Airborne hyperspectral imaging data acquisition channel monitoring system

Abstract

The invention discloses an airborne hyperspectral imaging data acquisition channel monitoring system, and relates to the technical field of airborne hyperspectral imaging data acquisition channel monitoring, the airborne hyperspectral imaging data acquisition channel monitoring system comprises a mounting rack and a machine body, the mounting rack is arranged on the surface of the machine body, the mounting rack and the machine body are electrically connected, and a lens is arranged at the front end of the machine body. Undercarriages are rotatably mounted at the four corners of the bottom of the unmanned aerial vehicle body, first torsional springs are arranged between the undercarriages and the unmanned aerial vehicle body, when the unmanned aerial vehicle lands, after the undercarriages make contact with the ground, supporting force is provided for equipment, impact force during landing is buffered, and the situation that internal parts are affected by violent shaking during equipment landing is avoided; the foot pad firstly makes contact with the ground and is a first buffering structure, the foot pad can rotate according to the ground terrain during landing, makes contact with the ground at a proper angle, and is fixed after the angle is adjusted according to the inclination degree of the ground when making contact with the ground, stable supporting force is provided for equipment, and the equipment is made to be suitable for various different working environments.

Description

Technical Field

[0001] This invention relates to the field of airborne hyperspectral imaging data acquisition and airway monitoring technology, specifically to an airborne hyperspectral imaging data acquisition and airway monitoring system. Background Technology

[0002] Airborne hyperspectral imaging equipment is an advanced remote sensing technology device that is usually carried on aviation platforms such as drones and airplanes. It is necessary to ensure the stability of the equipment when it follows the drone as it lands and to be able to work for a long time.

[0003] Patent publication number CN112498724B relates to a freely rotatable airborne camera, comprising a mounting plate, a connector, and a camera unit. The mounting plate is connected to the camera unit via the connector. The mounting plate has a through-hole. The connector includes a rotating shaft connected to the through-hole, an L-shaped rod connected to the rotating shaft, and a fork connected to the L-shaped rod. The fork is C-shaped, and through holes are provided at both ends of the fork. The axis of the through holes is perpendicular to the axis of the rotating hole. The camera unit includes a camera and an adjustment plate connected to the camera. Circular bosses are provided at both ends of the adjustment plate, and the circular bosses are coaxially arranged with the through holes.

[0004] In the above invention, an adjustment unit is set up to adjust the angle so as to perform geometric measurement, mutual comparison and composite analysis of image information, reduce data deviation and improve work efficiency. However, since it is an airborne device, a strong impact will be generated when the drone lands, causing the device to shake violently. Over time, this will damage the internal parts of the device and affect the normal use of the device. In particular, the rotatable parts are more likely to be loosened by impact. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides an airborne hyperspectral imaging data acquisition and airway monitoring system, which solves the problems mentioned in the background section.

[0006] To achieve the above objectives, the present invention provides the following technical solution: an airborne hyperspectral imaging data acquisition and airway monitoring system, comprising a mounting frame and a fuselage. The mounting frame is disposed on the surface of the fuselage and the two are electrically connected. A lens is disposed at the front end of the fuselage. Landing gears are rotatably mounted at the four corners of the bottom of the fuselage. A first torsion spring is disposed between the landing gear and the fuselage. When the UAV lands, the landing gear provides support for the equipment after contacting the ground, buffering the impact force during landing and preventing severe shaking of the equipment during landing from affecting internal parts. Foot pads are rotatably mounted at the bottom of the landing gear. The foot pads contact the ground first, serving as a first buffer structure. The foot pads rotate according to the inclination of the ground during landing to contact the ground at a suitable angle. Sliding devices are mounted between the sides of the fuselage and the mounting frame. The landing gear includes a sliding plate with a lifting rod hinged to its surface. A support spring is installed between the lifting rod and the sliding plate. When the lifting rod retracts, it compresses the support spring, which provides elasticity to the lifting rod. Because the mounting frame and the body are connected, the impact force during landing makes the connection point more prone to shaking. The lifting rod locks the mounting frame and the body in place. Sliding rods are slidably mounted on both sides of the sliding plate. When the sliding rods move upward, they lift the sliding plate. A push rod is hinged to the surface of the landing gear. The end of the push rod away from the landing gear is sleeved inside the sliding rod. When the push rod moves, it pushes the sliding rod upward. The two sides of the sliding plate are fixedly connected. A spring is fixedly mounted on the surface of the push rod. The spring contacts the surface of the foot pad. When the push rod moves, it causes the spring to rotate and compress the surface of the foot pad, so that the foot pad is in full contact with the ground and maintains the current angle to provide stable support for the equipment.

