Wind resistance device of remote sensing surveying and mapping unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and discloses a wind resistance device of a remote sensing surveying and mapping unmanned aerial vehicle. The device comprises a device body, a surveying and mapping camera is arranged at the bottom of the device body, two symmetrically-arranged lifting grooves are formed in the bottom of the device body, the inner wall of each lifting groove is slidably connected with a lifting leg, and a lifting assembly used for lifting the lifting legs is installed on the device body; the bottom of each landing leg is provided with a damping assembly used for damping the fuselage main body, after the unmanned aerial vehicle lifts off, the lifting assemblies are controlled to drive the two landing legs to move upwards, the landing legs are folded and enter the lifting grooves, and the situation that the landing legs block shooting of the surveying and mapping camera is avoided; the probability that the unmanned aerial vehicle shakes during shooting and surveying due to the fact that wind resistance is increased outside the landing legs is reduced, when landing is needed, the two landing legs are driven by controlling the lifting assembly to move downwards and make contact with the ground through the damping assembly, impact force generated during landing of the unmanned aerial vehicle is reduced, and protection for the surveying and mapping camera is facilitated.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an anti-wind resistance device for a remote sensing mapping unmanned aerial vehicle. Background Art

[0002] An unmanned aerial vehicle is an unpiloted aircraft controlled by a radio remote control device or an on-board computer program control system. The unmanned aerial vehicle has a simple structure and low use cost. It can not only complete the tasks performed by a piloted aircraft, but is more suitable for tasks that a piloted aircraft is not suitable for, such as geological disaster surveys in dangerous areas, aerial rescue command, and environmental remote sensing monitoring.

[0003] Remote sensing mapping unmanned aerial vehicles all need to take pictures and conduct mapping at high altitudes, where the wind force is relatively large. The landing gears of existing remote sensing mapping unmanned aerial vehicles cannot be retracted. This not only increases the wind resistance, making it easy for the unmanned aerial vehicle to shake during picture taking and mapping, but also easily blocks the shooting of the mapping camera, thus affecting the shooting effect of the remote sensing mapping unmanned aerial vehicle. Content of the Utility Model

[0004] In order to solve the above problems, the utility model provides an anti-wind resistance device for a remote sensing mapping unmanned aerial vehicle.

[0005] The above technical purpose of the utility model is achieved through the following technical solutions: An anti-wind resistance device for a remote sensing mapping unmanned aerial vehicle includes a fuselage main body. A mapping camera is arranged at the bottom of the fuselage main body. Two symmetrically arranged lifting grooves are opened at the bottom of the fuselage main body. A landing leg is slidably connected to the inner wall of each lifting groove. A lifting assembly for lifting the landing legs is installed on the fuselage main body. A shock absorption assembly for shock-absorbing the fuselage main body is installed at the bottom of each landing leg.

[0006] By adopting the above technical solutions, when the unmanned aerial vehicle takes off, the two landing legs are driven to move upward by controlling the lifting assembly, so that the landing legs are retracted into the lifting grooves, avoiding the situation where the landing legs block the shooting of the mapping camera, reducing the probability of the landing legs increasing the wind resistance outside and causing the unmanned aerial vehicle to shake during picture taking and mapping. When landing is required, the two landing legs are driven to move downward by controlling the lifting assembly and contact the ground through the shock absorption assembly, reducing the impact force generated when the unmanned aerial vehicle lands, which is beneficial to protecting the mapping camera.

[0007] Further, two symmetrically arranged mounting grooves are formed at the top of the fuselage main body. The lifting assembly includes a driving motor fixed to the inner bottom wall of the mounting groove. The output shaft of the driving motor penetrates the inner bottom wall of the mounting groove and is rotatably connected. The lifting assembly further includes a controller fixed to the side wall of the fuselage main body and electrically connected to the driving motor, a wireless transceiver fixed to the side wall of the fuselage main body and electrically connected to the controller, and a threaded rod fixed to the end of the output shaft of the driving motor. The landing leg is sleeved on the threaded rod and is threadedly connected to the threaded rod.

