Rotor unmanned aerial vehicle

Abstract

The invention belongs to the technical field of aviation equipment, and particularly relates to a rotor unmanned aerial vehicle which comprises an unmanned aerial vehicle body and further comprises a gravity center adjusting mechanism, a loading connecting mechanism, a weighing feedback mechanism, a gravity center height control driving mechanism, a wind power monitoring mechanism and a PLC. The height of the gravity center of the whole rotor unmanned aerial vehicle can be quickly adjusted according to use requirements, so that the stable flight requirement of the unmanned aerial vehicle is better met, and the problem that the flight stability is affected due to the fact that the gravity center of the unmanned aerial vehicle is relatively high and the unmanned aerial vehicle is prone to inclination and shaking when encountering wind due to the multi-rotor layout is solved; the gravity center height of the whole unmanned aerial vehicle can be automatically and accurately regulated and controlled based on the magnitude of the environmental wind force borne by the unmanned aerial vehicle during flight, and the gravity center height of the unmanned aerial vehicle is reduced when the wind force is large, so that the unmanned aerial vehicle keeps a more stable posture in strong wind.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation equipment, and in particular relates to a rotary-wing unmanned aerial vehicle. Background Art

[0002] A rotorcraft drone is an unmanned aerial vehicle with multiple rotors. The multi-rotor structure gives the drone good stability and maneuverability, allowing it to take off and land and hover in a smaller space.

[0003] Due to the structural characteristics of the multi-rotor rotor of the rotary-wing UAV, it is highly sensitive to wind. Flying in a strong wind environment can easily affect flight stability or even cause loss of control. The multi-rotor layout makes the center of gravity of the UAV relatively high, which is prone to tilt and shake when encountering wind, thus affecting flight stability. The power of the rotary-wing UAV mainly comes from the rotors driven by multiple motors. When encountering strong winds, the force of the wind on the rotors will interfere with the output power and speed of the motor, causing the lift and attitude control of the UAV to be affected. Summary of the invention

[0004] The purpose of the present invention is to provide a rotary-wing UAV in view of the above problems.

[0005] To achieve the above object, the present invention adopts the following technical solution: a rotary wing UAV, including a UAV body, and also including: A center of gravity adjustment mechanism is fixedly mounted at the bottom end of the drone body; A loading connection mechanism, fixedly mounted on the moving end of the center of gravity adjustment mechanism; A weighing feedback mechanism is arranged between the moving end of the center of gravity adjustment mechanism and the upper end of the loading connection mechanism; A center of gravity height control driving mechanism is fixedly mounted at the lower end of the drone body and is electrically connected to the center of gravity adjustment mechanism; A wind force monitoring mechanism is fixedly mounted on the upper end of the drone body and is electrically connected to the center of gravity height control driving mechanism; The PLC controller is fixedly mounted at the lower end of the UAV body and is electrically connected to the center of gravity adjustment mechanism, the loading connection mechanism, the weighing feedback mechanism, the center of gravity height control drive mechanism and the wind force monitoring mechanism.

[0006] In the above-mentioned rotor UAV, the center of gravity adjustment mechanism includes a fixed shell fixedly installed at the lower end of the UAV body, and two adjusting screws are symmetrically rotatably connected to the bottom of the inner wall of the fixed shell and the lower end of the UAV body. The bottom end of the UAV body is set as a hollow structure, and the upper end of the adjusting screw penetrates and extends into the bottom end of the UAV body. A dual-axis motor is fixedly installed on the inner side of the bottom end of the UAV body, and the output ends of the dual-axis motor are both connected to the upper end of the adjusting screw through a bevel gear assembly. The rod wall threads of the two adjusting screws are threadedly sleeved with the same lifting plate.

