Rotor unmanned aerial vehicle carried cesium optical pump aeromagnetic system

Abstract

The utility model relates to the technical field of aeromagnetic equipment carrying, in particular to a caesium optical pump aeromagnetic system carried by a rotor wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle main body, a plurality of supports arranged on four sides of the unmanned aerial vehicle main body and rotor wings arranged on the supports, the bottom of the unmanned aerial vehicle main body is clamped with an aeromagnetic system main body, and the aeromagnetic system main body comprises an equipment box. A data processor is arranged in the equipment box, two groups of detection rods are arranged at the bottom of the equipment box, and the two groups of detection rods are connected with the data processor through connecting wires. Through innovative fixing and dismounting design, the combination efficiency of the aeromagnetic system body and the unmanned aerial vehicle body is improved, the auxiliary fixing assembly and the clamping assembly are ingeniously combined, the aeromagnetic system body can be rapidly and stably installed at the bottom of the unmanned aerial vehicle, meanwhile, after a detection task is completed, dismounting can be easily achieved, and the detection efficiency is improved. The time cost is saved, the flexibility of the aeromagnetic system carried by the unmanned aerial vehicle is improved, and rapid switching among different tasks is facilitated.

Description

Technical Field

[0001] The utility model relates to the technical field of aeromagnetic equipment mounting, in particular to a cesium optical pump aeromagnetic system mounted on a rotary-wing unmanned aerial vehicle. Background Art

[0002] Aeromagnetic systems, specifically those that use aviation technology to conduct magnetic exploration, work based on the interaction between the Earth's magnetic field and magnetic materials. When aircraft such as airplanes or drones fly over an area, their onboard magnetometers continuously record the strength and direction of the magnetic field. If magnetic materials are present underground, they can locally interfere with the Earth's magnetic field, causing abnormal magnetometer readings.

[0003] The installation and disassembly process of traditional aeromagnetic systems is cumbersome and time-consuming, and it is difficult to quickly switch between different tasks, which greatly limits the flexibility and efficiency of drone aeromagnetic detection. At the same time, during the detection process, both the pre-detection preparation work and the post-detection recovery work require manual participation, which not only increases the difficulty of operation, but also easily causes damage to the detection equipment during landing. Utility Model Content

[0004] The purpose of the present invention is to provide a cesium optical pump aeromagnetic system for a rotary-wing UAV to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] The rotor UAV is equipped with a cesium optical pump aeromagnetic system, which includes a UAV body, multiple brackets installed on the four sides of the UAV body, and rotors installed on the brackets. The bottom of the UAV body is clamped with an aeromagnetic system body, and the aeromagnetic system body includes an equipment box, which is provided with a data processor. The bottom of the equipment box is provided with two sets of detection rods, and the two sets of detection rods are connected to the data processor via connecting lines.

[0007] The bottom of the drone body is further provided with three sets of auxiliary fixing components for fixing the auxiliary equipment box, and both sides of the equipment box are further provided with snap-on components for fixing to the drone body.

[0008] Preferably: a connecting groove is provided at the bottom of the equipment box, a connecting box is slidably connected to the connecting groove, sliding grooves are provided on both sides of the connecting groove, sliders adapted to adjacent sliding grooves are installed on both sides of the connecting box, the two sliders are respectively slidably connected to the adjacent sliding grooves, and the two groups of detection rods are slidably connected to the connecting box.

[0009] Preferably: an electric push rod is also installed in the equipment box, the output end of the electric push rod passes through the connection box and extends into the connection box, the output end of the electric push rod is fixedly connected to a connecting plate, the connecting plate is slidably connected to the connection box, and the bottom of the connecting plate is fixed to the two detection rods.

[0010] Preferably: the auxiliary fixing assembly includes an L-shaped fixing plate, the L-shaped fixing plate is installed at the bottom of the drone body, the bottom of the L-shaped fixing plate is threadedly connected with a fixing bolt, the top of the fixing bolt is installed with an abutment plate, and the top of the abutment plate abuts against the bottom of the equipment box.

