thereby improving the protection effect on the synthetic aperture radar;

[0029] S9: When the rectangular block described in S7 moves upward, when the rectangular block moves upward to squeeze and contact the first touch switch, it touches the first touch switch, and at this time, the first touch switch transmits a closing signal to the controller, and the controller controls the driving motor to automatically close, which can automatically and intelligently control the driving motor to close in time, preventing personnel from failing to grasp the closing timing in time;

[0030] S10: When the drone lands and impacts the ground, the synthetic aperture radar will vibrate, driving the mounting plate to move up and down. The mounting plate drives the two guide rods to slide in the corresponding guide grooves respectively. The mounting plate compresses or stretches the two short shock-absorbing springs. Under the elastic force of the short shock-absorbing springs, it can buffer and protect the synthetic aperture radar, weaken the hard impact energy it receives, and further reduce the risk of its damage.

[0031] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0032] The present invention facilitates personnel to quickly remotely control and intelligently synchronously release the fixation and occlusion of the synthetic aperture radar during the flight of the drone, facilitates automatically keeping the synthetic aperture radar always downward during the flight, and facilitates fixing the synthetic aperture radar, occluding the bottom, and damping during landing, reducing the risk of damage caused by factors such as shock force impact and ground protrusion collision during landing, improving its service life, and being beneficial for use. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 is a schematic structural diagram of a geological disaster early identification device based on InSAR technology proposed by the present invention;

[0034] Figure 2 is a schematic cross-sectional structural diagram of a geological disaster early identification device based on InSAR technology proposed by the present invention;

[0035] Figure 3 is Figure 2 the enlarged structural diagram of part A in

[0036] Figure 4 is Figure 2 the enlarged structural diagram of part B in

[0037] Figure 5 is a schematic top view structural diagram of the rectangular seat and ball connector of a geological disaster early identification device based on InSAR technology proposed by the present invention;

[0038] Figure 6 is a schematic top view structural diagram of the shielding plate, fixed seat, rotating shaft and second gear connector of a geological disaster early identification device based on InSAR technology proposed by the present invention;

[0039] Figure 7 is a schematic three-dimensional structural diagram of the fixing plate and spherical shield connector of a geological disaster early identification device based on InSAR technology proposed by the present invention.

[0040] In the figure: 100, synthetic aperture radar; 1, spherical shield; 2, fixing plate; 3, rectangular groove; 4, screw; 5, internally threaded sleeve; 6, rectangular seat; 7, hemispherical hole; 8, universal ball; 9, ball; 10, connecting seat; 11, counterweight; 12, mounting plate; 13, short shock-absorbing spring; 14, guide rod; 15, spherical cavity; 16, spherical ball; 17, shielding plate; 18, rotating shaft; 19, rectangular groove; 20, guide groove; 21, fixed seat; 22, second gear; 23, rectangular sleeve; 24, rectangular rod; 25, third rack; 26, first rack; 27, first gear; 28, second rack; 29, rectangular box; 30, rectangular block; 31, anti-slip rubber; 32, compression spring; 33, first touch switch; 34, controller; 35, drive motor; 36, pressing block; 37, second touch switch; 38, second sprocket; 39, first sprocket; 40, chain. Specific implementation manner

[0041] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying 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.