[0007] In the above-mentioned rotor UAV, the loading connection mechanism includes a plurality of support slide bars symmetrically fixedly arranged at the lower end of the lifting plate, a plurality of the support slide bars are slidably sleeved with the same U-shaped connecting plate, the lower end of the U-shaped connecting plate is fixedly connected to the loading plate, the lower end of the fixed shell is provided with a rectangular opening for the lower end of the U-shaped connecting plate to extend through, the surface of the U-shaped connecting plate is provided with a plurality of sleeve holes slidably sleeved with the support slide bars, and the inner walls of the corresponding sleeve holes are embedded with positioning electromagnetic blocks, the rod wall of the support slide bar is embedded with a positioning permanent magnetic strip in contact with the positioning electromagnetic block, and the upper end of the U-shaped connecting plate and the lower end of the lifting plate are fixedly provided with a plurality of pulling springs sleeved outside the support slide bar.

[0008] In the above-mentioned rotor UAV, the weighing feedback mechanism includes a transmission rack fixedly installed at the lower end of the lifting plate, the lower end of the transmission rack passes through the upper end of the U-shaped connecting plate, and the lower end of the horizontal part of the U-shaped connecting plate is also fixedly installed with a feedback shell, the inner wall of the feedback shell is rotatably connected with a transmission screw, one end of the transmission screw passes through and extends out of the feedback shell, and is fixedly connected with a transmission gear meshing with the transmission rack, the rod wall of the transmission screw is threadedly sleeved with a transmission seat, and the inner wall of the feedback shell is fixedly installed with a gear parallel to the transmission screw A feedback resistor rod is set, and the side wall of the transmission seat is provided with a through hole which is sleeved outside the feedback resistor rod, and the inner wall corresponding to the through hole is fixedly provided with a feedback conductive contact which is electrically in contact with the feedback resistor rod, a prompt switch is fixedly provided at the lower end of the transmission seat, a rotating screw is rotatably connected to the lower side of the inner wall of the feedback shell, a rotating motor for driving the rotating screw to rotate is fixedly provided on the outer wall of the feedback shell, a moving block is threadedly sleeved on the rod wall of the rotating screw, and a pressing round head corresponding to the position of the prompt switch is fixedly provided on the upper end of the moving block.

[0009] In the above-mentioned rotor UAV, the center of gravity height control drive mechanism includes a control shell, the inner wall of the control shell is fixedly installed with a plurality of guide slide bars arranged side by side, the plurality of guide slide bars are slidably sleeved with the same trigger plate, the upper and lower ends of the trigger plate are both set as arc head structures, the trigger plate and the control shell are fixedly installed with a plurality of compensation springs sleeved outside the guide slide bars, the side wall of the trigger plate is fixedly installed with a thrust permanent magnet plate, the inner wall of the control shell is fixedly installed with a thrust electromagnetic plate arranged opposite to the thrust permanent magnet plate, the upper side of the inner wall of the control shell is rotatably connected with a driving screw, the outer wall of the control shell is fixedly installed with a driving motor for driving the driving screw to rotate, the rod wall of the driving screw is threadedly sleeved with a driving block, the lower end of the driving block is fixedly connected with a U-shaped mounting plate, and the upper and lower ends of the inner wall of the U-shaped mounting plate are respectively fixedly installed with a lifting control switch and a lowering control switch.

[0010] In the above-mentioned rotor UAV, the wind force monitoring mechanism includes a monitoring shell fixedly mounted on the upper end of the UAV body, the upper end of the monitoring shell is rotatably sleeved with a forced wind wheel, a generator is fixedly mounted inside the monitoring shell, and the rotating end of the forced wind wheel is fixedly connected to the input end of the generator.

[0011] In the above-mentioned rotary wing UAV, a plurality of limit sliding blocks are symmetrically fixedly mounted on the outer wall of the lifting plate, and a limit sliding groove matching and slidingly connected with the limit sliding blocks is opened on the inner side of the fixed shell.

