A rotor unmanned aerial vehicle for geophysical prospecting is disclosed, which comprises a rotor unmanned aerial vehicle body, a magnetic sensor, a magnetic field total field detection system, a power

Abstract

The application belongs to the technical field of aeromagnetic detection, in particular to a rotary-wing unmanned aerial vehicle aeromagnetic total field detection system for geophysical prospecting, which comprises a rotary-wing unmanned aerial vehicle and a probe rod, the bottom end of the rotary-wing unmanned aerial vehicle is fixedly provided with a mounting block, the probe rod is slidably arranged in the mounting block, a control block is slidably arranged in the mounting block, a moving block is elastically arranged in the mounting block, the control block is connected with the moving block through a connecting rod, a clamping assembly is arranged in the control block and clamps the probe rod through rotation of the control block, a moving assembly is arranged in the mounting block and is used for driving the control block to slide in the mounting block, and a shifting assembly is arranged in the mounting block and is used for driving the control block to rotate. Through cooperation of the above structures, the probe rod can be effectively retracted, and the area required when the unmanned aerial vehicle lands is reduced.

Description

Technical Field

[0001] This invention belongs to the field of aeromagnetic detection technology, specifically a geophysical exploration-specific rotary-wing UAV aeromagnetic total field detection system. Background Technology

[0002] To address the need for efficient airborne geomagnetic field exploration, a mature manned helicopter platform was selected. Combined with my country's experience in UAV development and advanced technologies, a heavy-payload, rotor-driven, combined-mount, intelligent autonomous flight, and ground-based remote telemetry and control rotor-wing UAV system was developed to meet the requirements of geophysical magnetic field detection. This system possesses three-dimensional precise navigation and autonomous obstacle avoidance capabilities. A set of rigid-frame and pod-type aeromagnetic payload devices was also developed to meet low magnetic and low static electricity requirements. Finally, an intelligent, heavy-payload, geophysical exploration-specific rotor-wing UAV detection system with the capability to carry aeromagnetic field sensors was developed. This system features vertical takeoff and landing, rapid translation, large radius, long endurance, low magnetic field, and low static electricity, enabling it to operate in complex terrains such as mountainous areas and canyons.

[0003] However, in mountainous areas with complex terrain, the landing site of a rotary-wing UAV equipped with an extended probe will have certain requirements. At least within the diameter of the probe, there should be no large obstructions in the space to ensure a normal landing. However, such sites are not readily available in mountainous areas with complex terrain, so finding a site will also add some trouble to the detection.

[0004] However, when deploying rotary-wing UAVs equipped with extended probes in mountainous areas with complex terrain, the landing process has specific requirements for the landing site. Specifically, there must be no large obstacles within the area covered by the probe diameter to ensure that the UAV can land safely and smoothly. However, given the complexity of mountainous terrain, landing sites that meet this condition are not readily available, which undoubtedly adds a certain degree of difficulty and challenge to the execution of the reconnaissance mission.

[0005] Therefore, the present invention provides a geophysical exploration-specific rotary-wing UAV aeromagnetic total field detection system. Summary of the Invention

[0006] In order to overcome the shortcomings of the prior art, at least one technical problem raised in the background art is solved.

[0007] The technical solution adopted by the present invention to solve its technical problem is: the geophysical exploration-specific rotary-wing UAV aeromagnetic total field detection system of the present invention includes a rotary-wing UAV and a probe rod. A mounting block is fixedly installed at the bottom of the rotary-wing UAV. The probe rod is slidably installed inside the mounting block. A control block is slidably installed inside the mounting block. A movable block is elastically installed inside the mounting block. The control block and the movable block are connected by a connecting rod. The clamping assembly is located inside the control block and clamps the probe rod by rotating the control block; The movable component, located inside the mounting block, is used to drive the control block to slide within the mounting block; The shifting component, located inside the mounting block, is used to drive the control block to rotate.

[0008] The clamping assembly includes a first sliding groove, a first pressure ball, and a first pressure plate. The first sliding groove is formed inside the control block, the first pressure plate is fixedly installed inside the first sliding groove, and the first pressure ball is slidably installed inside the first sliding groove.