[0042] Refer to Figures 1-7, a geological disaster early identification device based on InSAR technology, including a fixing plate 2 fixed at the bottom of a drone and a synthetic aperture radar 100. The synthetic aperture radar 100 is located below the fixing plate 2. A spherical shield 1 is fixedly connected to the bottom of the fixing plate 2. The interior of the spherical shield 1 is provided with a rectangular groove 3 with an open bottom. The synthetic aperture radar 100 is located within the rectangular groove 3. A rectangular seat 6 is provided within the rectangular groove 3. A universal ball 8 is movably nested at the top of the rectangular seat 6. The bottom of the universal ball 8 is fixedly connected to a connecting seat 10. The bottom of the connecting seat 10 is fixedly connected to a counterweight 11. A spherical cavity 15 is formed in the counterweight 11. A spherical ball 16 is movably in contact with the bottom inner wall of the spherical cavity 15. The bottom of the counterweight 11 is slidably connected to an elastic guiding mechanism threadedly fixed to the top of the synthetic aperture radar 100. Two nuts are fixed on both sides of the synthetic aperture radar 100. Four threaded grooves are formed in the bottom of the counterweight 11. Bolts are threadedly connected to the corresponding threaded grooves and the inner threads of the threaded grooves. The synthetic aperture radar 100 is threadedly fixed to the counterweight 11 through the four nuts and bolts. A rectangular box 29 with an open bottom is fixedly connected between the front inner wall and the rear inner wall of the rectangular groove 3. A rectangular block 30 with an arc-shaped bottom is slidably sleeved within the rectangular box 29. An anti-slip rubber sheet 31 that is in close contact with the top of the universal ball 8 is adhesively fixed to the bottom of the rectangular block 30. A plurality of compression springs 32 in a compressed state are fixedly connected between the top of the rectangular block 30 and the top inner wall of the rectangular box 29. The two sides of the rectangular seat 6 are fixedly connected to the same intelligent threaded driving mechanism that is rotatably connected to the top inner wall of the rectangular groove 3. The intelligent threaded driving mechanism is fixedly installed on the top of the rectangular box 29. Rectangular grooves 19 are formed on both inner walls of the rectangular groove 3. A force-assisted linkage driving mechanism is fixedly connected to the inner wall of the rectangular groove 19 away from its opening. On one side where the two force-assisted linkage driving mechanisms are close to each other, a shielding plate 17 located below the synthetic aperture radar 100 is fixedly connected. The two shielding plates 17 are symmetrically arranged obliquely. On one side where the two force-assisted linkage driving mechanisms are close to each other, they are fixedly connected to the outer side of the intelligent threaded driving mechanism;

[0043] The elastic guiding mechanism includes a mounting plate 12 arranged below the counterweight 11. The synthetic aperture radar 100 is threadedly fixed to the bottom of the mounting plate 12. Guide rods 14 are fixedly connected to both sides of the top of the mounting plate 12. The counterweight 11 is slidably sleeved on the two guide rods 14. Two short shock-absorbing springs 13 are fixedly connected between the top of the mounting plate 12 and the bottom of the counterweight 11. The short shock-absorbing springs 13 are movably sleeved on the corresponding guide rods 14;

[0044] The intelligent thread driving mechanism includes two screw rods 4 rotatably connected to the inner wall of the top of the rectangular groove 3. A rotating groove is formed in the inner wall of the top of the rectangular groove 3, and a first bearing is fixedly connected in the rotating groove. The inner ring of the first bearing is fixedly connected to the outer side of the corresponding screw rod 4. The screw rod 4 is rotatably connected to the inner wall of the top of the rectangular groove 3 through the corresponding first bearing. An internally threaded sleeve 5 with a sealing structure at the bottom end is sleeved on the screw rod 4. The two sides of the rectangular seat 6 are respectively fixedly connected to the sides of the two internally threaded sleeves 5 close to each other. A driving motor 35 fixedly installed on the top of the rectangular box 29 is arranged between the two screw rods 4. The top end of the output shaft of the driving motor 35 is fixedly connected with a first sprocket 39. A second sprocket 38 is fixedly sleeved on the screw rod 4. The same chain 40 is connected to the two second sprockets 38 and the first sprocket 39 in a transmission manner. A controller 34 electrically connected to the driving motor 35 is fixedly connected to the top of the rectangular box 29. A first touch switch 33 in close contact with the top of the rectangular block 30 is embedded in the top of the rectangular box 29. The touch end of the first touch switch 33 is in movable contact with the top of the rectangular block 30. An embedding hole fixedly connected to the outer side of the first touch switch 33 is formed in the inner wall of the top of the rectangular box 29. The touch end of the first touch switch 33 is located inside the rectangular box 29. A second touch switch 37 is fixedly installed on the right side of the rectangular box 29. A pressing block 36 fixedly connected to the left side of the internally threaded sleeve 5 on the right side is arranged above the second touch switch 37 in a matching manner. Both the first touch switch 33 and the second touch switch 37 are electrically connected to the controller 34. A wireless remote control switch is fixedly connected and electrically connected to the front side of the driving motor 35. The wireless remote control switch is provided with an external remote controller in a matching manner;