[0012] In the above-mentioned rotary wing UAV, the lower end of the supporting slide bar is fixedly connected with an anti-slip plate, and the lower end of the horizontal portion of the U-shaped connecting plate is fixedly provided with an alarm switch arranged corresponding to the position of the anti-slip plate.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. Through the setting of the drone body, loading connection mechanism, and center of gravity adjustment mechanism, the function of drone cargo loading can be realized, and the center of gravity height of the entire rotor drone can be quickly adjusted according to the use requirements, thereby better meeting the stable flight requirements of the drone and avoiding the problem that the multi-rotor layout makes the center of gravity of the drone relatively high, which is easy to tilt and shake when encountering wind, thereby affecting the flight stability.

[0014] 2. By setting up the loading connection mechanism, weighing feedback mechanism, center of gravity height control drive mechanism, and wind force monitoring mechanism, the weight of the cargo can be automatically calculated and fed back when the rotor UAV is loaded with cargo, and the center of gravity height of the entire UAV can be automatically and accurately adjusted based on the size of the environmental wind force to which the UAV is subjected during flight. When the wind force is strong, the center of gravity height of the UAV can be lowered, so that the UAV can maintain a more stable posture in strong winds, and the sensitivity of the UAV to wind is reduced, and the torque of the wind on the UAV is reduced, so that when the UAV is disturbed by strong winds, it is less likely to be blown off the predetermined route or lose balance by the wind, and the problem of poor steering and flexibility of the UAV in flight and excessive restriction of the maneuverability of the UAV can be avoided due to the too low center of gravity.

[0015] 3. Through the weighing feedback mechanism, the drone's endurance can be further calculated and fed back based on the weight of the cargo loaded on the drone. The drone's flight mission can be reasonably planned according to the weight of the cargo to avoid dangerous situations caused by insufficient power during flight. The operator can be reminded in time to make corresponding arrangements to ensure the quality of the implementation of the flight mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a three-dimensional structural schematic diagram of the present invention; Figure 2 It is a front view cross-sectional structural schematic diagram of the present invention; Figure 3 yes Figure 2 The middle part is an enlarged structural diagram; Figure 4 It is a cross-sectional structural schematic diagram of the center of gravity adjustment mechanism of the present invention; Figure 5 It is a structural schematic diagram of the loading connection mechanism of the present invention; Figure 6 yes Figure 5 A magnified view of part A; Figure 7 It is a schematic cross-sectional structural diagram of the weighing feedback mechanism of the present invention; Figure 8 yes Figure 7 A magnified view of part B; Fig. 9 It is a side cross-sectional structural schematic diagram of the center of gravity height control driving mechanism of the present invention; Fig.10 yes Fig. 9 A schematic diagram of the three-dimensional structure of the installation of the middle U-shaped mounting plate and the lifting control switch and the lowering control switch; Fig.11 It is a schematic cross-sectional view of the wind force monitoring mechanism of the present invention.

[0017] In the figure: 1 drone body, 2 center of gravity adjustment mechanism, 21 fixed shell, 22 adjustment screw, 23 dual-axis motor, 24 bevel gear assembly, 25 lifting plate, 3 loading connection mechanism, 31 support slide bar, 32 U-shaped connection plate, 33 loading plate, 34 positioning electromagnetic block, 35 positioning permanent magnetic strip, 36 pulling spring, 37 anti-drop plate, 38 alarm switch, 4 weighing feedback mechanism, 41 transmission rack, 42 ​​feedback shell, 43 transmission screw, 44 transmission gear, 45 transmission seat, 46 feedback resistor rod, 47 feedback conductive contact piece, 4 8 prompt switch, 49 rotating screw, 410 rotating motor, 411 moving block, 412 pressing round head, 5 center of gravity height control driving mechanism, 51 control shell, 52 guide slide bar, 53 trigger plate, 54 compensation spring, 55 thrust permanent magnet plate, 56 thrust electromagnetic plate, 57 driving screw, 58 driving motor, 59 driving block, 510 U-shaped mounting plate, 511 lifting control switch, 512 lowering control switch, 6 wind force monitoring mechanism, 61 monitoring shell, 62 force wind wheel, 63 generator, 7 PLC controller. DETAILED DESCRIPTION