[0008] By adopting the above technical solution, when the landing leg needs to be lifted or lowered, the controller receives the signal received by the wireless transceiver and controls the driving motor to start, driving the threaded rod to rotate. Since the threaded rod is threadedly connected to the landing leg and the landing leg is slidably connected to the inner wall of the lifting groove, the landing leg is caused to move along the axial direction of the threaded rod, thereby lifting or lowering the landing leg.

[0009] Further, each shock absorption assembly includes a base provided at the bottom of the landing leg. A chute is formed on the upper surface of the base. The shock absorption assembly further includes a mounting plate fixed to the bottom of the landing leg and slidably connected to the inner wall of the chute, and a shock absorption spring provided in the chute. The upper end of the shock absorption spring is fixed to the bottom of the mounting plate, and the lower end of the shock absorption spring is fixed to the inner bottom wall of the chute.

[0010] By adopting the above technical solution, the setting of the shock absorption assembly reduces the impact force generated when the drone lands and collides with the ground, playing a protective role for the drone and the mapping camera.

[0011] Further, a receiving groove matching the base is formed at the bottom of the fuselage main body.

[0012] By adopting the above technical solution, after the drone takes off, the landing leg is retracted by the driving assembly, and the base simultaneously enters the receiving groove, avoiding the situation that the base increases the wind resistance outside.

[0013] Further, a limiting groove is formed on the inner wall of the chute, and a limiting block slidably connected to the inner wall of the limiting groove is fixed to the side wall of the mounting plate.

[0014] By adopting the above technical solution, the limiting block is slidably connected to the limiting groove, which plays a role in restricting the moving position of the mounting plate, avoiding the situation that the base detaches from the mounting plate, and is beneficial to the normal use of the shock absorption assembly.

[0015] Further, a rubber pad is fixed to the bottom of the base.

[0016] By adopting the above technical solution, the rubber pad is made of rubber material, and its material is elastic, playing a good shock absorption role and reducing the wear generated between the bottom of the base and the ground.

[0017] Furthermore, a sliding groove is formed in the inner wall of the lifting groove, and a sliding block is fixed on the side wall of the landing leg and is slidably connected to the inner wall of the sliding groove.

[0018] By adopting the above technical solution, the sliding block is slidably connected in the sliding groove to limit the lifting range of the landing leg, avoiding the situation that the landing leg disengages downward from the lifting groove.

[0019] Furthermore, a trapezoidal groove is formed at the intersection between the inner wall of the installation groove and the upper surface of the fuselage main body, and a trapezoidal baffle plate that cooperates with the trapezoidal groove is hinged on the upper surface of the fuselage main body.

[0020] By adopting the above technical solution, the trapezoidal baffle plate protects the drive motor in the installation groove. The cross-sections of both the trapezoidal groove and the trapezoidal baffle plate are trapezoidal, which is convenient for the staff to open and close the trapezoidal baffle plate for maintaining the drive motor.

[0021] In summary, the present utility model has the following beneficial effects:

[0022] 1. In this application, when the drone takes off, by controlling the lifting component, the two landing legs are driven to move upward, so that the landing legs are retracted into the lifting groove, avoiding the situation that the landing legs block the shooting of the mapping camera, reducing the probability of the landing legs increasing wind resistance outside and causing the drone to shake during mapping shooting. When landing is required, by controlling the lifting component, the two landing legs are driven to move downward and contact the ground through the shock absorption component, reducing the impact force generated when the drone lands, which is beneficial to protecting the mapping camera;

[0023] 2. In this application, when the landing legs need to be lifted or lowered, the controller receives the signal received by the wireless transceiver and controls the drive motor to start and drive the threaded rod to rotate. Since the threaded rod is threadedly connected to the landing leg and the landing leg is slidably connected to the inner wall of the lifting groove, the landing leg moves along the axial direction of the threaded rod, thereby lifting or lowering the landing leg;