[0011] Preferably, adjustment slots are provided in the inner walls of both sides of the equipment box, and the two sets of the clamping components are respectively arranged in adjacent adjustment slots;

[0012] The card assembly includes a pressing block and a card block, the pressing block is slidably connected to the adjustment slot, the card block is slidably set on the top of the equipment box, the side of the pressing block close to the inside of the adjustment slot is fixed to the card block, and a return spring is also provided between the pressing block and the adjustment slot, the two ends of the return spring are respectively fixed to the pressing block and the adjustment slot, and two slots adapted to the card block are provided at the bottom of the drone body.

[0013] Preferably, a foot buffer assembly is provided on a side below each of the brackets close to the rotor, the foot buffer assembly comprising a foot body, the top of the foot body being fixed to the bracket, a buffer rod being slidably connected to the foot body, a buffer pad being installed at the bottom of the buffer rod, a shock absorbing spring being sleeved on the buffer rod, one end of the shock absorbing spring being fixed to the outer wall of the buffer rod, and the other end being fixed to the interior of the foot body;

[0014] A solar panel is also installed on the top of the drone body.

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

[0016] 1. The utility model significantly improves the efficiency of combining the main body of the aeromagnetic system with the main body of the UAV through innovative fixing and disassembly design. The ingenious combination of auxiliary fixing components and clamping components enables the main body of the aeromagnetic system to be quickly and firmly installed on the bottom of the UAV. At the same time, it can also be easily disassembled after completing the detection task. This fast installation and disassembly feature not only saves time and cost, but also improves the flexibility of the UAV equipped with the aeromagnetic system, making it convenient for rapid switching between different tasks.

[0017] 2. The utility model realizes automatic preparation before detection and automatic recovery after detection through the coordinated work of the electric push rod, connecting plate, detection rod and other components, effectively avoiding possible damage to the detection rod during the landing process and ensuring the long-term stable operation of the equipment.

[0018] 3. The utility model effectively absorbs the impact force during landing through the combined action of the buffer pad on the support leg buffer assembly, the buffer rod, the shock-absorbing spring and other components, reduces the impact of vibration on the drone and the aeromagnetic system, and extends the service life of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram from the first perspective of the present invention;

[0020] Figure 2 This is a partial structural diagram of the main body, auxiliary fixing assembly and clamping assembly of the aeromagnetic system of the present invention;

[0021] Figure 3 This is a schematic structural diagram of the main body of the aeromagnetic system in the present utility model;

[0022] Figure 4 It is a structural diagram of the equipment box in the utility model;

[0023] Figure 5 This is a structural diagram of the support leg buffer assembly of the utility model.

[0024] In the figure: 1. UAV body; 11. Bracket; 12. Rotor; 13. Solar panel; 2. Support leg buffer assembly; 21. Support leg body; 22. Buffer rod; 23. Buffer pad; 24. Shock-absorbing spring; 3. Aeromagnetic system body; 31. Equipment box; 32. Connecting slot; 33. Connecting box; 34. Slide slot; 35. Slider; 36. Electric push rod; 37. Connecting plate; 38. Detection rod; 39. Adjustment slot; 4. Auxiliary fixing assembly; 41. L-shaped fixing plate; 42. Fixing bolt; 43. Abutment plate; 5. Clamping assembly; 51. Pressing block; 52. Clamping block; 53. Reset spring. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] For example 1, please refer to Figure 1-5The rotor UAV is equipped with a cesium optical pump aeromagnetic system, including a UAV body 1, a plurality of brackets 11 installed on the four sides of the UAV body 1 and a rotor 12 installed on the bracket 11. The bottom of the UAV body 1 is connected with an aeromagnetic system body 3, and the aeromagnetic system body 3 includes an equipment box 31. The equipment box 31 is provided with a data processor. The bottom of the equipment box 31 is provided with two groups of detection rods 38. The two groups of detection rods 38 are connected to the data processor through a connecting line. The bottom of the UAV body 1 is also provided with three groups of auxiliary fixing components 4 for fixing the auxiliary equipment box 31. The two sides of the equipment box 31 are also provided with There is a clamping assembly 5 for fixing to the drone body 1. A foot buffer assembly 2 is provided on one side of each bracket 11 near the rotor 12. The foot buffer assembly 2 includes a foot body 21. The top of the foot body 21 is fixed to the bracket 11. A buffer rod 22 is slidably connected to the foot body 21. A buffer pad 23 is installed at the bottom of the buffer rod 22. A shock-absorbing spring 24 is also sleeved on the buffer rod 22. One end of the shock-absorbing spring 24 is fixed to the outer wall of the buffer rod 22, and the other end is fixed to the inside of the foot body 21. A solar panel 13 is also installed on the top of the drone body 1.