[0045] The force - borrowing linkage driving mechanism includes two rectangular sleeves 23 fixedly connected to the inner wall of the side of the corresponding rectangular groove 19 far from its opening. The same rectangular rod 24 is slidably sleeved in the two rectangular sleeves 23 located in the same rectangular groove 19. A first transmission component rotatably connected to the front inner wall and the rear inner wall of the rectangular groove 3 is embedded on the sides of the two rectangular rods 24 close to each other. The sides of the two first transmission components close to each other are respectively fixedly connected to the sides of the two internally threaded sleeves 5 far from each other. A second transmission component rotatably connected to the front inner wall and the rear inner wall of the rectangular groove 3 is embedded at the bottom of the sides of the two rectangular rods 24 close to each other. The sides of the two second transmission components close to each other are respectively fixedly connected to the sides of the two shielding plates 17 far from each other;

[0046] The first transmission component includes a first rack 26 embedded on the side of the corresponding rectangular rod 24 close to the internal thread sleeve 5. Embedding grooves are formed on the mutually approaching sides of the two rectangular rods 24 and are fixedly connected to the outer sides of the corresponding first racks 26 respectively. A first gear 27 rotatably connected between the front inner wall and the rear inner wall of the rectangular groove 3 is meshed with the mutually approaching sides of the two first racks 26. Pin shafts are fixedly connected to the front side and the rear side of the first rack 27. Second bearings are fixedly connected to the front inner wall and the rear inner wall of the rectangular groove 3. The inner rings of the second bearings are fixedly sleeved on the outer sides of the corresponding pin shafts. The first gear 27 is rotatably connected to the front inner wall and the rear inner wall of the rectangular groove 3 through the two pin shafts and the two second bearings. A second rack 28 is meshed with the mutually approaching sides of the two first gears 27. The mutually approaching sides of the two second racks 28 are fixedly connected to the mutually remote sides of the two internal thread sleeves 5 respectively;

[0047] The second transmission component includes a third rack 25 embedded on the side of the corresponding rectangular rod 24 close to the shielding plate 17. A second gear 22 is meshed with the mutually approaching sides of the two third racks 25. Two rotating shafts 18 are rotatably installed between the front inner wall and the rear inner wall of the rectangular groove 3. The two second gears 22 are respectively fixedly sleeved on the corresponding rotating shafts 18. Fixing seats 21 fixedly sleeved on the corresponding rotating shafts 18 are arranged on the front side and the rear side of the second gear 22. The side of the fixing seat 21 close to the corresponding shielding plate 17 is fixedly connected to the shielding plate 17. In this embodiment, it is convenient for personnel to quickly remotely control and synchronously release the fixation and shielding of the synthetic aperture radar 100 during the flight of the unmanned aerial vehicle, and it is convenient to always keep the synthetic aperture radar 100 downward automatically during the flight. Moreover, it is convenient to fix the synthetic aperture radar 100, shield the bottom and reduce vibration during landing, reduce the risk of damage caused by factors such as the impact of the seismic force and the collision with ground protrusions during landing, improve its service life, and is beneficial to use.

[0048] In this embodiment, two guiding grooves 20 are formed at the bottom of the counterweight block 11 and are respectively slidably connected to the outer sides of the corresponding guiding rods 14. Limiting through holes are formed on the mutually remote sides of the two guiding grooves 20. Limiting sliders respectively slidably connected to the corresponding limiting through holes are fixedly connected to the mutually remote sides of the two guiding rods 14. Limiting holes are formed on the inner walls of the two sides of the rectangular box 29. Limiting blocks respectively slidably connected to the corresponding limiting holes are fixedly connected to the two sides of the rectangular block 30. A hemispherical hole 7 is formed at the top of the rectangular seat 6. Two groups of balls 9 are nested in a ring on the inner wall of the hemispherical hole 7. The number of each group of balls 9 is six and they are arranged at equal intervals. This embodiment facilitates the operator to quickly remotely control and synchronously release the fixation and occlusion of the synthetic aperture radar 100 during the flight of the unmanned aerial vehicle, facilitates automatically keeping the synthetic aperture radar 100 downward during the flight, and facilitates fixing, bottom occlusion and shock absorption of the synthetic aperture radar 100 during landing, reducing the risk of damage caused by factors such as the impact of the seismic force and the collision with ground protrusions during landing, improving its service life, and being beneficial for use.

