Unmanned aerial vehicle surveying and mapping instrument protection structure
By setting up a dust removal mechanism for the suction fan in the drone, the problem of dust and water vapor adhesion of the wings in harsh environments is solved, the flight stability and mapping accuracy are improved, and the risk of wing damage is reduced.
Patent Information
- Application Number
- CN202420628977.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-03-29
- Publication Date
- 2025-03-14
- Estimated Expiration
- 2034-03-29
AI Technical Summary
During flight detection in harsh environments, the drone wings are prone to adhere to dust and water vapor, resulting in reduced balance, reduced detection accuracy, and easily damaged when falling.
A protective structure of drone surveying and mapping instruments is designed, including a dust removal mechanism for setting up a suction fan inside the drone shell, blow-air cleaning of the wing surface through the suction duct and the air outlet duct, and filtering and collecting dust and impurities through a filter net and a collection box.
Effectively clean the dust and water vapor on the surface of the wing, improve the flight stability of the wing, improve the surveying and mapping accuracy, and reduce the risk of wing damage through protective mechanisms.
Smart Images
Figure CN222607405U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a protective structure of an unmanned aerial vehicle surveying and mapping instrument. Background Art
[0002] UAV aerial survey is a powerful supplement to traditional aerial photogrammetry. It is characterized by flexibility, high efficiency, precision, accuracy, low operating cost, wide application range and short production cycle. It has obvious advantages in quickly acquiring high-resolution images in small areas and areas with difficult flight. With the development of UAV and digital camera technology, digital aerial photography technology based on UAV platform has shown its unique advantages.
[0003] At present, in the process of drone aerial survey, surveying and mapping instruments are needed for aerial survey, and in the process of flight detection in harsh environments, the wings of the drone are often adhered to a large amount of dust and water vapor, which can easily affect the rotation of the drone wings, reducing the balance of the drone, thereby reducing the detection accuracy. At the same time, in special circumstances, when the drone falls, the wings are easily damaged by impact, causing the drone to lose its detection ability. Utility Model Content
[0004] The purpose of the utility model is to provide a protective structure for an unmanned aerial vehicle surveying and mapping instrument, so as to solve the problem proposed in the above-mentioned background technology that during flight detection in harsh environments, a large amount of dust and water vapor often adhere to the wings of the unmanned aerial vehicle, which can easily affect the rotation of the wings of the unmanned aerial vehicle, reduce the balance of the unmanned aerial vehicle, and thus reduce the detection accuracy.
[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a protective structure for an unmanned aerial vehicle surveying and mapping instrument, comprising an unmanned aerial vehicle shell, wings, and a frame, wherein the wings are arranged on the side walls of the unmanned aerial vehicle shell, and the frame is fixedly installed at the bottom end of the unmanned aerial vehicle shell; a dust removal mechanism with a suction fan is arranged inside the unmanned aerial vehicle shell, and the dust removal mechanism comprises a suction fan, and the suction fan is fixedly installed inside the unmanned aerial vehicle shell; an air outlet pipe is fixedly installed at the output end of the suction fan, and the free end of the air outlet pipe is located at the bottom end of the wing; an air inlet pipe is fixedly installed at the output end of the suction fan, and the free end of the air inlet pipe is connected to and installed with an air suction pipe, and the free end of the air suction pipe is located at the bottom end of the wing.
[0006] As a preferred technical solution of the utility model, an auxiliary mechanism is arranged inside the air suction pipe, and the auxiliary mechanism includes a collecting box and a filter. The collecting box is installed between the air suction pipe and the air inlet pipe, and the bottom end of the collecting box is connected to the outside world. The filter is arranged at one end of the air inlet pipe located inside the collecting box. A rotating plate is rotatably installed inside the collecting box, and a first spring is fixedly installed between the rotating plate and the inner wall of the collecting box.