[0027] When in use, first install the equipment box 31 on the bottom of the drone body 1 through the auxiliary fixing component 4 and the clamping component 5 to fix the aeromagnetic system body 3. After fixing, start the drone body 1, drive the aeromagnetic system body 3 to rise, and at the same time start the detection rod 38 in the equipment box 31 to perform detection;

[0028] When the detection is completed, the drone body 1 is controlled to descend. When the drone body 1 is about to touch the ground, the aeromagnetic system body 3 is controlled to retract the detection rod 38 to prevent the detection rod 38 from impacting the ground and causing damage. At the same time, the multiple leg buffer assemblies 2 on the bracket 11 touch the ground.

[0029] When the drone body 1 lands, the buffer pad 23 on the support leg buffer assembly 2 first contacts the ground, and the buffer pad 23 cushions the impact force during landing. At the same time, the buffer pad 23 pushes the buffer rod 22 to move slightly toward the support leg body 21, and the shock-absorbing spring 24 absorbs and dampens the impact force again, reducing the vibration during landing.

[0030] For example 2, please refer to Figure 1-5, a connecting groove 32 is provided at the bottom of the equipment box 31, and a connecting box 33 is slidably connected to the connecting groove 32. Slide grooves 34 are provided on both sides of the connecting groove 32, and sliders 35 adapted to adjacent slide grooves 34 are installed on both sides of the connecting box 33. The two sliders 35 are slidably connected to the adjacent slide grooves 34 respectively. The two sets of detection rods 38 are slidably connected to the connecting box 33. An electric push rod 36 is also installed in the equipment box 31. The output end of the electric push rod 36 passes through the connecting box 33 and extends into the connecting box 33. The output end of the electric push rod 36 is fixedly connected to a connecting plate 37. The connecting plate 37 is slidably connected to the connecting box 33, and the bottom of the connecting plate 37 is fixed to the two detection rods 38;

[0031] During the inspection, after the drone body 1 is lifted off, the electric push rod 36 in the equipment box 31 is started, so that the electric push rod 36 drives the connecting plate 37 to move downward. When the connecting plate 37 moves downward, the two detection rods 38 are first pushed to extend from the connecting box 33, so that the two detection rods 38 are moved out. When the connecting plate 37 moves downward to the bottom end in the connecting box 33, the detection rods 38 are fixed in the connecting box 33. At this time, the electric push rod 36 continues to move, and the connecting box 33 slides along the slide grooves 34 on both sides through the two sliders 35 under the push of the electric push rod 36, so that the connecting box 33 extends downward from the connecting groove 32, completing the preparation work before the inspection, starting the two detection rods 38 for inspection, and transmitting the detected data to the data processor for processing through the connecting line;

[0032] When the inspection work is completed and the vehicle is about to land, the electric push rod 36 is controlled to drive the connecting plate 37 to move upward, so that the two inspection rods 38 slide toward the connection box 33. When the connecting plate 37 slides to the top of the connection box 33, the electric push rod 36 drives the connection box 33 to slide toward the connection groove 32 through the connecting plate 37, so that the connection box 33 and the inspection rod 38 are completely retracted, avoiding the inspection rod 38 from hitting the ground and causing damage during landing.

[0033] For example three, please refer to Figure 1-4The auxiliary fixing assembly 4 includes an L-shaped fixing plate 41, which is installed at the bottom of the drone body 1. The bottom of the L-shaped fixing plate 41 is threadedly connected with a fixing bolt 42, and the top of the fixing bolt 42 is installed with an abutment plate 43. The top of the abutment plate 43 abuts against the bottom of the equipment box 31. Adjustment slots 39 are also provided in the inner walls of both sides of the equipment box 31. Two groups of clamping assemblies 5 are respectively arranged in adjacent adjusting slots 39. The clamping assembly 5 includes a pressing block 51 and a clamping block 52. The pressing block 51 is slidably connected to the adjusting slot 39, and the clamping block 52 is slidably arranged at the top of the equipment box 31. The side of the pressing block 51 close to the inside of the adjusting slot 39 is fixed to the clamping block 52. A return spring 53 is further provided between the pressing block 51 and the adjusting slot 39. The two ends of the return spring 53 are respectively fixed to the pressing block 51 and the adjusting slot 39. The bottom of the drone body 1 is provided with two slots adapted to the clamping block 52.