[0009] The moving component includes a pull rope, a take-up roller, and a power component. One end of the pull rope is fixedly connected to the side wall of the moving block, and the other end of the pull rope is fixedly connected to the take-up roller. The take-up roller is rotatably mounted inside the mounting block, and the power component is located inside the mounting block to control the rotation of the take-up roller.

[0010] The power assembly includes a first bevel gear, a second bevel gear, a drive roller, and a drive motor. The first bevel gear is fixedly installed at one end of the take-up roller, the drive roller is rotatably installed inside the mounting block, the second bevel gear is fixedly installed at the end of the drive roller near the first bevel gear, and the drive motor is fixedly installed at the bottom end of the drive roller. The first bevel gear meshes with the second bevel gear.

[0011] The displacement assembly includes a first push rod, a second push rod, and a pressing wedge. The first push rod is fixedly installed at one end of the control block away from the moving block. The first push rod is symmetrically installed at the other end of the control block. The pressing wedge is located inside the mounting block and close to the first push rod. There are two pressing wedges, which are symmetrically arranged inside the mounting block.

[0012] The mounting block has a first groove and a second groove inside. A guide rod is elastically installed on the top of the control block, and the end of the guide rod near the second groove is inclined.

[0013] The mounting block has a reciprocating threaded rod inside, which rotates, and a control rod is slidably mounted on the reciprocating threaded rod.

[0014] The first gear is fixedly installed at the end of the take-up roller away from the first bevel gear, and the second gear is fixedly installed at one end of the reciprocating threaded rod. The first gear meshes with the second gear.

[0015] A support block is fixedly installed at the bottom of the rotary-wing drone. A second sliding groove is opened inside the support block. A second top pressure plate is fixedly installed inside the second sliding groove. A second top pressure ball is slidably installed inside the second sliding groove.

[0016] The beneficial effects of this invention are as follows: 1. The geophysical exploration-specific rotary-wing UAV aeromagnetic field detection system of the present invention controls the rotation of the winding roller to wind up the pull rope. At this time, the moving block drives the control block to slide the first top pressure ball, which slides to the right inside the first sliding groove under the friction with the probe rod, thereby pressing the probe rod and retracting the probe rod, which facilitates the landing of the rotary-wing UAV and improves the adaptability of the rotary-wing UAV to the landing point.

[0017] 2. The aeromagnetic field detection system for a rotary-wing UAV dedicated to geophysical exploration described in this invention uses a drive motor to rotate a take-up roller. The rotation of a first gear drives a second gear to control the rotation of a reciprocating threaded rod. A control rod set on the reciprocating threaded rod can slide back and forth on the outer wall of the reciprocating threaded rod. The pull rope passes through the control rod. Therefore, when the control rod slides back and forth, it can drive the pull rope to move on the take-up roller, which can improve the pull rope winding effect, avoid the wire pressing situation, and improve the service life of the pull rope. Attached Figure Description

[0018] The invention will now be further described with reference to the accompanying drawings.

[0019] Figure 1 This is a perspective view of the present invention; Figure 2 This is a schematic diagram of the probe structure in this invention; Figure 3 In this invention Figure 2 Enlarged view of point A in the image; Figure 4 This is a cross-sectional view of the mounting block in this invention; Figure 5 In this invention Figure 4 Enlarged view of point B in the image; Figure 6 This is a cross-sectional view of the support block in this invention; Figure 7 This is a schematic diagram of the mounting block in this invention; Figure 8 In this invention Figure 7 Enlarged view of point C in the image; Figure 9 This is a cross-sectional view of the control block in this invention.

[0020] In the diagram: 1. Rotary-wing UAV; 2. Probe rod; 3. Mounting block; 4. Support block; 5. Second sliding groove; 6. Second top pressure plate; 7. Second top pressure ball; 8. Control block; 9. First top rod; 10. Top pressure wedge; 11. Guide rod; 12. First sliding groove; 13. Second sliding groove; 14. Second top rod; 15. Connecting rod; 16. Pull rope; 17. Take-up roller; 18. First bevel gear; 19. Transmission roller; 20. Second bevel gear; 21. First gear; 22. Second gear; 23. Reciprocating threaded rod; 24. Control rod; 25. First sliding groove; 26. First top pressure plate; 27. First top pressure ball; 28. Moving block; 29. ​​Drive motor. Detailed Implementation

[0021] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with specific embodiments.

