Wind resistance reducing structure of surveying and mapping unmanned aerial vehicle

Abstract

The utility model discloses a wind resistance reducing structure of a surveying and mapping unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises an unmanned aerial vehicle main body, unmanned aerial vehicle wings are arranged at four corners of the unmanned aerial vehicle main body, a surveying and mapping camera is arranged at the bottom of the unmanned aerial vehicle main body, and undercarriages are arranged on two sides of the bottom of the unmanned aerial vehicle main body in the width direction. A first resistance reducing mechanism is further arranged on the unmanned aerial vehicle body and comprises a storage shell, symmetrical shaft grooves are formed in the storage shell, first shaft rods are rotationally connected into the shaft grooves, the undercarriage is fixedly connected to the first shaft rods, a transmission cavity is formed in the front side of the storage shell, and a second shaft rod is rotationally connected into the transmission cavity; the first motor drives the second shaft rod to rotate, so that the worm is meshed with the worm gear, the first shaft rods on the two sides and the undercarriage are driven to synchronously overturn upwards in a mirror image mode, the undercarriage is contained in the containing groove, and therefore the wind resistance generated by the undercarriage to the unmanned aerial vehicle body is reduced.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a structure for reducing wind resistance in a surveying UAV. Background Technology

[0002] Surveying drones are unmanned aerial vehicle systems designed specifically for scenarios such as geographic information collection, topographic mapping, and engineering surveying. Their core advantage lies in the efficient and low-cost acquisition of high-precision spatial data, and they have widely replaced traditional manual surveying and manned drone surveying.

[0003] When existing surveying drones fly in the air, the landing gear of the drone will have a certain amount of wind resistance due to the strong wind at high altitudes, which will cause the camera to shake to a certain extent during the surveying process and affect the surveying results. Utility Model Content

[0004] In order to overcome the above-mentioned defects of the prior art, this utility model provides a wind resistance reduction structure for surveying drones, so as to solve the problem that the landing gear of the drone will have a certain wind resistance on the drone due to the large wind force at high altitudes, which will cause the camera to shake to a certain extent during the drone surveying process.

[0005] To solve the above-mentioned technical problems, this utility model provides the following technical solution: a wind resistance reduction structure for a surveying drone, including a drone body, drone wings at all four corners of the drone body, a surveying camera at the bottom of the drone body, landing gears on both sides of the bottom width direction of the drone body, and a first drag reduction mechanism on the drone body. The first drag reduction mechanism includes a storage shell, symmetrical shaft grooves are opened in the storage shell, and a first shaft is rotatably connected in each shaft groove. The landing gear is fixedly connected to the first shaft. A transmission cavity is provided on the front side of the storage shell, a second shaft is rotatably connected in the transmission cavity, and a first motor for driving the second shaft to rotate is fixedly installed in the transmission cavity. Symmetrical worm gears are provided at both ends of the second shaft. A worm wheel is fixedly installed at the end of the first shaft near the second shaft, and the worm gear meshes with the worm gear.

[0006] Preferably, storage slots are provided on both the front and rear sides of the storage shell, and the landing gear can be stored in the storage slots.

[0007] Preferably, the landing gear is arranged in a U-shape.

[0008] Preferably, the storage shell is provided with a second drag-reducing mechanism, which includes slide rails on the front and rear sides of the storage shell. A cover plate is attached to both the front and rear sides of the storage shell. A first slider and a second slider are fixedly installed on the bottom sides of the cover plate, respectively. The first slider and the second slider are slidably installed in the slide rails. The storage shell is also provided with a lifting mechanism.

[0009] Preferably, the lifting mechanism includes an anti-detachment rod, a threaded rod, and a second motor. The second motor is fixedly installed inside the housing. The threaded rod is rotatably installed in a set of slide rails. The anti-detachment rod is fixedly installed in another set of slide rails. The first slider is threadedly connected to the threaded rod, and the second slider is slidably sleeved on the outer surface of the anti-detachment rod.

[0010] Preferably, there are two sets of slide rails, with two slide rails in each set.

[0011] Preferably, the cover plate is configured with a frustum-shaped structure.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] This invention uses a first motor to drive the second shaft to rotate, causing the worm gear to mesh with the worm wheel, which in turn drives the first shafts on both sides and the landing gear to rotate upwards in a mirror image, thus storing the landing gear in the storage slot and reducing the wind resistance generated by the landing gear on the main body of the drone.