[0049] This embodiment also proposes a usage method of a geological disaster early identification device based on the InSAR technology, including the following steps:

[0050] S1: During use, fix the fixing plate 2 to the bottom of the unmanned aerial vehicle with bolts. When the unmanned aerial vehicle drives this device to fly, the operator uses an external remote controller to remotely control the wireless remote control switch to positively start the driving motor 35. The driving motor 35 drives the first sprocket 39 to rotate. The first sprocket 39 drives two second sprockets 38 to rotate through a chain 40. The two second sprockets 38 drive two screw rods 4 to rotate.

[0051] S2: When the two screw rods 4 in S1 rotate, they drive two internally threaded sleeves 5 to move downward. The two internally threaded sleeves 5 drive the rectangular seat 6 to move downward. The rectangular seat 6 drives the universal ball 8 to move downward. The universal ball 8 gradually relaxes the extrusion force on the anti-slip rubber sheet 31 and separates from the anti-slip rubber sheet 31. At this time, the elastic force of the compression spring 32 in the compressed state drives the rectangular block 30 to slide downward in the rectangular box 29 and separate from the first touch switch 33. The rectangular block 30 drives two limiting blocks to move downward.

[0052] S3: When the internally threaded sleeve 5 in S2 moves downward, it also drives the corresponding second rack 28 to move downward. The second rack 28 drives the corresponding first gear 27 to rotate. The first gear 27 drives the first rack 26 meshed with it to move upward. The first rack 26 drives the corresponding rectangular rod 24 to slide upward in the two rectangular sleeves 23.

[0053] S4: When the rectangular rod 24 in S3 moves upward, it drives the corresponding third rack 25 to move upward. The third rack 25 drives the corresponding second gear 22 to rotate. The second gear 22 drives the two fixing seats 21 to rotate downward through the corresponding rotating shaft 18. The fixing seats 21 drive the corresponding shielding plates 17 to rotate downward and open, removing the shielding of the synthetic aperture radar 100;

[0054] S5: After the universal ball 8 in S2 moves downward and separates from the anti-slip rubber 31, the pressing and fixing state is released. At this time, when the drone tilts during flight, it will drive the whole device to tilt. At this time, under the action of the self-gravity of the counterweight 11, it will always remain vertically downward. Therefore, when tilting at this time, the counterweight 11 will drive the universal ball 8 to rotate adaptively among the multiple balls 9 in the hemispherical hole 7 through the connecting seat 10. Therefore, it will not be affected by external tilting. Therefore, at this time, the counterweight 11 drives the synthetic aperture radar 100 to always remain vertically downward through the two guide rods 14 and the mounting plate 12 in sequence. When tilting occurs during flight, the ball 16 will also move in the spherical cavity 15 and quickly return to the bottom of the spherical cavity 15 under the action of its own gravity, which can assist the counterweight 11 to quickly maintain verticality, and cooperate with the effect of removing the shielding of the synthetic aperture radar 100 in S4, so that the shielding of the synthetic aperture radar 100 can be automatically opened while quickly releasing the fixation during use;

[0055] S6: When the internal thread sleeve 5 in S2 moves downward, it also drives the pressing block 36 to move downward. When the pressing block 36 moves downward and squeezes and contacts the second touch switch 37, it touches the second touch switch 37. At this time, the second touch switch 37 transmits a closing signal to the controller 34, and the controller 34 controls the driving motor 35 to close, which can automatically and intelligently control the driving motor 35 to close in time to prevent personnel from failing to grasp the closing opportunity in time;