[0024] 3. In this application, the setting of the shock absorption component reduces the impact force generated when the drone collides with the ground during landing, playing a protective role for the drone and the mapping camera. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is the overall structural schematic diagram of an embodiment of the present utility model;

[0026] Figure 2 is the cross-sectional structural schematic diagram of an embodiment of the present utility model;

[0027] Figure 3 is Figure 2 the enlarged schematic diagram of part A in

[0028] In the figure: 1. Body main body; 11. Lifting groove; 12. Installation groove; 13. Accommodation groove; 14. Sliding groove; 15. Trapezoidal groove; 2. Surveying and mapping camera; 3. Landing leg; 4. Lifting component; 41. Driving motor; 42. Controller; 43. Wireless transceiver; 44. Threaded rod; 5. Shock absorption component; 51. Base; 511. Sliding groove; 512. Limiting groove; 52. Mounting plate; 53. Shock absorption spring; 6. Limiting block; 7. Rubber pad; 8. Sliding block; 9. Trapezoidal baffle. Detailed implementation manners

[0029] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application; obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0030] As Figures 1 - 3 shown, the embodiments of the present application disclose an anti-wind resistance device for a remote sensing surveying and mapping unmanned aerial vehicle, including a body main body 1, a surveying and mapping camera 2, landing legs 3, a lifting component 4, and a shock absorption component 5.

[0031] The body main body 1 is a body main body 1 commonly used in the prior art and applicable to this embodiment. Two symmetrically arranged lifting grooves 11 are opened at the bottom of the body main body 1, and two symmetrically arranged installation grooves 12 are opened at the top of the body main body 1. The surveying and mapping camera 2 is a surveying and mapping camera 2 commonly used in the prior art and applicable to this embodiment, and is used for remote sensing surveying. The surveying and mapping camera 2 is arranged at the bottom of the body main body 1. The landing legs 3 are of a cuboid structure, and there are two landing legs 3, and the two landing legs 3 are respectively slidably connected to the inner walls of the two lifting grooves 11.

[0032] The lifting component 4 is installed on the body main body 1 and is used for lifting the landing legs 3. The lifting component 4 includes a driving motor 41, a controller 42, a wireless transceiver 43, and a threaded rod 44. The driving motor 41 is fixed on the inner bottom wall of the installation groove 12, and the output shaft of the driving motor 41 penetrates through the inner bottom wall of the installation groove 12 and is rotatably connected. The controller 42 is fixed on the side wall of the body main body 1, and the controller 42 is electrically connected to the driving motor 41. The wireless transceiver 43 is fixed on the side wall of the body main body 1, and the wireless transceiver 43 is electrically connected to the controller 42. The threaded rod 44 is a rod-shaped structure arranged vertically, the threaded rod 44 is fixed at the end of the output shaft of the driving motor 41, the axis of the threaded rod 44 coincides with the end of the output shaft of the driving motor 41, and the landing legs 3 are sleeved on the threaded rod 44 and are threadedly connected to the threaded rod 44.

[0033] There are two sets of shock-absorbing components 5, and the two sets of shock-absorbing components 5 are respectively installed at the bottoms of the two landing legs 3 for shock-absorbing the fuselage main body 1. Each set of shock-absorbing components 5 includes a base 51, a mounting plate 52 and a shock-absorbing spring 53. The base 51 has a cuboid structure, the base 51 is arranged at the bottom of the landing leg 3, and a chute 511 is opened on the upper surface of the base 51. The mounting plate 52 has a rectangular plate structure, the mounting plate 52 is fixed at the bottom of the landing leg 3, and the mounting plate 52 is slidably connected to the inner wall of the chute 511. The shock-absorbing spring 53 is arranged in the chute 511, the upper end of the shock-absorbing spring 53 is fixed to the bottom of the mounting plate 52, and the lower end of the shock-absorbing spring 53 is fixed to the inner bottom wall of the chute 511.