[0018] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0019] like Figure 1-Figure 11 As shown, a rotary wing UAV includes a UAV body 1 and further includes: The center of gravity adjustment mechanism 2 is fixedly installed at the bottom end of the drone body 1. The center of gravity adjustment mechanism 2 includes a fixed shell 21 fixedly installed at the lower end of the drone body 1. The bottom of the inner wall of the fixed shell 21 and the lower end of the drone body 1 are symmetrically rotatably connected with two adjusting screws 22. The bottom end of the drone body 1 is set as a hollow structure. The upper end of the adjusting screw 22 penetrates and extends into the bottom end of the drone body 1. A dual-axis motor 23 is fixedly installed on the inner side of the bottom end of the drone body 1. The output ends of both ends of the dual-axis motor 23 are transmission-connected with the upper end of the adjusting screw 22 through a bevel gear assembly 24. The rod walls of the two adjusting screws 22 are threadedly sleeved with the same lifting plate 25. The outer wall of the lifting plate 25 is symmetrically fixedly installed with a plurality of limit sliders. The inner side of the fixed shell 21 is provided with a limit slide groove that matches and slides with the limit slider. The center of gravity height of the entire rotor drone can be quickly adjusted according to the use requirements, thereby better meeting the stable flight requirements of the drone.

[0020] The loading connection mechanism 3 is fixedly mounted on the moving end of the center of gravity adjustment mechanism 2. The loading connection mechanism 3 includes a plurality of support slide bars 31 symmetrically fixedly mounted on the lower end of the lifting plate 25. The plurality of support slide bars 31 are slidably sleeved with the same U-shaped connection plate 32. The lower end of the U-shaped connection plate 32 is fixedly connected with a loading plate 33. The lower end of the fixed shell 21 is provided with a rectangular opening for the lower end of the U-shaped connection plate 32 to extend through. The surface of the U-shaped connection plate 32 is provided with a plurality of sleeve holes slidably sleeved with the support slide bars 31. A positioning electromagnetic block 34 is embedded in the inner wall of the corresponding sleeve hole, a positioning permanent magnetic strip 35 in contact with the positioning electromagnetic block 34 is embedded in the rod wall of the supporting slide bar 31, a plurality of pulling springs 36 sleeved on the outside of the supporting slide bar 31 are fixedly installed on the upper end of the U-shaped connecting plate 32 and the lower end of the lifting plate 25, an anti-slip plate 37 is fixedly connected to the lower end of the supporting slide bar 31, and an alarm switch 38 corresponding to the position of the anti-slip plate 37 is fixedly installed on the lower end of the horizontal part of the U-shaped connecting plate 32, which can realize the function of drone cargo loading.

[0021] The weighing feedback mechanism 4 is arranged between the moving end of the center of gravity adjustment mechanism 2 and the upper end of the loading connection mechanism 3. The weighing feedback mechanism 4 includes a transmission rack 41 fixedly arranged at the lower end of the lifting plate 25. The lower end of the transmission rack 41 passes through the upper end of the U-shaped connecting plate 32. The lower end of the horizontal part of the U-shaped connecting plate 32 is also fixedly arranged with a feedback shell 42. The inner wall of the feedback shell 42 is rotatably connected with a transmission screw 43. One end of the transmission screw 43 passes through and extends out of the feedback shell 42, and is fixedly connected with a transmission gear 44 meshing with the transmission rack 41. The rod wall of the transmission screw 43 is threadedly sleeved with a transmission seat 45. The inner wall of the feedback shell 42 is fixedly provided with a transmission screw 43 arranged parallel to the transmission screw 43. Feedback resistor rod 46, the side wall of the transmission seat 45 is provided with a through hole which is sleeved outside the feedback resistor rod 46, and the inner wall of the corresponding through hole is fixedly provided with a feedback conductive contact 47 which is in electrical contact with the feedback resistor rod 46, and a prompt switch 48 is fixedly provided at the lower end of the transmission seat 45, and a rotating screw 49 is rotatably connected to the lower side of the inner wall of the feedback shell 42, and a rotating motor 410 for driving the rotating screw 49 to rotate is fixedly provided on the outer wall of the feedback shell 42, and a moving block 411 is threadedly sleeved on the rod wall of the rotating screw 49, and a pressing round head 412 which is arranged corresponding to the position of the prompt switch 48 is fixedly provided on the upper end of the moving block 411, so as to quickly detect and feedback the weight of the carried goods.