[0022] like Figures 1 to 9 As shown in the embodiment of the present invention, a geophysical exploration-specific rotary-wing UAV aeromagnetic total field detection system includes a rotary-wing UAV 1 and a probe 2.

[0023] The probe rod 2 is divided into three sections: front section, middle section, and rear section; the three sections are connected by a recessed insertion method and connected with non-magnetic copper bolts.

[0024] Probe 2 front section: This section is the probe installation section, 1.22m long and 3mm thick. The material is fiberglass prepreg, and the thickness and layup are calculated based on experience. According to the instrument layout requirements, the probe can rotate along the axis. A three-component magnetometer is installed behind the total field probe.

[0025] Probe 2 Middle Section: This section is the equipment installation section, 3m long and 6mm thick, made of carbon fiber prepreg, with the thickness and layup calculated based on experience. According to the instrument layout requirements, it is equipped with front and rear GPS antennas, an optical pump magnetometer electronic box, and an inertial navigation module. The center distance between the front and rear GPS antennas is required to be no less than 1.5m. The three-component magnetometer is installed at the front of probe 2 because it needs to be far away from the inertial navigation. The inertial navigation and rear GPS antennas can be placed together.

[0026] A mounting block 3 is fixedly installed at the bottom of the rotary-wing UAV 1. A probe rod 2 is slidably installed inside the mounting block 3. A control block 8 is slidably installed inside the mounting block 3. A movable block 28 is elastically installed inside the mounting block 3. The control block 8 and the movable block 28 are connected by a connecting rod 15. The connecting rod 15 is fixedly installed at the end of the control block 8 near the movable block 28. A guide groove is opened inside the movable block 28. A spring is provided between the connecting rod 15 and the guide groove.

[0027] The probe 2 is fixed to the underside of the rotorcraft UAV 1 via the mounting block 3. The rotorcraft UAV 1 generates lift and attitude changes by changing the rotational speed and periodic pitch of the main rotor and tail rotor. The flight control computer collects the aircraft's attitude and position information and performs real-time control of the rotational speed and periodic pitch through calculation, thereby achieving autonomous flight. Remote communication and control between the ground control station and the aircraft are achieved through a communication data link. Precise position information is obtained through GPS, IMU, and altimeter, thereby achieving three-dimensional precise navigation flight. Obtaining distant obstacles is achieved through machine vision sensors and microwave radar, and the flight control system makes decisions and generates avoidance actions, thereby achieving autonomous obstacle avoidance flight. According to the aeromagnetic operation specifications, a special mounting device is designed for the aeromagnetic instruments to be carried, meeting the requirements of no magnetism or low magnetism, thereby realizing the UAV aeromagnetic operation.

[0028] The clamping assembly is located inside the control block 8 and clamps the probe rod 2 by rotating the control block 8; When the control block 8 rotates, the outer wall of the probe rod 2 can be clamped by the clamping assembly. At this time, the movement of the control block 8 will simultaneously drive the probe rod 2.

[0029] A movable component is set inside the mounting block 3 to drive the control block 8 to slide inside the mounting block 3. The movable component can drive the control block 8 to slide. When the control block 8 slides inside the mounting block 3, the probe 2 can be moved and the extended probe 2 can be retracted. At this time, when the rotor drone 1 lands, it can land in an area with a small open space.

[0030] The shifting component is located inside the mounting block 3 and is used to drive the control block 8 to rotate. The shifting component can drive the control block 8 to rotate inside the mounting block 3.

[0031] The clamping assembly includes a first sliding groove 25, a first pressing ball 27, and a first pressing plate 26. The first sliding groove 25 is formed inside the control block 8, the first pressing plate 26 is fixedly installed inside the first sliding groove 25, and the first pressing ball 27 is slidably installed inside the first sliding groove 25.