[0056] S7: After use, when landing is required, the personnel use an external remote control to operate the wireless remote control switch to reverse-start the driving motor 35. Similarly, the movement direction is completely opposite to that of the above-mentioned forward-starting driving motor 35. At this time, the rectangular seat 6 and the internal thread sleeve 5 change to move upward. The rectangular seat 6 drives the universal ball 8 to move upward and contact and squeeze the anti-slip rubber 31. Under the squeezing force, the anti-slip rubber 31 moves upward and drives the rectangular block 30 to move upward. The rectangular block 30 compresses the compression spring 32. At this time, under the squeezing friction force between the universal ball 8 and the anti-slip rubber 31, the universal ball 8 is locked to prevent it from swinging back and forth when not in use or during landing;

[0057] S8: When the internal-threaded sleeve 5 in S7 moves upward, it also drives the corresponding first rack 28 to move upward. Similarly, the movement direction is completely opposite to that when the first rack 28 moves downward. At this time, the two shielding plates 17 are turned to rotate upward and close, and shield the bottom of the synthetic aperture radar 100. At this time, the two shielding plates 17 and the spherical shield 1 can form a comprehensive shielding protection for the synthetic aperture radar 100. Moreover, due to the shielding formed by the two shielding plates 17 at the bottom, it can avoid the phenomenon that the ground protrusion directly hits the synthetic aperture radar 100 during landing, thereby improving the protection effect on the synthetic aperture radar 100;

[0058] S9: When the rectangular block 30 in S7 moves upward, when the rectangular block 30 moves upward to squeeze and contact the first touch switch 33, it touches the first touch switch 33. At this time, the first touch switch 33 transmits a closing signal to the controller 34, and the controller 34 controls the driving motor 35 to automatically close, which can timely and automatically control the driving motor 35 to close intelligently, preventing personnel from failing to grasp the closing time in time;

[0059] S10: When the unmanned aerial vehicle lands and generates an impact shock force on the ground, at this time, when the synthetic aperture radar 100 vibrates, it will drive the mounting plate 12 to move up and down. The mounting plate 12 drives the two guide rods 14 to slide in the corresponding guide grooves 20 respectively. The mounting plate 12 compresses or stretches the two short shock-absorbing springs 13. Under the elastic force of the short shock-absorbing springs 13, it can play a role in buffering and protecting the synthetic aperture radar 100, weakening the hard impact energy it receives, and further reducing its damage risk.

[0060] As mentioned above, it is only the preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent replacements or changes, and should be covered by the protection scope of the present invention.

Claims

1. A geological disaster early identification device based on InSAR technology, comprising a fixing plate (2) fixed to the bottom of a drone and a synthetic aperture radar (100), the synthetic aperture radar (100) being located below the fixing plate (2), characterized in that, The bottom of the fixed plate (2) is fixedly connected with a spherical shield (1). The interior of the spherical shield (1) is provided with a rectangular groove (3) with an open bottom. The synthetic aperture radar (100) is located in the rectangular groove (3). A rectangular seat (6) is arranged in the rectangular groove (3). A universal ball (8) is movably nested at the top of the rectangular seat (6). The bottom of the universal ball (8) is fixedly connected with a connecting seat (10). The bottom of the connecting seat (10) is fixedly connected with a counterweight block (11). A spherical cavity (15) is formed in the counterweight block (11). A spherical ball (16) is movably contacted with the inner wall of the bottom of the spherical cavity (15). The bottom of the counterweight block (11) is slidably connected with an elastic guiding mechanism that is threadedly fixed to the top of the synthetic aperture radar (100). A rectangular box (29) with an open bottom is fixedly connected between the front inner wall and the rear inner wall of the rectangular groove (3). A rectangular block (30) with an arc-shaped bottom is slidably sleeved in the rectangular box (29). An anti-slip rubber sheet (31) that is in close contact with the top of the universal ball (8) is adhesively fixed to the bottom of the rectangular block (30). A plurality of compression springs (32) in a compressed state are fixedly connected between the top of the rectangular block (30) and the inner wall of the top of the rectangular box (29). The two sides of the rectangular seat (6) are fixedly connected with the same intelligent thread driving mechanism that is rotatably connected to the inner wall of the top of the rectangular groove (3). The intelligent thread driving mechanism is fixedly installed on the top of the rectangular box (29). Rectangular grooves (19) are formed on the inner walls of both sides of the rectangular groove (3). A force-assisted linkage driving mechanism is fixedly connected to the inner wall of one side of the rectangular groove (19) away from its opening. A shielding plate (17) located below the synthetic aperture radar (100) is fixedly connected to one side of the two force-assisted linkage driving mechanisms that are close to each other. The two shielding plates (17) are symmetrically arranged obliquely. One side of the two force-assisted linkage driving mechanisms that are close to each other is fixedly connected to the outer side of the intelligent thread driving mechanism.