[0022] The center of gravity height control driving mechanism 5 is fixedly installed at the lower end of the drone body 1 and is electrically connected to the center of gravity adjustment mechanism 2. The center of gravity height control driving mechanism 5 includes a control shell 51. A plurality of guide slide bars 52 arranged side by side are fixedly installed on the inner wall of the control shell 51. The plurality of guide slide bars 52 are slidably sleeved with the same trigger plate 53 outside. The upper and lower ends of the trigger plate 53 are both set as arc head structures. A plurality of compensation springs 54 sleeved outside the guide slide bars 52 are fixedly installed on the opposite side of the trigger plate 53 and the control shell 51. A thrust permanent magnet plate 55 is fixedly installed on the side wall of the trigger plate 53. A thrust permanent magnet plate 55 arranged opposite to the thrust permanent magnet plate 55 is fixedly installed on the inner wall of the control shell 51. The driving screw 57 is rotatably connected to the upper side of the inner wall of the control shell 51, and a driving motor 58 for driving the driving screw 57 to rotate is fixedly installed on the outer wall of the control shell 51. A driving block 59 is threadedly sleeved on the rod wall of the driving screw 57, and a U-shaped mounting plate 510 is fixedly connected to the lower end of the driving block 59. A lifting control switch 511 and a lowering control switch 512 are fixedly installed on the upper and lower ends of the inner wall of the U-shaped mounting plate 510, respectively. The center of gravity height of the entire UAV can be automatically and accurately adjusted based on the size of the environmental wind force to which the UAV is subjected during flight, and the center of gravity height of the UAV can be lowered when the wind is strong, so that the UAV can maintain a more stable posture in strong winds.

[0023] The wind force monitoring mechanism 6 is fixedly mounted on the upper end of the UAV body 1 and is electrically connected to the center of gravity height control driving mechanism 5. The wind force monitoring mechanism 6 includes a monitoring shell 61 fixedly mounted on the upper end of the UAV body 1. A force-bearing wind wheel 62 is rotatably sleeved on the upper end of the monitoring shell 61. A generator 63 is fixedly mounted inside the monitoring shell 61. The rotating end of the force-bearing wind wheel 62 is fixedly connected to the input end of the generator 63, so as to quickly detect the environmental wind force.

[0024] The PLC controller 7 is fixedly mounted at the lower end of the drone body 1 and is electrically connected to the center of gravity adjustment mechanism 2, the loading connection mechanism 3, the weighing feedback mechanism 4, the center of gravity height control drive mechanism 5 and the wind force monitoring mechanism 6 respectively.