[0007] According to the above technical solution, one end of the slide bar is located at the bottom of the slide plate and is not directly connected to the slide plate. Regardless of which part of the landing gear lands first, it will trigger the slide plate to lift and lock the device, so that the landing gear can adapt to landing in various terrains.

[0008] According to the above technical solution, a rotating ring is rotatably installed at the bottom of the fuselage. A second torsion spring is provided between the rotating ring and the fuselage, providing elastic force for the rotating ring to reset. A rotating rod is fixedly installed between the two landing gears at the front end of the fuselage. The rotating rod rotates with the landing gear. The rotating rod passes through the rotating ring. A long protrusion is fixedly installed on the surface of the rotating rod, and a short protrusion is fixedly installed on the inner wall of the rotating ring. The rotation of the rotating rod drives the long protrusion to rotate. After the long protrusion rotates, it pushes the short protrusion, causing the rotating ring to rotate. The rotating rod and the rotating ring are set as indirect transmission, so that the rotating rod and the rotating ring have a sequential reset order. Only when the landing gear is fully retracted and the fuselage is completely away from the ground and dust will the rotating ring drive the cover to reset and open the lens. A curved rod is fixedly installed on the outer wall of the rotating ring, and a cover is fixedly installed on the surface of the curved rod. The surface shape of the cover matches the lens.

[0009] According to the above technical solution, an arc rod is rotatably installed at the bottom of the machine body, and an elastic element is provided between the arc rod and the machine body. A protruding rod is fixedly installed on the surface of the rotating ring. The arc rod has a straight surface and an arc surface continuously arranged on the side near the protruding rod. When the protruding rod rotates, it squeezes the straight surface to make the arc rod rotate, so that the protruding rod can reach the top of the other end of the arc rod through the arc surface. The elastic element provides an upward elastic force to the arc rod, so that when the protruding rod is reset, friction is formed between the arc surface and the protruding rod, so that the rotating ring drives the cover to slowly reset.

[0010] According to the above technical solution, a scraper is rotatably installed between the lens and the camera body. A rack is slidably installed below the scraper. After the rack moves, it pushes the scraper to rotate. A first spring is provided between the rack and the camera body, which provides elastic force for the rack to return to its original position. The rack meshes with the bottom of the scraper. A vibrating bar is fixedly installed at the bottom of the rack. A crank pushes the vibrating bar to move it. When the vibrating bar moves, it drives the rack to move. The vibrating bar bends continuously. Because the surface of the vibrating bar bends continuously in multiple segments, when the crank squeezes the surface of the vibrating bar, the vibrating bar moves rapidly and intermittently in one direction, achieving a vibration effect. The vibrating bar transmits the vibration to the scraper surface through the rack, improving the scraper's ability to remove residual dust from the lens surface. A stop bar is rotatably installed opposite the scraper. A third torsion spring is provided between the stop bar and the camera body.