[0034] When installing the equipment box 31, first insert the equipment box 31 horizontally onto the multiple sets of auxiliary fixing components 4 through the side of the bottom of the drone body 1 where the auxiliary fixing components 4 are not provided, so that the equipment box 31 is located above the multiple abutment plates 43, and at the same time push the two pressing blocks 51 inward, so that the two pressing blocks 51 drive the two clamping blocks 52 to move toward each other in the adjustment slots 39, and move the equipment box 31 so that the top of the equipment box 31 is completely in contact with the bottom of the drone body 1, release the pressing block 51, and under the action of the rebound force of the return spring 53, drive the pressing block 51 and the clamping block 52 to pop outward, so that the clamping block 52 is clamped in the slot provided on the drone body 1, so that the aeromagnetic system body 3 is initially fixed;

[0035] After being fixed, the multiple fixing bolts 42 are rotated in sequence, so that the multiple fixing bolts 42 drive the abutment plate 43 to move upward, gradually abutting against the bottom of the equipment box 31, and the aeromagnetic system body 3 is completely fixed to the drone body 1 through the multiple auxiliary fixing components 4;

[0036] By providing the auxiliary fixing assembly 4 and the clamping assembly 5, the aeromagnetic system body 3 can be quickly fixed to the drone body 1 during use. At the same time, after use, the aeromagnetic system body 3 can be quickly disassembled for easy use.

[0037] Working principle: When in use, first install the aeromagnetic system body 3 on the bottom of the drone body 1. When installing the equipment box 31, first insert the equipment box 31 into the multiple sets of auxiliary fixing components 4, and at the same time push the two pressing blocks 51 inward, so that the two pressing blocks 51 drive the two clamping blocks 52 to move toward each other in the adjustment slot 39. Move the equipment box 31 so that the top of the equipment box 31 is in full contact with the bottom of the drone body 1. Release the pressing block 51. Under the action of the rebound force of the return spring 53, the pressing block 51 and the clamping block 52 pop outward, so that the clamping block 52 is engaged in the slot provided on the drone body 1, so that the aeromagnetic system body 3 is initially fixed.

[0038] After being fixed, the multiple fixing bolts 42 are rotated in sequence, so that the multiple fixing bolts 42 drive the abutment plate 43 to move upward, gradually abutting against the bottom of the equipment box 31, and the aeromagnetic system body 3 is completely fixed to the drone body 1 through the multiple auxiliary fixing components 4;

[0039] By providing the auxiliary fixing assembly 4 and the clamping assembly 5, the aeromagnetic system body 3 can be quickly fixed to the drone body 1 during use. At the same time, after use, the aeromagnetic system body 3 can be quickly disassembled for easy use.

[0040] Start the drone body 1, drive the aeromagnetic system body 3 to rise, start the electric push rod 36 so that the electric push rod 36 drives the connecting plate 37 to move downward, when the connecting plate 37 moves downward, pushes the two detection rods 38 to extend from the connecting box 33, when the connecting plate 37 moves downward to the bottom end of the connecting box 33, the detection rods 38 are fixed in the connecting box 33, at this time the electric push rod 36 continues to move, and the connecting box 33 slides along the slide grooves 34 on both sides under the push of the electric push rod 36, so that the connecting box 33 extends downward from the connecting groove 32, completing the preparation work before the test, start the two detection rods 38 for detection, and transmit the detected data to the data processor for processing through the connecting line;

[0041] When the inspection work is completed and the drone is about to land, the electric push rod 36 is controlled to drive the connecting plate 37 and the detection rod 38 to move upward. The electric push rod 36 drives the connecting box 33 to slide toward the connecting groove 32 through the connecting plate 37, so that the connecting box 33 and the detection rod 38 are completely retracted to avoid the detection rod 38 hitting the ground and causing damage during landing. When the drone body 1 lands, the buffer pad 23 on the support leg buffer assembly 2 first contacts the ground, and the buffer pad 23 cushions the impact force during landing. At the same time, the buffer pad 23 pushes the buffer rod 22 to move slightly toward the support leg body 21, and the shock-absorbing spring 24 absorbs and dampens the impact force again to reduce vibration during landing.