[0014] This invention uses a second motor to drive a threaded rod to rotate, which in turn drives a first slider. This allows the cover plate to move vertically up and down along a slide rail via the first and second sliders. When the landing gear is being retracted or extended, the cover plate can be lifted to open the storage slot. After the landing gear is retracted or extended, the cover plate can be lowered to seal the storage slot, making the side of the drone body a smooth surface. Airflow can flow smoothly along the surface, reducing turbulence. At the same time, the cover plate fills the "recessed area" of the storage slot, preventing the airflow from forming vortices in the storage slot, thereby further reducing the wind resistance of the drone body. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the main structure of this utility model;

[0016] Figure 2 This is an exploded view of the main structure of this utility model;

[0017] Figure 3 This is a front sectional view of the relevant structure of the first drag-reducing mechanism of this utility model;

[0018] Figure 4 This is a side sectional view of the relevant structure of the first drag reduction mechanism of this utility model;

[0019] Figure 5 This is a schematic diagram of the relevant structure of the second drag-reducing mechanism of this utility model.

[0020] [Figure Labels]

[0021] 1. Drone body; 2. Drone wing; 3. Mapping camera; 4. Landing gear; 5. First drag reduction mechanism; 51. Storage shell; 52. Shaft groove; 53. First shaft; 54. Transmission cavity; 55. Second shaft; 56. First motor; 57. Worm gear; 58. Worm wheel; 59. Storage slot; 6. Second drag reduction mechanism; 61. Slide rail; 62. Anti-detachment rod; 63. Threaded rod; 64. Second motor; 65. First slider; 66. Second slider; 67. Cover plate. Detailed Implementation

[0022] To make the technical problems, technical solutions and advantages of this utility model clearer, a detailed description will be given below in conjunction with the accompanying drawings and specific embodiments.

[0023] As attached Figure 1 To be continued Figure 5 This utility model provides a wind resistance reduction structure for a surveying drone, including a drone body 1, with drone wings 2 at each of the four corners of the drone body 1, a surveying camera 3 at the bottom of the drone body 1, and landing gear 4 on both sides of the bottom width direction of the drone body 1. The drone body 1 also has a first drag reduction mechanism 5, which includes a housing 51 with symmetrical shaft grooves 52 inside. Each shaft groove 52 is rotatably connected to a first shaft 53, and the landing gear 4 is fixedly connected to the first shaft 53. A transmission cavity 54 is provided on the front side of the storage shell 51. A second shaft 55 is rotatably connected in the transmission cavity 54. A first motor 56 for driving the second shaft 55 to rotate is fixedly installed in the transmission cavity 54. Symmetrical worm gears 57 are provided at both ends of the second shaft 55. A worm wheel 58 is fixedly installed at the end of the first shaft 53 near the second shaft 55. The worm gears 57 mesh with the worm wheel 58. Storage slots 59 are provided on both the front and rear sides of the storage shell 51. The landing gear 4 can be stored in the storage slots 59. The landing gear 4 is a rectangular frame with one side open, forming a U-shape.

[0024] Specifically, after the main body of the drone 1 takes off through the drone wing 2, it starts the first motor 56 using its own control system. The first motor 56 drives the second shaft 55 to rotate, causing the worm gear 57 to mesh with the worm wheel 58. This causes the first shafts 53 on both sides and the landing gear 4 to rotate upward synchronously and mirrorively, so that the landing gear 4 is stored in the storage slot 59, thereby reducing the wind resistance generated by the landing gear 4 on the main body of the drone 1.

[0025] Furthermore, the storage shell 51 is provided with a second drag-reducing mechanism 6, which includes slide rails 61 on the front and rear sides of the storage shell 51. A cover plate 67 is fitted to both the front and rear sides of the storage shell 51. A first slider 65 and a second slider 66 are fixedly installed on the bottom sides of the cover plate 67, respectively. The first slider 65 and the second slider 66 are slidably installed within the slide rails 61. The storage shell 51 is also provided with a lifting mechanism, which includes an anti-detachment rod 62, a threaded rod 63, and a second motor 64. The second motor 64 is fixedly installed within the storage shell 51. The threaded rod 63 is rotatably installed within one set of slide rails 61, and the anti-detachment rod 62 is fixedly installed within another set of slide rails 61. The first slider 65 is threadedly connected to the threaded rod 63, and the second slider 66 is slidably sleeved on the outer surface of the anti-detachment rod 62. There are two sets of slide rails 61, each set consisting of two slide rails. The cover plate 67 is arranged in a frustum-shaped structure.