[0007] As a preferred technical solution of the utility model, a fixed rod is rotatably installed on the top of the rotating plate, a scraper is fixedly installed on the top of the fixed rod, the scraper slides on the surface of the filter, a limit plate is fixedly installed on one end of the air inlet pipe close to the filter, and a second spring is fixedly installed between the limit plate and the fixed rod.
[0008] As a preferred technical solution of the utility model, a spiral impeller is rotatably installed inside the air suction pipe, a rotating rod is fixedly installed on the shaft end of the wing, and a belt is installed for transmission between the rotating rod and the outer surface of the spiral impeller.
[0009] As a preferred technical solution of the utility model, a protective mechanism is provided on the outer surface of the wing, and the protective mechanism includes a baffle. A support rod is fixedly installed on the outer surface of the UAV shell close to the wing, and the baffle is fixedly installed on the top of the support rod, and the wing is located inside the baffle. A protective net is fixedly installed on the top of the baffle, and a plurality of viscoelastic dampers are arranged between the baffle and the supporting mechanism of the wing.
[0010] Compared with the prior art, the beneficial effects of the utility model are:
[0011] 1. The utility model provides a suction fan so that when the UAV performs flight detection, the suction fan can blow air on the surface of the wing, so that the dust and water vapor adhering to the surface of the wing can be cleaned and dried, thereby ensuring the flight stability of the wing and improving the surveying and mapping accuracy. At the same time, the blown dust can be adsorbed and discharged through the suction pipe, thereby further cleaning the wing and preventing the wing from being disturbed by dust circulation.
[0012] 2. The utility model provides a viscoelastic damper so that when the UAV performs flight detection, the wings can be shielded by baffles and protective nets, thereby achieving further protection of the wings, preventing the wings from being affected by floating objects in the air, and also preventing the wings from being cushioned when the UAV malfunctions and falls, thereby reducing damage to the wings. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is a schematic diagram of the structure of the utility model;
[0014] Figure 2 This is a schematic diagram of the protective plate structure of the utility model;
[0015] Figure 3 This is a schematic diagram of the internal structure of the UAV shell of the utility model;
[0016] Figure 4 For the utility model Figure 3 Schematic diagram of the structure at point A in .
[0017] In the figure: 1. UAV shell; 2. Wing; 21. Protection mechanism; 211. Protection net; 212. Baffle; 213. Support rod; 214. Viscoelastic damper; 3. Frame; 4. Dust removal mechanism; 41. Suction fan; 42. Air outlet duct; 43. Air suction duct; 44. Auxiliary mechanism; 441. Spiral impeller; 442. Belt; 443. Rotating rod; 444. Collecting box; 445. First spring; 446. Rotating plate; 447. Fixed rod; 448. Second spring; 449. Limiting plate; 4410. Filter; 4411. Scraper; 45. Air inlet duct. DETAILED DESCRIPTION
[0018] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0019] See also Figure 1-4 , the utility model provides a technical solution for the protection structure of the UAV surveying and mapping instrument:
[0020] Embodiment 1:
[0021] according to Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the protective structure of the unmanned aerial vehicle surveying and mapping instrument includes a unmanned aerial vehicle shell 1, a wing 2, and a frame 3. The wing 2 is arranged on the side wall of the unmanned aerial vehicle shell 1, and the frame 3 is fixedly installed at the bottom end of the unmanned aerial vehicle shell 1. A dust removal mechanism 4 with a suction fan 41 is arranged inside the unmanned aerial vehicle shell 1. The dust removal mechanism 4 includes a suction fan 41, and the suction fan 41 is fixedly installed inside the unmanned aerial vehicle shell 1. An air outlet pipe 42 is fixedly installed at the output end of the suction fan 41. The free end of the air outlet pipe 42 is located at the bottom end of the wing 2. The output end of the suction fan 41 is fixedly installed. An air inlet pipe 45 is equipped, and air can be blown on the surface of the wing 2 through the air outlet pipe 42, so that the dust and water vapor adhered to the surface of the wing 2 can be cleaned and dried, thereby ensuring the flight stability of the wing 2 and improving the surveying and mapping accuracy. The air outlet pipe 42 can be blown on the surface of the wing 2, so that the dust and water vapor adhered to the surface of the wing 2 can be cleaned and dried, thereby ensuring the flight stability of the wing 2 and improving the surveying and mapping accuracy. The free end of the air inlet pipe 45 is connected to the air suction pipe 43, and the free end of the air suction pipe 43 is located at the bottom end of the wing 2.