[0032] The first sliding groove 25 is formed inside the control block 8. The opening at the bottom of the first sliding groove 25 contacts the probe rod 2. The first top pressure plate 26 is located at the end of the first sliding groove 25 away from the probe rod 2. The first top pressure plate 26 is inclined. The first top pressure ball 27 is located between the first top pressure plate 26 and the probe rod 2. When the first top pressure ball 27 is located at the leftmost side of the first sliding groove 25, it will contact the probe rod 2. When the control block 8 moves to the left inside the mounting block 3, the first top pressure ball 27 will slide to the right inside the first sliding groove 25 under the friction with the probe rod 2. Under the action of the inclined first top pressure plate 26, the first top pressure ball 27 will press against the outer wall of the probe rod 2, thus pressing the probe rod 2. When the control block 8 slides to the left inside the mounting block 3, it will simultaneously drive the probe rod 2 to slide to the left. At this time, the probe rod 2 can be retracted, making it easier for the rotor drone 1 to land.

[0033] The probe 2, which has been retrieved after landing, can be manually re-extended.

[0034] The moving assembly includes a pull rope 16, a take-up roller 17, and a power assembly. One end of the pull rope 16 is fixedly connected to the side wall of the moving block 28, and the other end of the pull rope 16 is fixedly connected to the take-up roller 17. The take-up roller 17 is rotatably mounted inside the mounting block 3. The power assembly is located inside the mounting block 3 and is used to control the rotation of the take-up roller 17.

[0035] By controlling the rotation of the take-up roller 17, the pull rope 16 can be wound up. When the pull rope 16 is wound up, the moving block 28 will slide toward the position of the take-up roller 17. Under the action of the connecting rod 15, the control block 8 will also slide. A spring is provided at one end of the moving block 28 away from the control block 8, and the other end is connected to the inside of the mounting block 3. Therefore, when the moving block 28 slides to the left when the pull rope 16 is wound up, the spring will also deform and store elastic potential energy.

[0036] The power assembly includes a first bevel gear 18, a second bevel gear 20, a drive roller 19, and a drive motor 29. The first bevel gear 18 is fixedly mounted on one end of the take-up roller 17. The drive roller 19 is rotatably mounted inside the mounting block 3. The second bevel gear 20 is fixedly mounted on one end of the drive roller 19 near the first bevel gear 18. The drive motor 29 is fixedly mounted on the bottom end of the drive roller 19. The first bevel gear 18 meshes with the second bevel gear 20.

[0037] The drive motor 29 starts and drives the transmission roller 19 to rotate. At this time, the second bevel gear 20 drives the first bevel gear 18 to rotate, so the winding roller 17 can wind up the pull rope 16. The reverse rotation of the drive motor 29 can unwind the pull rope 16. The spring on the moving block 28 releases the elastic potential energy and drives the moving block 28 to slide to the right side of the mounting block 3 for reset.

[0038] The displacement assembly includes a first push rod 9, a second push rod 14, and a pressing wedge 10. The first push rod 9 is fixedly installed at one end of the control block 8 away from the moving block 28. The first push rod 9 is symmetrically installed at the other end of the control block 8. The pressing wedge 10 is disposed inside the mounting block 3 and close to the first push rod 9. There are two pressing wedges 10, which are symmetrically disposed inside the mounting block 3.

[0039] One of the top-pressing wedges 10 is located on the right side of the mounting block 3 and the other is located on the left side of the mounting block 3. When the control block 8 is located on the far right side of the mounting block 3, the first push rod 9 will disengage from the top-pressing wedge 10 located on the right side. By setting the top-pressing wedge 10, the control block 8 can rotate clockwise inside the mounting block 3. At the same time, the connecting rod 15 will slide inside the guide groove and press the spring.

[0040] At this time, when the moving block 28 drives the control block 8 to slide to the left, the first push rod 9 moves away from the top wedge block 10, and the spring releases its elastic potential energy to reset the connecting rod 15 inside the guide groove, and at the same time resets the control block 8. Until the control block 8 slides to the leftmost side, the cooperation between the second push rod 14 and the top wedge block 10 located on the left side will cause the control block 8 to rotate clockwise again.