[0011] According to the above technical solution, the mounting bracket is provided with screws on its surface. The screws are used to install the mounting bracket and the aircraft body on the bottom of the flight equipment. Two clips are hinged to one side of the mounting bracket. The two clips are symmetrically arranged. A fourth torsion spring is provided between the clips and the mounting bracket. When the clips are released from their limiting position, the fourth torsion spring provides elastic force for the clips to open. The surface of the screws and the inner walls of the two clips are threaded together. Through the threaded engagement between the clips and the screws, the mounting bracket is installed on the bottom of the UAV. A limit plate is fixedly installed above the clips. A sliding frame is slidably installed on the surface of the limit plate. A second spring and a third spring are provided between the sliding frame and the limit plate to reset the sliding frame. A connecting rod is slidably installed on the surface of the aircraft body. The connecting rod is fixedly connected to the sliding frame and drives the sliding frame to move. An opening is opened on the surface of the clips. Support rods are fixedly installed on both sides of the sliding frame. A limit rod is sleeved inside the support rod. The limiting rod limits the clamp in the opening, ensuring the clamp is in a closed state. After the landing gear completes one rotation and reset, the support rod drives the limiting rod to complete one up-and-down reciprocating movement, causing the limiting rod to retract into the support rod, releasing the clamp from its limit. The clamp springs open, and the mounting bracket is in a semi-fixed state. At this point, the drone has completed one landing. The operator can choose to inspect the equipment or continue working. If inspection is required, simply pull the motor to detach the mounting bracket from the bottom of the drone. If work is to continue, simply retighten the clamp and push the limiting rod back from the bottom of the support rod. The operation is convenient, and in monitoring environments where frequent equipment retrieval is required, the equipment can be easily inspected without carrying additional tools.

[0012] According to the above technical solution, baffles are slidably installed on both sides of the sliding frame, and a buffer spring is provided between the baffles and the sliding frame. After the clip is opened, it contacts the baffle. The baffle restricts the rotation angle of the clip, so that the clip still partially holds the screw and will not completely separate.

[0013] According to the above technical solution, the support rod is through the top and bottom, and the length of the limiting rod is greater than that of the support rod. The collapsed limiting rod can be lifted and reset from the bottom of the support rod, which is convenient for operation and allows the equipment to be disassembled and re-fixed without the need for other tools.

[0014] This invention provides an airborne hyperspectral imaging data acquisition and airway monitoring system. It features the following:

[0015] Beneficial effects:

[0016] (1) This invention, by setting up landing gear, protects the equipment when it is installed on the surface of flight equipment without a landing buffer mechanism. When it touches the ground, the landing gear rotates and works with the elastic force of the first torsion spring to buffer the equipment from the violent shaking generated when the flight equipment lands, avoiding damage to the internal parts of the equipment due to the strong impact force. Moreover, the foot pads at the bottom of the landing gear can adapt to various terrains. When it touches the ground, the angle is adjusted according to the degree of inclination of the ground before it is fixed, providing stable support for the equipment and making the equipment suitable for various working environments.

[0017] (2) In this invention, when the flying equipment lands, the cover flips to cover the lens and protect the lens from contamination. When the flying equipment such as drones is landing, the rotor generates a large vortex on the ground when it approaches the ground, which causes the ground dust to be stirred up. By temporarily closing the lens, the dust on the lens surface is prevented from affecting the clarity of the subsequently generated image. When it is necessary to work again, the cover will automatically and slowly reset. After the equipment has completely left the dust area, the lens will be reopened. When the cover is closed, it can also peel off any dust that may remain on the lens surface, further ensuring the cleanliness of the lens surface.