[0025] The operating principle of the present invention is described as follows: the cargo to be transported is fixed to the lower end of the loading plate 33 through a connecting piece, and the drone body 1 is supported first. Under the action of gravity, the cargo drives the loading plate 33 and the U-shaped connecting plate 32 to move downward relative to the lifting plate 25 along the supporting slide bar 31 to overcome the elastic force of the pulling spring 36. Specifically, the greater the weight of the cargo, the greater the distance the U-shaped connecting plate 32 moves relative to the lifting plate 25. After the cargo is stable, the PLC controller 7 controls the power supply device to supply power to the positioning electromagnetic block 34, and the positioning electromagnetic block 34 is energized to generate a force opposite to the positioning permanent magnetic strip 35. Magnetism makes the U-shaped connecting plate 32 and the supporting slide bar 31 stably connected together, thereby realizing the fixed installation of the cargo and the drone body 1. It is additionally explained that when the weight of the carried cargo is greater than the carrying weight of the drone body 1, the distance moved by the U-shaped connecting plate 32 relative to the lifting plate 25 reaches a preset threshold. At this time, the anti-slip plate 37 at the lower end of the supporting slide bar 31 will press on the alarm switch 38, thereby prompting the operator to adjust the loading amount of the cargo, thereby avoiding the problem that the drone body 1 cannot complete the complete flight mission due to overweight cargo; When the U-shaped connecting plate 32 moves relative to the lifting plate 25, the transmission gear 44 and the transmission rack 41 move relative to each other, so that the transmission gear 44 drives the transmission screw 43 to rotate, and the transmission seat 45 drives the feedback conductive contact piece 47 to slide on the feedback resistor rod 46 through the threaded sleeve effect of the transmission screw 43 and the transmission seat 45, and the distance between the prompt switch 48 at the lower end of the transmission seat 45 and the pressing round head 412 becomes shorter. Specifically, the greater the weight of the carried goods, the greater the moving distance of the transmission seat 45, so that the access resistance value of the feedback resistor rod 46 is greater and the distance between the prompt switch 48 and the pressing round head 412 is shorter. During the UAV's flight mission, the PLC controller 7 controls the rotating motor 410 to drive the rotating screw 49 to rotate synchronously, and the moving block 411 drives the pressing round head 412 to move through the threaded sleeve effect of the rotating screw 49 and the moving block 411, until the pressing round head 412 acts on the prompt switch 48, indicating that the current power consumption of the UAV body 1 has reached 60%, and then the PLC controller 7 sends a wireless signal to the operator's receiving terminal to remind the operator to take corresponding measures to avoid dangerous situations caused by the exhaustion of power consumption of the UAV body 1. The heavier the cargo carried by the UAV body 1, the shorter the interval between the prompt switch 48 and the pressing round head 412, so that the pressing round head 412 can act on the prompt switch 48 faster. When the drone body 1 is performing a flight mission, the wind in the environment will drive the forced wind wheel 62 to rotate, and then drive the input end of the generator 63 to rotate, so that the generator 63 generates electricity. Specifically, the greater the environmental wind force, the greater the power generation of the generator 63. The generator 63 supplies power to the thrust electromagnetic plate 56, and the thrust electromagnetic plate 56 is energized to generate the same magnetism as the thrust permanent magnet plate 55, thereby driving the trigger plate 53 to slide along the guide slide rod 52 to overcome the elastic force of the compensation spring 54. The greater the environmental wind force, the greater the thrust electromagnetic plate 56. The greater the power supply current, the greater the sliding distance of the trigger plate 53. When the lower end of the trigger plate 53 presses on the lower descent control switch 512, the PLC controller 7 synchronously controls the dual-axis motor 23 and the drive motor 58 to work in the forward direction for 5 seconds. The dual-axis motor 23 drives the two adjusting screws 22 to rotate synchronously in the forward direction through the bevel gear assembly 24, and then drives the carried goods to move downward through the threaded sleeve effect of the adjusting screw 22 and the lifting plate 25, thereby reducing the center of gravity height of the entire drone body 1, thereby avoiding strong winds. The problem of affecting the flight stability of the UAV body 1 is that the driving motor 58 drives the driving screw 57 to rotate. Through the threaded sleeve effect of the driving screw 57 and the driving block 59, the driving block 59 drives the U-shaped mounting plate 510 to move forward, and the lifting control switch 511 and the lowering control switch 512 are moved to the two sides of the trigger plate 53 again. When the environmental wind force decreases, the power supply current of the thrust electromagnetic plate 56 is reduced. Under the action of the compensation spring 54, the trigger plate 53 moves back, and the upper end of the trigger plate 53 presses on the lifting control switch 511. At this time, the PLC controller 7 controls the dual-axis motor 23 and the driving motor 58 to work in reverse for 5s. The dual-axis motor 23 drives the adjusting screw 22 to reverse, so that the loaded cargo moves up, and the center of gravity height of the entire rotor UAV is increased, so as to avoid the problem that the steering and flexibility of the UAV in flight are deteriorated and the maneuverability of the UAV is greatly restricted when the lower center of gravity height is not needed. The center of gravity height of the UAV body 1 is automatically and accurately regulated; The feedback conductive contact 47 and the feedback resistor rod 46 are also connected in series to the power supply circuit of the dual-axis motor 23, and the dual-axis motor 23 is a DC motor device. When the center of gravity height of the UAV body 1 is adjusted by the dual-axis motor 23, the heavier the weight of the cargo, the greater the access resistance of the feedback resistor rod 46, and thus the lower the rotation speed of the dual-axis motor 23. Within 5 seconds of the dual-axis motor 23 working to adjust the center of gravity, the displacement distance of the cargo is smaller. Because when the cargo is heavier, in order to achieve the same torque change to adjust the center of gravity, the required force arm (that is, the distance of the center of gravity height adjustment) will be relatively smaller, thereby achieving more precise adjustment of the center of gravity height of the UAV and ensuring the stability of the UAV flight.