[0041] A support block 4 is fixedly installed at the bottom of the rotary-wing drone 1. A second sliding groove 5 is opened inside the support block 4. A second top pressure plate 6 is fixedly installed inside the second sliding groove 5. A second top pressure ball 7 is slidably installed inside the second sliding groove 5.

[0042] The support block 4 is set on one side of the mounting block 3 to improve the installation stability of the probe rod 2. Through the second sliding groove 5 and the second top pressure ball 7, the second top pressure ball 7 can clamp the probe rod 2 when it rotates clockwise.

[0043] The mounting block 3 has a first groove 12 and a second groove 13 inside. A guide rod 11 is elastically mounted on the top of the control block 8. The end of the guide rod 11 near the second groove 13 is inclined.

[0044] When the control block 8 is on the far right, the top wedge block 10 will press the control block 8 to rotate clockwise, and the second top ball 7 will clamp the probe rod 2. When the control block 8 moves to the left, the control block 8 away from the top wedge block 10 will immediately rotate counterclockwise to reset under the action of the spring. As the control block 8 slides, the guide rod 11 enters the interior of the first slide groove 12. At this time, the support block 4 releases the clamp on the probe rod 2, and the control block 8 clamps the probe rod 2. Therefore, by sliding the control block 8 to the left, the probe rod 2 can be retracted, thereby reducing the problem of the probe rod 2 extending and requiring a large landing area.

[0045] When the control block 8 slides to the far left, the second push rod 14 presses against the left-side push wedge block 10, causing the control block 8 to rotate the guide rod 11 clockwise and rotate the guide rod 11 into the interior of the second slide groove 13. At this time, when the control block 8 slides to the right to reset, the support block 4 will lock the current position of the probe rod 2. The control block 8 will not clamp the probe rod 2 when sliding to the right, which facilitates the reset of the control block 8 and will not drive the probe rod 2 to move. By repeating the above operation, the probe rod 2 can be retracted, thereby reducing the space required for landing and making it suitable for more areas.

[0046] The reciprocating threaded rod 23 is rotatably mounted inside the mounting block 3, and the control rod 24 is slidably mounted on the reciprocating threaded rod 23.

[0047] The take-up roller 17 has a first gear 21 fixedly installed at one end away from the first bevel gear 18, and a second gear 22 fixedly installed at one end of the reciprocating threaded rod 23. The first gear 21 and the second gear 22 mesh.

[0048] When the take-up roller 17 rotates, it can drive the first gear 21 to rotate. At the same time, the second gear 22 will drive the reciprocating threaded rod 23 to rotate. The control rod 24 set on the reciprocating threaded rod 23 can slide back and forth on the outer wall of the reciprocating threaded rod 23. The pull rope 16 passes through the control rod 24. Therefore, when the control rod 24 slides back and forth, it can drive the pull rope 16 to move on the take-up roller 17, which can improve the winding effect of the pull rope 16 and avoid the situation of pressing the wire.

[0049] Working principle: By controlling the rotation of the take-up roller 17, the pull rope 16 can be wound up. When the pull rope 16 is wound up, the moving block 28 will slide towards the position of the take-up roller 17. Under the action of the connecting rod 15, the control block 8 will also slide. At this time, the first pressure ball 27 will slide to the right inside the first sliding groove 25 under the friction with the probe 2. Under the action of the inclined first pressure plate 26, the first pressure ball 27 will press against the outer wall of the probe 2, thus pressing the probe 2. At this time, when the control block 8 slides to the left inside the mounting block 3, it will simultaneously drive the probe 2 to slide to the left, which can retract the probe 2, making it easier for the rotor drone 1 to land and improving the adaptability of the rotor drone 1 to the landing point.

[0050] When the drive motor 29 drives the take-up roller 17 to rotate, the rotation of the first gear 21 will drive the second gear 22 to control the rotation of the reciprocating threaded rod 23. The control rod 24 set on the reciprocating threaded rod 23 can slide back and forth on the outer wall of the reciprocating threaded rod 23. The pull rope 16 passes through the control rod 24. Therefore, when the control rod 24 slides back and forth, it can drive the pull rope 16 to move on the take-up roller 17, which can improve the winding effect of the pull rope 16, avoid the situation of pressing the wire, and improve the service life of the pull rope 16.