[0018] (3) After the device completes a landing, the clamp will open to a certain angle. The mounting bracket is still connected to the flying device, but the device can be directly separated by pulling it out, which makes it easy for staff to disassemble and repair the device. If repair is required, simply pull the machine to detach the mounting bracket from the bottom of the drone. If you want to continue flying, simply squeeze the clamp again and push the limit rod back from the bottom of the support rod. The operation is convenient. In monitoring environments where the device needs to be frequently retrieved, the device can be easily inspected without carrying more tools. Attached Figure Description

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

[0020] Figure 2This is a schematic diagram of the skateboard structure of the present invention;

[0021] Figure 3 This is a schematic diagram of the positional structure of the spring and the rubber pad of the present invention;

[0022] Figure 4 This is a schematic diagram of the arc rod position structure of the present invention;

[0023] Figure 5 This is a schematic diagram of the position structure of the protruding rod and the arc rod of the present invention;

[0024] Figure 6 For the present invention Figure 5 Enlarged view of section A in the middle;

[0025] Figure 7 This is a schematic diagram of the rotating rod structure of the present invention;

[0026] Figure 8 This is a schematic diagram of the position structure of the cover and the crank rod of the present invention;

[0027] Figure 9 This is a schematic diagram showing the position and structure of the scraper and stop bar of the present invention;

[0028] Figure 10 This is a schematic diagram of the clip structure of the present invention;

[0029] Figure 11 This is a schematic diagram showing the position and structure of the support rod and the limiting rod of the present invention;

[0030] Figure 12 This is a schematic diagram of the position and structure of the baffle and buffer spring of the present invention.

[0031] In the diagram: 1. Mounting bracket; 2. Body; 3. Lens; 4. Landing gear; 5. Foot pads; 6. Push rod; 7. Slide rod; 8. Support spring; 9. Lifting rod; 10. Slide plate; 11. Spring; 12. Arc rod; 13. Rotating rod; 14. Rotating ring; 15. Protruding rod; 16. Short protrusion; 17. Long protrusion; 18. Scraper; 19. Rack; 20. Shaking bar; 21. Protective cover; 22. Curved rod; 23. Stop bar; 24. Connecting rod; 25. Screw; 26. Slide frame; 27. Limiting plate; 28. Clamp; 29. ​​Opening; 30. Limiting rod; 31. Buffer spring; 32. Baffle; 33. Support rod. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Please see Figures 1-12 The first embodiment of the present invention is: an airborne hyperspectral imaging data acquisition and airway monitoring system, comprising a mounting frame 1 and a fuselage 2. The mounting frame 1 is disposed on the surface of the fuselage 2 and the two are electrically connected. A lens 3 is disposed at the front end of the fuselage 2. Landing gears 4 are rotatably mounted at the four corners of the bottom of the fuselage 2. A first torsion spring is disposed between the landing gears 4 and the fuselage 2. The first torsion spring provides elastic force for the support of the landing gears 4. When the UAV lands, the landing gears 4 provide support force after contacting the ground. Foot pads 5 are rotatably mounted at the bottom of the landing gears 4. The foot pads 5 contact the ground first and serve as a first buffer structure. Slide plates 10 are slidably mounted between the sides of the fuselage 2 and the mounting frame 1. Lifting rods 9 are hinged to the surface of the slide plates 10. The slide plates 10 move upward. After the lifting rod 9 retracts, a support spring 8 is provided between the lifting rod 9 and the slide plate 10. After the lifting rod 9 retracts, it squeezes the support spring 8, and the support spring 8 provides elastic force for the lifting rod 9. Slide rods 7 are slidably installed on both sides of the slide plate 10. After the slide rods 7 move upward, they lift the slide plate 10. A push rod 6 is hinged to the surface of the landing gear 4. After the landing gear 4 rotates, it drives the push rod 6 to move. The end of the push rod 6 away from the landing gear 4 is sleeved in the slide rod 7. After the push rod 6 moves, it pushes the slide rod 7 to move upward. The two slide plates 10 are fixedly connected. When one slide plate 10 moves upward, it will drive the other slide plate 10 to move simultaneously. A spring piece 11 is fixedly installed on the surface of the push rod 6. The spring piece 11 contacts the surface of the foot pad 5. When the push rod 6 moves, it drives the spring piece 11 to rotate and squeeze the surface of the foot pad 5.