[0026] Specifically, the control system of the drone body 1 starts the second motor 64, which drives the threaded rod 63 to rotate. This threaded rod drives the first slider 65, allowing the cover plate 67 to rise and fall vertically along the slide rail 61 via the first slider 65 and the second slider 66. When the landing gear 4 is being retracted or extended, the cover plate 67 can be raised to open the storage slot 59. After the landing gear 4 is retracted or extended, the cover plate 67 can be lowered to cover the storage slot 59, making the side of the drone body 1 a smooth surface. Airflow can flow smoothly along the surface, reducing turbulence. At the same time, the cover plate 67 fills the "recessed area" of the storage slot 59, preventing the airflow from forming vortices in the storage slot 59, thereby further reducing the wind resistance of the drone body 1.

[0027] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change.

[0028] Secondly: The accompanying drawings of the embodiments disclosed in this utility model only involve the structures involved in the embodiments disclosed in this utility model. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this utility model can be combined with each other.

[0029] Finally: The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A wind resistance reduction structure for a surveying drone, comprising a drone body (1), drone wings (2) provided at each of the four corners of the drone body (1), a surveying camera (3) provided at the bottom of the drone body (1), and landing gear (4) provided on both sides of the bottom width direction of the drone body (1), characterized in that, A first drag reduction mechanism (5) is further provided on the UAV body (1). The first drag reduction mechanism (5) includes a storage shell (51). Symmetrical shaft grooves (52) are formed in the storage shell (51). First shafts (53) are rotatably connected in the shaft grooves (52). The landing gear (4) is fixedly connected to the first shafts (53). A transmission cavity (54) is provided on the front side of the storage shell (51). A second shaft (55) is rotatably connected in the transmission cavity (54). A first motor (56) for driving the second shaft (55) to rotate is fixedly installed in the transmission cavity (54). Symmetrical spiral threads (57) are provided at both ends of the second shaft (55). A worm gear (58) is fixedly installed at one end of the first shaft (53) close to the second shaft (55). The spiral threads (57) are engaged with the worm gear (58).

2. The wind resistance reduction structure for a mapping UAV according to claim 1, characterized in that, Storage grooves (59) are formed on both the front and rear sides of the storage shell (51). The landing gear (4) can be stored in the storage grooves (59).

3. The wind resistance reduction structure for a mapping UAV according to claim 1, characterized in that, The landing gear (4) is arranged in a U shape.

4. The wind resistance reduction structure for a mapping UAV according to claim 2, characterized in that, A second drag reduction mechanism (6) is provided on the storage shell (51). The second drag reduction mechanism (6) includes slide rails (61) formed on both the front and rear sides of the storage shell (51). Cover plates (67) are respectively and closely arranged on both the front and rear sides of the storage shell (51). First sliders (65) and second sliders (66) are respectively fixedly installed at both sides of the bottom of the cover plates (67). The first sliders (65) and the second sliders (66) are both slidably installed in the slide rails (61). A lifting mechanism is further provided on the storage shell (51).

5. The wind resistance reduction structure for a mapping UAV according to claim 4, characterized in that, The lifting mechanism includes an anti - detachment rod (62), a threaded rod (63), and a second motor (64). The second motor (64) is fixedly installed in the storage shell (51). The threaded rod (63) is rotatably installed in a group of slide rails (61). The anti - detachment rod (62) is fixedly installed in the other group of slide rails (61). The first slider (65) is threadedly connected to the threaded rod (63). The second slider (66) is slidably sleeved on the outer surface of the anti - detachment rod (62).

6. The wind resistance reduction structure for a mapping UAV according to claim 4, characterized in that, There are two groups of slide rails (61), and each group has two slide rails.

7. The wind resistance reduction structure for a mapping UAV according to claim 4, characterized in that, The cover plates (67) are arranged in a frustum - shaped structure.

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