[0034] After the drone takes off, the controller 42 receives the signal received by the wireless transceiver 43 to control the driving motor 41 to start and drive the threaded rod 44 to rotate. Since the threaded rod 44 is threadedly connected to the landing leg 3 and the landing leg 3 is slidably connected to the inner wall of the lifting groove 11, the landing leg 3 is moved along the axial direction of the threaded rod 44, so that the landing leg 3 is retracted into the lifting groove 11, avoiding the situation that the landing leg 3 blocks the shooting of the mapping camera 2, and reducing the probability that the landing leg 3 increases the wind resistance outside and causes the drone to shake during mapping shooting. When landing is required, the driving motor 41 is used to drive the threaded rod 44 to rotate in the reverse direction to move the two landing legs 3 downward, and the shock-absorbing spring 53 is used to buffer the impact force generated by the collision with the ground during landing, reducing the impact force generated when the drone lands, which is beneficial to protecting the mapping camera 2.

[0035] In order to avoid the increase of wind resistance caused by the base 51 outside, a receiving groove 13 matching the base 51 is opened at the bottom of the fuselage main body 1. After the drone takes off, the driving component is used to retract the landing leg 3, and the base 51 enters the receiving groove 13 at the same time, thus avoiding the situation that the base 51 increases the wind resistance outside.

[0036] In order to prevent the base 51 from detaching from the mounting plate 52, a limiting groove 512 is opened on the inner wall of the chute 511, and a limiting block 6 slidably connected to the inner wall of the limiting groove 512 is fixed on the side wall of the mounting plate 52. The limiting block 6 is slidably connected to the limiting groove 512, which restricts the moving position of the mounting plate 52, thus avoiding the situation that the base 51 detaches from the mounting plate 52 and is beneficial to the normal use of the shock-absorbing component 5.

[0037] In order to reduce the wear between the bottom of the base 51 and the ground, a rubber pad 7 is fixed at the bottom of the base 51. The rubber pad 7 is made of rubber material, and its material is elastic, playing a good shock-absorbing role, thereby reducing the wear between the bottom of the base 51 and the ground.

[0038] To prevent the lifting leg 3 from disengaging downward from the lifting slot 11, a sliding slot 14 is provided on the inner wall of the lifting slot 11, and a sliding block 8 fixedly connected to the side wall of the lifting leg 3 is slidably connected to the inner wall of the sliding slot 14. The sliding block 8 is slidably connected within the sliding slot 14 to limit the lifting range of the lifting leg 3, thereby preventing the lifting leg 3 from disengaging downward from the lifting slot 11.

[0039] To protect the drive motor 41, a trapezoidal slot 15 is provided at the intersection between the inner wall of the installation slot 12 and the upper surface of the fuselage main body 1. A trapezoidal baffle 9 that cooperates with the trapezoidal slot 15 is hinged to the upper surface of the fuselage main body 1. The trapezoidal baffle 9 protects the drive motor 41 within the installation slot 12. The cross-sections of both the trapezoidal slot 15 and the trapezoidal baffle 9 are trapezoidal, facilitating the staff to open and close the trapezoidal baffle 9 for maintaining the drive motor 41.

[0040] The working principle of the wind resistance device for a remote sensing mapping unmanned aerial vehicle in this embodiment is as follows: After the unmanned aerial vehicle takes off, the controller 42 receives the signal received by the wireless transceiver 43 to control the drive motor 41 to start and drive the threaded rod 44 to rotate. Since the threaded rod 44 is threadedly connected to the lifting leg 3 and the lifting leg 3 is slidably connected to the inner wall of the lifting slot 11, the lifting leg 3 moves along the axial direction of the threaded rod 44, causing the lifting leg 3 to retract into the lifting slot 11, preventing the lifting leg 3 from blocking the shooting of the mapping camera 2, and reducing the probability of the unmanned aerial vehicle shaking during mapping shooting due to the increased wind resistance of the lifting leg 3 outside. When landing is required, the drive motor 41 drives the threaded rod 44 to rotate in the reverse direction to move the two lifting legs 3 downward, and the shock absorption spring 53 buffers the impact force generated during the collision with the ground during landing, reducing the impact force generated when the unmanned aerial vehicle lands, which is beneficial to protecting the mapping camera 2.