[0042] It should be noted that the various devices in this application are common devices in the market, and can be selected according to specific needs during specific use. The circuit connection relationship of each device is a simple series and parallel connection circuit. There is no innovation in the circuit connection part. Those skilled in the art can implement it relatively easily. It belongs to the existing technology and will not be elaborated on.

[0043] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A rotary-wing UAV equipped with a cesium optical pump aeromagnetic system, comprising a UAV body (1), a plurality of brackets (11) mounted on four sides of the UAV body (1), and a rotor (12) mounted on the brackets (11), characterized in that: The bottom of the drone body (1) is connected to an aeromagnetic system body (3), the aeromagnetic system body (3) includes an equipment box (31), a data processor is provided in the equipment box (31), and two groups of detection rods (38) are provided at the bottom of the equipment box (31), and the two groups of detection rods (38) are connected to the data processor via a connecting line; The bottom of the drone body (1) is also provided with three sets of auxiliary fixing components (4) for fixing the auxiliary equipment boxes (31), and both sides of the equipment boxes (31) are also provided with snap-on components (5) for fixing to the drone body (1).

2. The cesium optical pump aeromagnetic system for a rotary-wing UAV according to claim 1, characterized in that: The bottom of the equipment box (31) is provided with a connecting groove (32), a connecting box (33) is slidably connected in the connecting groove (32), sliding grooves (34) are provided on both sides of the connecting groove (32), and sliders (35) adapted to adjacent sliding grooves (34) are installed on both sides of the connecting box (33), and the two sliders (35) are respectively slidably connected to the adjacent sliding grooves (34), and the two groups of detection rods (38) are both slidably connected to the connecting box (33).

3. The cesium optical pump aeromagnetic system for a rotary-wing UAV according to claim 1, characterized in that: An electric push rod (36) is also installed in the equipment box (31), and the output end of the electric push rod (36) passes through the connection box (33) and extends into the connection box (33). The output end of the electric push rod (36) is fixedly connected to a connecting plate (37), and the connecting plate (37) is slidably connected to the connection box (33), and the bottom of the connecting plate (37) is fixed to two detection rods (38).

4. The cesium optical pump aeromagnetic system for a rotary-wing UAV according to claim 1, characterized in that: The auxiliary fixing assembly (4) includes an L-shaped fixing plate (41), the L-shaped fixing plate (41) is installed on the bottom of the drone body (1), the bottom of the L-shaped fixing plate (41) is threadedly connected with a fixing bolt (42), the top of the fixing bolt (42) is installed with an abutment plate (43), and the top of the abutment plate (43) abuts against the bottom of the equipment box (31).

5. The cesium optical pump aeromagnetic system for a rotary-wing UAV according to claim 1, characterized in that: Adjustment slots (39) are also provided in the inner walls of both sides of the equipment box (31), and the two groups of the clamping components (5) are respectively arranged in adjacent adjustment slots (39); The clamping assembly (5) includes a pressing block (51) and a clamping block (52), wherein the pressing block (51) is slidably connected to the adjusting groove (39), and the clamping block (52) is slidably arranged on the top of the equipment box (31). The pressing block (51) is fixed to the clamping block (52) on one side close to the inside of the adjusting groove (39). A return spring (53) is further arranged between the pressing block (51) and the adjusting groove (39), and the two ends of the return spring (53) are respectively fixed to the pressing block (51) and the adjusting groove (39). Two slots adapted to the clamping block (52) are provided at the bottom of the drone body (1).

6. The cesium optical pump aeromagnetic system for a rotary-wing UAV according to claim 1, characterized in that: A foot buffer assembly (2) is provided on one side of each bracket (11) close to the rotor (12), and the foot buffer assembly (2) includes a foot body (21), the top of the foot body (21) is fixed to the bracket (11), a buffer rod (22) is slidably connected in the foot body (21), a buffer pad (23) is installed at the bottom of the buffer rod (22), and a shock-absorbing spring (24) is sleeved on the buffer rod (22), one end of the shock-absorbing spring (24) is fixed to the outer wall of the buffer rod (22), and the other end is fixed to the inside of the foot body (21); A solar panel (13) is also installed on the top of the drone body (1).

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