[0022] An auxiliary mechanism 44 is provided inside the air suction pipe 43, and the auxiliary mechanism 44 includes a collection box 444 and a filter 4410. The collection box 444 is connected and installed between the air suction pipe 43 and the air inlet pipe 45, and the bottom end of the collection box 444 is connected and installed with the outside. The filter 4410 is arranged at one end of the air inlet pipe 45 located inside the collection box 444. A rotating plate 446 is rotatably installed inside the collection box 444, and a first spring 445 is fixedly installed between the rotating plate 446 and the inner wall of the collection box 444. A fixing rod 447 is rotatably installed on the top of the rotating plate 446, and a scraper 4411 is fixedly installed on the top of the fixing rod 447. The scraper 441 1 slides on the surface of the filter 4410, a limit plate 449 is fixedly installed at one end of the air inlet pipe 45 close to the filter 4410, a second spring 448 is fixedly installed between the limit plate 449 and the fixing rod 447, a spiral impeller 441 is rotatably installed inside the air suction pipe 43, a rotating rod 443 is fixedly installed at the shaft end of the wing 2, and a belt 442 is installed on the outer surface of the rotating rod 443 and the spiral impeller 441 for transmission. When the wing 2 rotates, the belt 442 is driven for transmission, and the belt 442 drives the spiral impeller 441 to rotate. The spiral impeller 441 can prevent the air suction pipe 43 from being blocked, which affects the extraction of dust and impurities.
[0023] During specific use, the protective structure of the unmanned aerial vehicle surveying and mapping instrument of the utility model, when the unmanned aerial vehicle performs flight detection, starts the suction fan 41 at this time, and can blow air to the surface of the wing 2 through the air outlet pipe 42, so that the dust and water vapor adhering to the surface of the wing 2 can be cleaned and dried, thereby ensuring the flight stability of the wing 2 and improving the surveying and mapping accuracy. At the same time, the dust blown off the surface of the wing 2 can be adsorbed and discharged through the suction pipe 43, and then filtered through the filter net 4410 and collected through the closed collection box 444. After that, through the action of gravity, the baffle 212 compresses the first spring 445, thereby opening the closed part of the bottom end of the collection box 444, and then the accumulated dust is discharged, thereby further realizing the cleaning of the wing 2 and preventing the wing 2 from being disturbed by dust circulation.
[0024] Embodiment 2:
[0025] On the basis of the first embodiment, Figure 1 and Figure 2As shown, a protective mechanism 21 is provided on the outer surface of the wing 2, and the protective mechanism 21 includes a baffle 212. A support rod 213 is fixedly installed on the outer surface of the UAV shell 1 near the wing 2. The baffle 212 is fixedly installed on the top of the support rod 213, and the wing 2 is located inside the baffle 212. A protective net 211 is fixedly installed on the top of the baffle 212. The baffle 212 and the protective net 211 can shield the wing 2 from dust. A plurality of viscoelastic dampers 214 are provided between the baffle 212 and the supporting mechanism of the wing 2. The viscoelastic dampers 214 can buffer the impact force to the greatest extent, so that the UAV can be protected when it is hit or falls due to a malfunction.