[0041] The above description is only a preferred embodiment of the present invention. The protection scope of the present invention is not limited to the above embodiments. All technical solutions falling within the idea of the present invention belong to the protection scope of the present invention. It should be noted that for those of ordinary skill in the art in this technical field, several improvements and refinements made without departing from the principle of the present invention should also be regarded as within the protection scope of the present invention.

Claims

1. A wind resistance device for a remote sensing mapping unmanned aerial vehicle, comprising a fuselage main body (1), characterized in that: A surveying and mapping camera (2) is provided at the bottom of the fuselage main body (1). Two symmetrically arranged lifting grooves (11) are opened at the bottom of the fuselage main body (1). A landing leg (3) is slidably connected to the inner wall of each lifting groove (11). A lifting assembly (4) for lifting the landing legs (3) is installed on the fuselage main body (1). A shock absorption assembly (5) for shock-absorbing the fuselage main body (1) is installed at the bottom of each landing leg (3).

2. The anti-wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 1, characterized in that: Two symmetrically arranged installation grooves (12) are opened at the top of the fuselage main body (1). The lifting assembly (4) includes a driving motor (41) fixed to the inner bottom wall of the installation groove (12). The output shaft of the driving motor (41) penetrates the inner bottom wall of the installation groove (12) and is rotatably connected. The lifting assembly (4) further includes a controller (42) fixed to the side wall of the fuselage main body (1) and electrically connected to the driving motor (41), a wireless transceiver (43) fixed to the side wall of the fuselage main body (1) and electrically connected to the controller (42), and a threaded rod (44) fixed to the end of the output shaft of the driving motor (41). The landing leg (3) is sleeved on the threaded rod (44) and is threadedly connected to the threaded rod (44).

3. The anti-wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 1, characterized in that: Each shock absorption assembly (5) includes a base (51) provided at the bottom of the landing leg (3). A sliding groove (511) is opened on the upper surface of the base (51). The shock absorption assembly (5) further includes a mounting plate (52) fixed to the bottom of the landing leg (3) and slidably connected to the inner wall of the sliding groove (511), and a shock absorption spring (53) provided in the sliding groove (511). The upper end of the shock absorption spring (53) is fixed to the bottom of the mounting plate (52), and the lower end of the shock absorption spring (53) is fixed to the inner bottom wall of the sliding groove (511).

4. The wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 3, characterized in that: A receiving groove (13) for cooperating with the base (51) is opened at the bottom of the fuselage main body (1).

5. The wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 4, characterized in that: A limiting groove (512) is opened on the inner wall of the sliding groove (511). A limiting block (6) fixed to the side wall of the mounting plate (52) is slidably connected to the inner wall of the limiting groove (512).

6. The wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 5, characterized in that: A rubber pad (7) is fixed to the bottom of the base (51).

7. The wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 2, wherein: A sliding groove (14) is opened on the inner wall of the lifting groove (11). A sliding block (8) fixed to the side wall of the landing leg (3) is slidably connected to the inner wall of the sliding groove (14).

8. The anti-wind resistance device for a remote sensing mapping unmanned aerial vehicle according to claim 7, characterized in that: A trapezoidal groove (15) is opened at the intersection between the inner wall of the installation groove (12) and the upper surface of the fuselage main body (1). A trapezoidal baffle (9) cooperating with the trapezoidal groove (15) is hinged to the upper surface of the fuselage main body (1).

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