[0034] One end of the slide bar 7 is located at the bottom of the slide plate 10, but is not directly connected to the slide plate 10.

[0035] In this embodiment, as an airborne spectral imaging device, the present invention needs to be installed on the bottom of the drone for large-scale environmental monitoring. Since some drone models are not equipped with landing stabilization buffer devices, the present invention uses landing gear 4 to ensure the stability of the drone during landing, reduce shaking, and avoid damage to the body 2.

[0036] When the drone lands, the landing gear 4 contacts the ground first. Together with the foot pads 5, the elasticity of the first torsion spring in the landing gear 4 cushions the impact of the drone's landing, preventing it from violently shaking and tipping over, thus avoiding damage to the equipment. While cushioning the drone, the landing gear 4 rotates under the pressure of the drone. This rotation drives the push rod 6 to move, which in turn moves the slide rod 7 upwards. The upward movement of the slide rod 7 lifts the sliding plate 10, which in turn moves the lifting rod 9 towards the mounting frame 1. As the sliding plate 10 slowly moves upwards, the lifting rod 9 slowly contracts and compresses the support spring 8, causing it to accumulate elastic potential energy. The contracted support spring 8 provides greater elasticity in the opposite direction to the contraction of the lifting rod 9, providing support between the body 2 and the mounting frame 1. Since the body 2 needs to rotate on the surface of the mounting frame 1 to adjust the monitoring angle during operation, rather than being directly connected to the flight equipment, providing support at the connection between the body 2 and the mounting frame 1 during drone landing prevents violent shaking of the equipment and avoids damage to internal components.

[0037] When the equipment encounters an emergency and needs to make an emergency landing on unpaved ground outdoors, the four landing gears 4 will not touch the ground simultaneously. The sliding plates 10 on both sides of the fuselage 2 are fixedly connected. Movement on one side will cause the other side to move simultaneously, locking the sides of the fuselage 2. The sliding rod 7 is not directly connected to the sliding plate 10, but rather in surface contact. Therefore, whichever landing gear 4 touches the ground first will trigger the sliding plate 10 to lift and lock the fuselage 2. The foot pads 5 are designed to rotate to adapt to different terrains during landing. During landing, they adjust their angle to contact the ground based on their movable characteristics. After the landing gear 4 rotates, the angle between the landing gear 4 and the push rod 6 decreases. The push rod 6 rotates relative to the landing gear 4 surface towards the foot pad 5, causing the spring 11 to press against the surface of the foot pad 5. The pressure applied by the spring 11 to the foot pad 5 temporarily fixes it, stabilizing the equipment. The design of the landing gear 4 and related components ensures the stability of the equipment during landing and is suitable for different environments and road conditions, ensuring a stable landing and preventing damage from violent shaking.

[0038] Please see Figures 1-12In another embodiment of the present invention, based on the above embodiments, a rotating ring 14 is rotatably mounted on the bottom of the fuselage 2. A second torsion spring is provided between the rotating ring 14 and the fuselage 2. The second torsion spring provides elastic force for the rotating ring 14 to return to its original position. A rotating rod 13 is fixedly mounted between the two landing gears 4 at the front end of the fuselage 2. The rotating rod 13 rotates with the landing gear 4. The rotating rod 13 passes through the rotating ring 14. A long protrusion 17 is fixedly mounted on the surface of the rotating rod 13. A short protrusion 16 is fixedly mounted on the inner wall of the rotating ring 14. The rotation of the rotating rod 13 drives the long protrusion 17 to rotate. After the long protrusion 17 rotates, it pushes the short protrusion 16, causing the rotating ring 14 to rotate. A curved rod 22 is fixedly mounted on the outer wall of the rotating ring 14. A cover 21 is fixedly mounted on the surface of the curved rod 22. The surface shape of the cover 21 matches the lens 3. When the rotating ring 14 rotates, it drives the curved rod 22 to rotate, causing the cover 21 to rotate and cover the surface of the lens 3.