[0051] The terms "front," "back," "left," "right," "top," and "bottom" all refer to the figures in the accompanying drawings. Figure 1 Based on the perspective of the observer, the side of the device facing the observer is defined as the front, the left side of the observer is defined as the left, and so on.

[0052] In the description of this invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0053] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A geophysical exploration-specific rotary-wing UAV aeromagnetic total field detection system, characterized in that: The device includes a rotary-wing drone (1) and a probe (2). The bottom end of the rotary-wing drone (1) is fixedly installed with a mounting block (3). The probe (2) is slidably installed inside the mounting block (3). A control block (8) is slidably installed inside the mounting block (3). A moving block (28) is elastically installed inside the mounting block (3). The control block (8) and the moving block (28) are connected by a connecting rod (15). The clamping assembly is located inside the control block (8) and clamps the probe rod (2) by rotating the control block (8); A movable component is located inside the mounting block (3) to drive the control block (8) to slide inside the mounting block (3); The shifting component is located inside the mounting block (3) and is used to drive the control block (8) to rotate; The displacement assembly includes a first push rod (9), a second push rod (14), and a top pressure wedge (10). The first push rod (9) is fixedly installed at one end of the control block (8) away from the moving block (28). The first push rod (9) is symmetrically installed at the other end of the control block (8). The top pressure wedge (10) is located inside the mounting block (3) and close to the first push rod (9). There are two top pressure wedges (10), which are symmetrically located inside the mounting block (3).

2. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 1, characterized in that: The clamping assembly includes a first sliding groove (25), a first pressure ball (27) and a first pressure plate (26). The first sliding groove (25) is opened inside the control block (8), the first pressure plate (26) is fixedly installed inside the first sliding groove (25), and the first pressure ball (27) is slidably installed inside the first sliding groove (25).

3. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 2, characterized in that: The moving component includes a pull rope (16), a take-up roller (17), and a power component. One end of the pull rope (16) is fixedly connected to the side wall of the moving block (28), and the other end of the pull rope (16) is fixedly connected to the take-up roller (17). The take-up roller (17) is rotatably mounted inside the mounting block (3). The power component is located inside the mounting block (3) and is used to control the rotation of the take-up roller (17).

4. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 3, characterized in that: The power assembly includes a first bevel gear (18), a second bevel gear (20), a transmission roller (19), and a drive motor (29). The first bevel gear (18) is fixedly mounted on one end of the take-up roller (17). The transmission roller (19) is rotatably mounted inside the mounting block (3). The second bevel gear (20) is fixedly mounted on one end of the transmission roller (19) near the first bevel gear (18). The drive motor (29) is fixedly mounted on the bottom end of the transmission roller (19). The first bevel gear (18) meshes with the second bevel gear (20).

5. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 4, characterized in that: The mounting block (3) has a first groove (12) and a second groove (13) inside. The top of the control block (8) is elastically mounted with a guide rod (11), and the end of the guide rod (11) near the second groove (13) is inclined.

6. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 4, characterized in that: The mounting block (3) is rotatably mounted with a reciprocating threaded rod (23), and a control rod (24) is slidably mounted on the reciprocating threaded rod (23).

7. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 6, characterized in that: The take-up roller (17) has a first gear (21) fixedly installed at one end away from the first bevel gear (18), and a second gear (22) fixedly installed at one end of the reciprocating threaded rod (23). The first gear (21) meshes with the second gear (22).

8. The aeromagnetic total field detection system for a dedicated rotary-wing UAV for geophysical exploration according to claim 7, characterized in that: The bottom end of the rotary-wing UAV (1) is fixedly installed with a support block (4), and a second sliding groove (5) is opened inside the support block (4). A second top pressure plate (6) is fixedly installed inside the second sliding groove (5), and a second top pressure ball (7) is slidably installed inside the second sliding groove (5).

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