[0026] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A rotary wing drone, comprising a drone body (1), characterized in that: Also includes: A center of gravity adjustment mechanism (2) is fixedly mounted on the bottom end of the drone body (1); a loading connection mechanism (3) is fixedly mounted on the mobile end of the center of gravity adjustment mechanism (2); a weighing feedback mechanism (4) is mounted between the mobile end of the center of gravity adjustment mechanism (2) and the upper end of the loading connection mechanism (3); a center of gravity height control drive mechanism (5) is fixedly mounted on the lower end of the drone body (1) and is electrically connected to the center of gravity adjustment mechanism (2); a wind force monitoring mechanism (6) is fixedly mounted on the upper end of the drone body (1) and is electrically connected to the center of gravity height control drive mechanism (5); and a PLC controller (7) is fixedly mounted on the lower end of the drone body (1) and is electrically connected to the center of gravity adjustment mechanism (2), the loading connection mechanism (3), the weighing feedback mechanism (4), the center of gravity height control drive mechanism (5) and the wind force monitoring mechanism (6).

2. A rotary wing UAV according to claim 1, characterized in that: The center of gravity adjustment mechanism (2) comprises a fixed shell (21) fixedly mounted at the lower end of the drone body (1); two adjusting screws (22) are symmetrically rotatably connected at the bottom of the inner wall of the fixed shell (21) and the lower end of the drone body (1); the bottom end of the drone body (1) is configured as a hollow structure; the upper ends of the adjusting screws (22) penetrate and extend into the bottom end of the drone body (1); a dual-axis motor (23) is fixedly mounted on the inner side of the bottom end of the drone body (1); both output ends of the dual-axis motor (23) are transmission-connected to the upper ends of the adjusting screws (22) via bevel gear assemblies (24); and the rod walls of the two adjusting screws (22) are threadedly sleeved with a common lifting plate (25).

3. A rotary wing UAV according to claim 2, characterized in that: The loading connection mechanism (3) comprises a plurality of support slide bars (31) symmetrically fixedly mounted on the lower end of the lifting plate (25); the plurality of support slide bars (31) are slidably sleeved with a same U-shaped connecting plate (32); the lower end of the U-shaped connecting plate (32) is fixedly connected with a loading plate (33); the lower end of the fixed shell (21) is provided with a rectangular opening for the lower end of the U-shaped connecting plate (32) to extend through; the surface of the U-shaped connecting plate (32) is provided with a plurality of sleeve holes slidably sleeved with the support slide bars (31); and the inner walls of the corresponding sleeve holes are embedded with positioning electromagnetic blocks (34); the rod wall of the support slide bar (31) is embedded with a positioning permanent magnetic strip (35) in contact with the positioning electromagnetic block (34); and the upper end of the U-shaped connecting plate (32) and the lower end of the lifting plate (25) are fixedly provided with a plurality of pulling springs (36) sleeved outside the support slide bars (31).