[0039] An arc rod 12 is rotatably mounted on the bottom of the body 2. An elastic element is provided between the arc rod 12 and the body 2. The elastic element provides an upward elastic force to the arc rod 12. A protruding rod 15 is fixedly mounted on the surface of the rotating ring 14. The side of the arc rod 12 near the protruding rod 15 has a straight surface and an arc surface. When the protruding rod 15 rotates, it squeezes the straight surface to make the arc rod 12 rotate, so that the protruding rod 15 can reach the other end of the arc rod 12 through the arc surface. When the protruding rod 15 returns to its original position, the arc surface provides friction for the protruding rod 15.

[0040] A scraper 18 is rotatably mounted between the lens 3 and the body 2. A rack 19 is slidably mounted below the scraper 18. When the rack 19 moves, it pushes the scraper 18 to rotate. A first spring is provided between the rack 19 and the body 2. The first spring provides elastic force for the rack 19 to return to its original position. The rack 19 meshes with the bottom of the scraper 18. A vibrating strip 20 is fixedly mounted at the bottom of the rack 19. A crank 22 pushes the vibrating strip 20 to move it. When the vibrating strip 20 moves, it drives the rack 19 to move. The vibrating strip 20 bends continuously. The vibrating strip 20 vibrates while moving. A stop bar 23 is rotatably mounted opposite the scraper 18. After the scraper 18 rotates, it pushes open the stop bar 23 and rotates to open it, allowing dust to fall off the surface of the glass lens 3. A third torsion spring is provided between the stop bar 23 and the body 2. The third torsion spring returns the stop bar 23 to its original position and closes it.

[0041] In this embodiment, when the landing gear 4 rotates, it drives the long protrusion 17 to rotate, which in turn drives the short protrusion 16 to rotate, causing the rotating ring 14 to rotate. After the rotating ring 14 rotates, it drives the cover 21 to rotate and cover the lens 3, thus shielding the lens 3 and preventing dust from being stirred up by the airflow of the drone rotor during landing from contaminating the surface of the lens 3. At the same time, the protruding rod 15 on the surface of the rotating ring 14 rotates with the rotating ring 14, passing over the straight and curved surfaces of the arc rod 12. When the drone takes off again, the landing gear 4 leaves the ground, and the cover 21 resets under the elastic force of the second torsion spring, causing the rotating ring 14 and the protruding rod 15 to rotate and reset. When the protruding rod 15 resets, it will be subjected to the elastic force of the arc rod 12, providing a reverse frictional force in the reset direction of the protruding rod 15, causing the protruding rod 15 to reset slowly, thereby causing the cover 21 to reset slowly. It will only reopen when the drone has fully taken off and is far away from the ground, ensuring that the lens 3 is still protected by the cover 21 during the drone's ascent. It will only enter the working state after it is completely away from the ground dust.

[0042] When the rotating ring 14 rotates, it drives the crank 22 to rotate. After the crank 22 rotates, it pushes the vibrating bar 20 to move. The vibrating bar 20 drives the rack 19 to move. After the rack 19 moves, it pushes the scraper 18 to rotate towards the lens 3 to remove any dust that may remain on the surface of the lens 3. After the scraper 18 rotates to a certain angle, it pushes the baffle 23 to rotate and open. The dust removed by the scraper 18 will fall off through the gap after the baffle 23 is opened, keeping the surface of the lens 3 clean and ensuring the clarity of the image captured by the device.