[0026] During specific use, the protective structure of the unmanned aerial vehicle surveying and mapping instrument of the utility model can shield and protect the wing 2 from dust through the baffle 212 and the protective net 211 when the unmanned aerial vehicle is performing flight detection, thereby achieving further protection for the wing 2 and preventing the wing 2 from being affected by floating objects in the air, so that the wing 2 cannot operate and is damaged. At the same time, a viscoelastic damper 214 is provided between the baffle 212 and the wing 2, so that when the wing 2 is hit, the viscoelastic damper 214 can buffer the impact force to the greatest extent, thereby protecting the unmanned aerial vehicle when it is hit or falls due to a malfunction, thereby reducing the degree of damage to the wing 2.
[0027] In the description of the present invention, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "axial", "radial", "circumferential" and the like indicating orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.
[0028] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.
[0029] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or a communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0030] In the present utility model, unless otherwise clearly specified and limited, the first feature "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. In the description of this specification, the description of reference terms "one scheme", "some schemes", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the scheme or example are included in at least one scheme or example of the present utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same scheme or example. Moreover, the specific features, structures, materials or characteristics described may be combined in a suitable manner in any one or more schemes or examples.
Claims
1. A protective structure for an unmanned aerial vehicle surveying and mapping instrument, comprising an unmanned aerial vehicle housing (1), wings (2), and a frame (3), characterized in that: The wing (2) is arranged on the side wall of the drone housing (1); the frame (3) is fixedly mounted on the bottom end of the drone housing (1); a dust removal mechanism (4) with a suction fan (41) is arranged inside the drone housing (1); the dust removal mechanism (4) comprises a suction fan (41); the suction fan (41) is fixedly mounted inside the drone housing (1); an air outlet pipe (42) is fixedly mounted on the output end of the suction fan (41); the free end of the air outlet pipe (42) is located at the bottom end of the wing (2); an air inlet pipe (45) is fixedly mounted on the output end of the suction fan (41); the free end of the air inlet pipe (45) is connected to an air suction pipe (43); the free end of the air suction pipe (43) is located at the bottom end of the wing (2).
2. The protective structure for the UAV surveying and mapping instrument according to claim 1 is characterized by: An auxiliary mechanism (44) is arranged inside the air suction pipe (43), and the auxiliary mechanism (44) comprises a collection box (444) and a filter (4410). The collection box (444) is installed between the air suction pipe (43) and the air inlet pipe (45), and the bottom end of the collection box (444) is connected to the outside. The filter (4410) is arranged at one end of the air inlet pipe (45) located inside the collection box (444). A rotating plate (446) is rotatably installed inside the collection box (444), and a first spring (445) is fixedly installed between the rotating plate (446) and the inner wall of the collection box (444).
3. The protective structure for the UAV surveying and mapping instrument according to claim 2 is characterized in that: A fixing rod (447) is rotatably mounted on the top of the rotating plate (446), a scraper (4411) is fixedly mounted on the top of the fixing rod (447), and the scraper (4411) slides on the surface of the filter screen (4410). A limiting plate (449) is fixedly mounted on one end of the air inlet pipe (45) close to the filter screen (4410), and a second spring (448) is fixedly mounted between the limiting plate (449) and the fixing rod (447).
4. The protective structure for the UAV surveying and mapping instrument according to claim 1 is characterized by: A spiral impeller (441) is rotatably mounted inside the air suction pipe (43), a rotating rod (443) is fixedly mounted on the shaft end of the wing (2), and a belt (442) is transmission-mounted on the outer surfaces of the rotating rod (443) and the spiral impeller (441).
5. The protective structure for the UAV surveying and mapping instrument according to claim 1 is characterized by: The outer surface of the wing (2) is provided with a protective mechanism (21), the protective mechanism (21) comprising a baffle (212), a support rod (213) is fixedly mounted on the outer surface of the drone housing (1) close to the wing (2), the baffle (212) is fixedly mounted on the top of the support rod (213), and the wing (2) is located inside the baffle (212), a protective net (211) is fixedly mounted on the top of the baffle (212), and a plurality of viscoelastic dampers (214) are arranged between the baffle (212) and the supporting mechanism of the wing (2).