4. A rotary wing UAV according to claim 3, characterized in that: The weighing feedback mechanism (4) comprises a transmission rack (41) fixedly mounted on the lower end of the lifting plate (25), the lower end of the transmission rack (41) passing through the upper end of the U-shaped connecting plate (32), a feedback shell (42) fixedly mounted on the lower end of the horizontal portion of the U-shaped connecting plate (32), a transmission screw (43) rotatably connected to the inner wall of the feedback shell (42), one end of the transmission screw (43) passing through and extending out of the feedback shell (42) and fixedly connected to a transmission gear (44) meshing with the transmission rack (41), a transmission seat (45) threadedly sleeved on the rod wall of the transmission screw (43), and a feedback resistor rod (44) arranged parallel to the transmission screw (43) fixedly mounted on the inner wall of the feedback shell (42). 46), a through hole is formed on the side wall of the transmission seat (45) and is sleeved on the outside of the feedback resistor rod (46), and a feedback conductive contact piece (47) that is in electrical contact with the feedback resistor rod (46) is fixedly mounted on the inner wall of the corresponding through hole, a prompt switch (48) is fixedly mounted on the lower end of the transmission seat (45), a rotating screw rod (49) is rotatably connected to the lower side of the inner wall of the feedback shell (42), a rotating motor (410) for driving the rotating screw rod (49) to rotate is fixedly mounted on the outer wall of the feedback shell (42), a moving block (411) is threadedly sleeved on the rod wall of the rotating screw rod (49), and a pressing round head (412) corresponding to the position of the prompt switch (48) is fixedly mounted on the upper end of the moving block (411).

5. The rotary wing UAV according to claim 1, characterized in that: The center of gravity height control driving mechanism (5) comprises a control shell (51), a plurality of guide slide bars (52) arranged side by side are fixedly mounted on the inner wall of the control shell (51), a same trigger plate (53) is slidably sleeved on the outer sides of the plurality of guide slide bars (52), upper and lower ends of the trigger plate (53) are both configured as arc head structures, a plurality of compensation springs (54) sleeved on the outer sides of the guide slide bars (52) are fixedly mounted on the opposite side of the trigger plate (53) and the control shell (51), a thrust permanent magnet plate (55) is fixedly mounted on the side wall of the trigger plate (53), and the inner wall of the control shell (51) is fixedly mounted. A thrust electromagnetic plate (56) is arranged opposite to the thrust permanent magnet plate (55), a driving screw (57) is rotatably connected to the upper side of the inner wall of the control housing (51), a driving motor (58) for driving the driving screw (57) to rotate is fixedly mounted on the outer wall of the control housing (51), a driving block (59) is threadedly sleeved on the rod wall of the driving screw (57), a U-shaped mounting plate (510) is fixedly connected to the lower end of the driving block (59), and a lifting control switch (511) and a lowering control switch (512) are fixedly mounted on the upper and lower ends of the inner wall of the U-shaped mounting plate (510), respectively.

6. The rotary wing UAV according to claim 1, characterized in that: The wind force monitoring mechanism (6) comprises a monitoring shell (61) fixedly mounted on the upper end of the drone body (1); a forced wind wheel (62) is rotatably sleeved on the upper end of the monitoring shell (61); a generator (63) is fixedly mounted inside the monitoring shell (61); and a rotating end of the forced wind wheel (62) is fixedly connected to an input end of the generator (63).

7. A rotary wing UAV according to claim 2, characterized in that: A plurality of limit sliding blocks are symmetrically fixedly mounted on the outer wall of the lifting plate (25), and a limit sliding groove matching and slidingly connected with the limit sliding blocks is provided on the inner side of the fixed shell (21).

8. The rotary wing UAV according to claim 3, characterized in that: The lower end of the support slide bar (31) is fixedly connected to an anti-slip plate (37), and the lower end of the horizontal portion of the U-shaped connecting plate (32) is fixedly provided with an alarm switch (38) arranged corresponding to the position of the anti-slip plate (37).

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