[0043] Please see Figures 1-12 Based on the above embodiments, in another embodiment of the present invention, the mounting bracket 1 is provided with screws 25, which fix the mounting bracket 1 to the UAV. The screws 25 are used to install the mounting bracket 1 and the body 2 on the bottom of the flight equipment. Two clips 28 are hinged to one side of the mounting bracket 1. The two clips 28 are symmetrically arranged. A fourth torsion spring is provided between the clips 28 and the mounting bracket 1. When the clips 28 are released from their limit, the fourth torsion spring provides elastic force for the clips 28 to open. The surface of the screws 25 is threadedly engaged with the inner walls of the two clips 28. When the two clips are engaged, the screws 25 can be used to open the UAV. When clamp 28 is closed, the inner wall formed is threadedly engaged with the surface of clamp 28. A limit plate 27 is fixedly installed above clamp 28, and a sliding frame 26 is slidably installed on the surface of limit plate 27. A second spring and a third spring are provided between sliding frame 26 and limit plate 27 to reset sliding frame 26. A connecting rod 24 is slidably installed on the surface of body 2 and is fixedly connected to sliding frame 26. Connecting rod 24 drives sliding frame 26 to move. An opening 29 is opened on the surface of clamp 28, and support rods 33 are fixedly installed on both sides of sliding frame 26. A limit rod 30 is sleeved inside the support rod 33. The limit rod 30 limits clamp 28 in the opening 29 to ensure that clamp 28 is in the closed state.

[0044] The slide frame 26 is slidably mounted with baffles 32 on both sides. A buffer spring 31 is provided between the baffles 32 and the slide frame 26. When the clip 28 is opened, it contacts the baffles 32, and the baffles 32 restrict the rotation angle of the clip 28.

[0045] The support rod 33 runs vertically through the body, and the length of the limiting rod 30 is greater than that of the support rod 33. The collapsed limiting rod 30 can be lifted and reset from the bottom of the support rod 33.

[0046] In this embodiment, during operation: when the equipment descends, the crank 22 rotates and contacts and lifts the connecting rod 24. The connecting rod 24 drives the sliding frame 26 to move upward, which in turn drives the support rod 33 and the limiting rod 30 to move upward. After moving upward, the limiting rod 30 is limited by the limiting plate 27 and retracts into the support rod 33. At this time, the limiting rod 30 is flush with the top of the support rod 33. When the operator needs to inspect the descended equipment, after picking up the equipment, the landing gear 4 retracts, the connecting rod 24 drives the sliding frame 26 to reset, and at the same time, the support rod 33 resets, causing the limiting rod 30 to move downward. Since the limiting rod 30 is now flush with the initial... The device shifts position and is no longer inside opening 29, releasing the restraint on clip 28. Clip 28 rotates to both sides under the elastic force of the fourth torsion spring. At this point, if the operator needs to inspect or repair the device 2, they only need to pull the device 2 to disengage the mounting bracket 1 from the screw 25, and the device 2 can be removed for inspection. Moreover, after the clip 28 rotates open, it is restrained by the baffle 32 and will not fully open. At the same time, the buffer spring 31 provides elastic force for the baffle 32 to restrain it. Clip 28 can both keep the mounting bracket 1 connected to the drone for easy re-fixing and can be easily disengaged. If inspection or repair is not required, simply squeeze clip 28 and push the restraint rod 30 back into opening 29 to fix clip 28 and continue working.

[0047] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An airborne hyperspectral imaging data acquisition flight path monitoring system comprising a mounting rack (1) and a body (2), characterized in that: The mounting frame (1) is arranged on the surface of the body (2), and the two are electrically connected, the front end of the body (2) is provided with a lens (3), the bottom of the body (2) is rotatably provided with landing gear (4) at four corners, the first torsional spring is arranged between the landing gear (4) and the body (2), the foot pad (5) is rotatably arranged at the bottom of the landing gear (4), the sliding plate (10) is slidably arranged between the two sides of the body (2) and the mounting frame (1), the lifting rod (9) is hingedly arranged on the surface of the sliding plate (10), the supporting spring (8) is arranged between the lifting rod (9) and the sliding plate (10), the sliding rod (7) is slidably arranged on the two sides of the sliding plate (10), the push rod (6) is hingedly arranged on the surface of the landing gear (4), and one end of the push rod (6) away from the landing gear (4) is sleeved in the sliding rod (7).