2. The geological disaster early identification device based on InSAR technology according to claim 1, characterized in that, The elastic guiding mechanism includes a mounting plate (12) arranged below the counterweight block (11). The synthetic aperture radar (100) is threadedly fixed to the bottom of the mounting plate (12). Guide rods (14) are fixedly connected to both sides of the top of the mounting plate (12). The counterweight block (11) is slidably sleeved on the two guide rods (14). Two short shock-absorbing springs (13) are fixedly connected between the top of the mounting plate (12) and the bottom of the counterweight block (11). The short shock-absorbing springs (13) are movably sleeved on the corresponding guide rods (14).

3. The geological disaster early identification device based on InSAR technology according to claim 1, characterized in that, The intelligent thread driving mechanism includes two screw rods (4) rotatably connected to the inner wall of the top of the rectangular groove (3). An internally threaded sleeve (5) with a plugging structure at the bottom is sleeved on the screw rod (4). One sides of the two internally threaded sleeves (5) close to each other are respectively fixedly connected to both sides of the rectangular seat (6). A driving motor (35) fixedly installed on the top of the rectangular box (29) is arranged between the two screw rods (4). The top end of the output shaft of the driving motor (35) is fixedly connected with a first sprocket (39). A second sprocket (38) is fixedly sleeved on the screw rod (4). The same chain (40) is drivingly connected to the two second sprockets (38) and the first sprocket (39). A controller (34) electrically connected to the driving motor (35) is fixedly connected to the top of the rectangular box (29). A first touch switch (33) in close contact with the top of the rectangular block (30) is embedded in the top of the rectangular box (29). The touch end of the first touch switch (33) is in movable contact with the top of the rectangular block (30). A second touch switch (37) is fixedly installed on the right side of the rectangular box (29). A pressing block (36) fixedly connected to the left side of the internally threaded sleeve (5) on the right side is arranged above the second touch switch (37). Both the first touch switch (33) and the second touch switch (37) are electrically connected to the controller (34). A wireless remote control switch is fixedly and electrically connected to the front side of the driving motor (35). The wireless remote control switch is provided with a matching external remote controller.

4. The geological disaster early identification device based on InSAR technology according to claim 1, characterized in that, The force - borrowing linkage driving mechanism includes two rectangular sleeves (23) fixedly connected to the inner wall of the corresponding rectangular groove (19) away from its opening. The same rectangular rod (24) is slidably sleeved in the two rectangular sleeves (23) located in the same rectangular groove (19). A first transmission assembly rotatably connected to the inner walls of the front and rear sides of the rectangular groove (3) is embedded on one sides of the two rectangular rods (24) close to each other. One sides of the two first transmission assemblies close to each other are respectively fixedly connected to one sides of the two internally threaded sleeves (5) away from each other. A second transmission assembly rotatably connected to the inner walls of the front and rear sides of the rectangular groove (3) is embedded at the bottom of one sides of the two rectangular rods (24) close to each other. One sides of the two second transmission assemblies close to each other are respectively fixedly connected to one sides of the two shielding plates (17) away from each other.

5. The geological disaster early identification device based on InSAR technology according to claim 4, characterized in that, The first transmission assembly includes a first rack (26) embedded on one side of the corresponding rectangular rod (24) close to the internally threaded sleeve (5). A first gear (27) rotatably connected between the inner walls of the front and rear sides of the rectangular groove (3) is meshed with one sides of the two first racks (26) close to each other. A second rack (28) is meshed with one sides of the two first gears (27) close to each other. One sides of the two second racks (28) close to each other are respectively fixedly connected to one sides of the two internally threaded sleeves (5) away from each other.