2. The airborne hyperspectral imaging data acquisition fairway monitoring system according to claim 1, characterized in that: The surface of the push rod (6) is fixedly provided with the elastic sheet (11), and the surface of the elastic sheet (11) is in contact with the foot pad (5).

3. The airborne hyperspectral imaging data acquisition fairway monitoring system according to claim 1, wherein: The two sliding plates (10) are fixedly connected, and one end of the sliding rod (7) is located at the bottom of the sliding plate (10) and is not directly connected with the sliding plate (10).

4. The airborne hyperspectral imaging data acquisition fairway monitoring system according to claim 1, characterized in that: The body (2) is rotatably provided with a rotating ring (14), the body (2) is fixedly provided with a rotating rod (13) between the two landing gears (4) at the front end, the rotating rod (13) penetrates the rotating ring (14), the long protrusion (17) is fixedly arranged on the surface of the rotating rod (13), the short protrusion (16) is fixedly arranged on the inner wall of the rotating ring (14), the curved rod (22) is fixedly arranged on the outer wall of the rotating ring (14), the cover (21) is fixedly arranged on the surface of the curved rod (22), and the surface shape of the cover (21) is consistent with the lens (3).

5. The airborne hyperspectral imaging data acquisition fairway monitoring system according to claim 1, wherein: The body (2) is rotatably provided with an arc rod (12), the elastic member is arranged between the arc rod (12) and the body (2), and the convex rod (15) is fixedly arranged on the surface of the rotating ring (14).

6. The airborne hyperspectral imaging data acquisition flight path monitoring system of claim 5, wherein: The second torsional spring is arranged between the rotating ring (14) and the body (2), and the straight surface and the arc surface are continuously arranged on one side of the arc rod (12) close to the convex rod (15).

7. The airborne hyperspectral imaging data acquisition flight path monitoring system of claim 1, wherein: The lens (3) is rotatably provided with a scraping strip (18) between the body (2), the rack (19) is slidably arranged below the scraping strip (18), the first spring is arranged between the rack (19) and the body (2), the rack (19) is engaged with the bottom of the scraping strip (18), the shaking strip (20) is fixedly arranged at the bottom of the rack (19), the shaking strip (20) is continuously bent, the blocking strip (23) is rotatably arranged opposite to the scraping strip (18), and the third torsional spring is arranged between the blocking strip (23) and the body (2).

8. The airborne hyperspectral imaging data acquisition flight path monitoring system of claim 1, wherein: The mounting frame (1) is provided with screws (25) for mounting the mounting frame (1) and the body (2) on the bottom of the flying device, one side of the mounting frame (1) is hingedly connected with two clamps (28), the two clamps (28) are symmetrically arranged, a fourth torsional spring is arranged between the clamp (28) and the mounting frame (1), the surface of the screw (25) is threadedly connected with the inner walls of the two clamps (28), a limiting plate (27) is fixedly installed above the clamp (28), a sliding frame (26) is slidably installed on the surface of the limiting plate (27), the sliding frame (26) and the limiting plate (27) are provided with a second spring, a connecting rod (24) is slidably installed on the surface of the body (2), the connecting rod (24) is fixedly connected with the sliding frame (26), an opening (29) is formed in the surface of the clamp (28), support rods (33) are fixedly installed on the two sides of the sliding frame (26), and the support rods (33) are internally sleeved with limiting rods (30).

9. The airborne hyperspectral imaging data acquisition flight path monitoring system of claim 8, wherein: The sliding frame (26) is slidably installed with baffles (32) on the two sides, and buffer springs (31) are arranged between the baffles (32) and the sliding frame (26).

10. The airborne hyperspectral imaging data acquisition flight path monitoring system of claim 8, wherein: The support rods (33) are through-penetrating, and the limiting rods (30) are longer than the support rods (33).

Images