6. The geological disaster early identification device based on InSAR technology according to claim 4, characterized in that The second transmission component includes third racks (25) embedded on one side of the corresponding rectangular rods (24) close to the shielding plate (17). Second gears (22) are meshed on the sides of the two third racks (25) close to each other. Two rotating shafts (18) are rotatably installed between the front inner wall and the rear inner wall of the rectangular groove (3). The two second gears (22) are respectively fixedly sleeved on the corresponding rotating shafts (18). Fixing seats (21) fixedly sleeved on the corresponding rotating shafts (18) are arranged on the front side and the rear side of the second gears (22). One side of the fixing seat (21) close to the corresponding shielding plate (17) is fixedly connected to the shielding plate (17).

7. An early geological disaster identification device based on InSAR technology according to claim 2, characterized in that Guide grooves (20) respectively slidably connected to the outer sides of the corresponding guide rods (14) are formed at the bottom of the counterweight block (11). Limit through holes are formed on the sides of the two guide grooves (20) away from each other. Limit sliders respectively slidably connected to the corresponding limit through holes are fixedly connected to the sides of the two guide rods (14) away from each other.

8. The geological disaster early identification device based on InSAR technology according to claim 1, characterized in that, Limit holes are formed on the inner walls of both sides of the rectangular box (29). Limit blocks respectively slidably connected to the corresponding limit holes are fixedly connected to both sides of the rectangular block (30).

9. The geological disaster early identification device based on InSAR technology according to claim 1, characterized in that, A hemispherical hole (7) is formed at the top of the rectangular seat (6). Two groups of ball bearings (9) are nested in a ring on the inner wall of the hemispherical hole (7). The number of each group of ball bearings (9) is six and they are arranged at equal intervals.

10. A method for using a geological disaster early identification device based on InSAR technology according to any one of claims 1-9, characterized in that, Comprising the following steps: S1: Fix the fixing plate (2) at the bottom of the unmanned aerial vehicle. By positively starting the driving motor (35), drive the two screw rods (4) to rotate under the cooperation of the first sprocket (39), the chain (40) and the two second sprockets (38). S2: When the two screw rods (4) described in S1 rotate, drive the two internally threaded sleeves (5) to move downward, so that drive the universal ball (8) to separate from the anti-slip rubber sheet (31) through the rectangular seat (6), and the compression spring (32) drives the rectangular block (30) to move downward and separate from the first touch switch (33). S3: When the internally threaded sleeve (5) described in S2 moves downward, drive the corresponding second rack (28) to move downward. The second rack (28) drives the first rack (26) and the rectangular rod (24) to move upward through the corresponding first gear (27). S4: The rectangular rod (24) described in S3 drives the shielding plate (17) to rotate downward and open in sequence through the corresponding third rack (25) and second gear (22), removing the shielding. S5: When the unmanned aerial vehicle tilts during flight, the counterweight block (11) will always remain vertically downward under its own gravity, and drive the universal ball (8) to adaptively rotate among the multiple ball bearings (9), so as to drive the synthetic aperture radar (100) to always remain vertically downward. S6: When the internally threaded sleeve (5) described in S2 moves downward, drive the pressing block (36) to move downward to squeeze and touch the second touch switch (37), so as to control the driving motor (35) to be turned off in time through the controller (34). S7: When landing, reverse-start the drive motor (35). At this time, the rectangular seat (6), the internal-threaded sleeve (5), and the universal ball (8) shift upward. The universal ball (8) squeezes the anti-slip rubber (31) and the rectangular block (30) to move upward and compress the compression spring (32), achieving the pressing and locking of the universal ball (8). S8: When the internal-threaded sleeve (5) described in S7 moves upward, it also drives the corresponding second rack (28) to move upward, achieving the control for the two shielding plates (17) to rotate upward and close to form a bottom shield. S9: When the rectangular block (30) described in S7 moves upward to squeeze and trigger the first touch switch (33), it achieves the control for the drive motor (35) to be automatically and timely turned off through the controller (34). S10: When the drone lands and generates an impact shock force with the ground, the synthetic aperture radar (100) drives the mounting plate (12) to move up and down, and compresses or stretches the two short shock-absorbing springs (13), achieving the shock buffering and protection for the synthetic aperture radar (100).

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