A micro aerial vehicle

Abstract

The present invention relates to the field of micro-UAVs, and discloses a micro-aircraft, including an aircraft body and a controller for wireless communication control thereof, wherein a driving mechanism is arranged inside the aircraft body, and a propeller and a tail driven by the driving mechanism are arranged above and on the rear side of the aircraft body, respectively, the propeller is a double-blade single propeller, the propeller blades of the propeller are fluid double-sided twisted structures, the tail is a single-sided double-blade propeller, and streamlined silicone components for shock absorption and noise reduction are arranged at multiple positions on one side of the propeller blade tail of the propeller, the length of the propeller is less than 125 mm, the total weight of the silicone components is less than 0.008 grams, and the total weight of the aircraft body is less than 32 grams. Small size, low noise, high concealment.

Description

Technical Field

[0001] The present invention relates to the field of micro-UAVs, and in particular to a micro-aircraft. Background Art

[0002] With the development of social technology, drones are being used more and more in various aspects. Drones are developing more and more deeply in the fields of micro-aircraft, bionic flapping wings and AI cluster control. In the development process of micro-drones, with the integrated equipment and loading of various functional components, while general micro-drones have sufficient power, the vibration amplitude and frequency of the drone's propeller increase, making the drone noisier during flight. The concealment of drones when used in specific fields is low, and it is difficult to meet increasingly high technical requirements. Summary of the invention

[0003] The present invention provides a micro-aircraft, which solves the technical problem that the propeller of the existing micro-aircraft vibrates greatly during flight, resulting in loud flight noise and poor concealment of the aircraft.

[0004] The technical solution adopted by the present invention to solve the technical problem is: a micro-aircraft, including an aircraft body and a controller for wireless communication control thereof, a driving mechanism is arranged inside the aircraft body, a propeller and a tail driven by the driving mechanism are arranged above and on the rear side of the aircraft body, respectively, the propeller is a double-bladed single propeller, the propeller blades of the propeller are fluid double-sided twisted structures, the tail is a single-sided double-bladed propeller, and streamlined silicone components for shock absorption and noise reduction are arranged at multiple positions on one side of the tail of the propeller blades of the propeller, the length of the propeller is less than 125 mm, the total weight of the silicone components is less than 0.008 grams, and the total weight of the aircraft body is less than 32 grams. Small size, low noise, high concealment.

[0005] The propeller is centrally symmetrical and includes a transmission connection part and a first propeller blade and a second propeller blade respectively fixed at both ends of the transmission connection part. The middle part of the transmission connection part is connected to a driving mechanism and driven to rotate by the driving mechanism. The integrated blade structure makes the transmission more balanced, the control simpler, and there is no crosstalk between the blades.

[0006] The silicone component includes two proximal silicone structures and two distal silicone structures that are centrally symmetrically arranged on the propeller, the two proximal silicone structures are respectively fixed at the connection between the two ends of the transmission connection part and the first propeller blade and the second propeller blade and are respectively located on one side of the tail of the first propeller blade and the second propeller blade, and the two distal silicone structures are respectively fixed on one end of the tail of the first propeller blade and the second propeller blade away from the transmission connection part. The structure is simple and the cost is reasonable.

[0007] The proximal silicone structure includes an elliptical first silicone part and a hemispherical second silicone part, one end of the circular cross section of the second silicone part is smoothly connected to the first silicone part, and one end of the first silicone part away from the second silicone part is smoothly connected to a smooth connecting rod vertically and smoothly connected to the transmission connection part, and the distal silicone structure includes a hemispherical third silicone component, a truncated cone-shaped fourth silicone component and a hemispherical fifth silicone component, the outer diameter of the third silicone component is smaller than the outer diameter of the fifth silicone component, and the diameters of the two ends of the fourth silicone component are respectively the same as the diameters of the third silicone component and the fifth silicone component and are respectively corresponding to the circular cross sections of the third silicone component and the fifth silicone component. The middle parts of the third silicone component and the fourth silicone component included in the two distal silicone structures are respectively fixed to the tail of the first propeller blade and the second propeller blade along the rotation direction of the propeller, and the length of the first propeller blade is 1.5 times the length of the transmission connection part, and the distal silicone structure is located at two-fifteenths of the first propeller blade away from the transmission connection part. Effectively relieve airflow and reduce the vibration and noise of the propeller blade of the propeller.

[0008] Furthermore, the front end of the aircraft body is provided with a flash, camera and thermal imaging component which are wirelessly connected to the controller and controlled by the controller. The controller includes a display component and a communication transmission component for sharing information with an external platform. It has daytime and nighttime reconnaissance capabilities, and can perform infrared reconnaissance on people, objects and mechanical equipment; a single person and a single machine can grasp the situation ahead in advance at a long distance, and has the ability to share and transmit videos and information in the background; in addition, multiple aircraft can obtain information on the target situation from multiple angles and spaces, and provide background information sharing capabilities through communication transmission components.

[0009] Furthermore, the wireless communication distance between the aircraft body and the controller is greater than 2 kilometers, so that the aircraft can be operated to effectively monitor targets within 2 kilometers. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a front lower main view schematic diagram of the present invention;

[0011] Figure 2 is a schematic diagram of a propeller viewed from above;

[0012] Figure 3 It is a top view schematic diagram of the proximal silicone structure and the distal silicone structure.

[0013] Marked in the figure are: aircraft body 100, propeller 200, transmission connection part 210, smooth connecting rod 211, first propeller blade 220, second propeller blade 230, silicone component 300, proximal silicone structure 310, first silicone part 311, second silicone part 312, distal silicone structure 320, third silicone component 321, fourth silicone component 322, fifth silicone component 323, tail 400, flash 500, camera 600, thermal imaging assembly 700. DETAILED DESCRIPTION

[0014] The invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0015] like Figure 1 A micro-aircraft is shown, comprising an aircraft body 100 and a controller for wireless communication control thereof, wherein a driving mechanism is arranged inside the aircraft body 100, and a propeller 200 and a tail wing 400 driven by the driving mechanism are arranged above and on the rear side of the aircraft body 100, respectively. The propeller 200 is a double-bladed single propeller, and the propeller blades of the propeller 200 are fluid double-sided twisted structures, and the tail wing 400 is a single-sided double-bladed propeller. Streamlined silicone components 300 for shock absorption and noise reduction are arranged at multiple locations on one side of the tail of the propeller blades of the propeller 200, the length of the propeller 200 is less than 125 mm, the total weight of the silicone component 300 is less than 0.008 grams, and the total weight of the aircraft body 100 is less than 32 grams. In this specific embodiment, the main shell structure of the aircraft body 100 is made of low-density and high-strength carbon fiber material, and its appearance conforms to the fluid design of the aircraft. The length of the propeller 200 is 118 mm, the total length of the aircraft is 156 mm, and the total weight of the aircraft body 100 is 31 grams. The overall mass is small, the power required for flight is lower, and the noise is lower; the streamlined silicone component structure at the tail end of the propeller blade can effectively relieve the airflow, and use the soft shock-absorbing characteristics of silicone to reduce wind noise when cutting the airflow; the propeller blades of the propeller 200 are fluid double-sided twisted structures that effectively enhance lift, and the arc-shaped structure design of the front section of the blade reduces the cutting airflow area and reduces wind resistance; it has a small size, low noise, and high concealment.

[0016] like Figure 1 and Figure 2As shown, the propeller 200 is centrally symmetrical and includes a transmission connection part 210 and a first propeller blade 220 and a second propeller blade 230 respectively fixed at both ends of the transmission connection part 210. The middle part of the transmission connection part 210 is connected to the driving mechanism and driven to rotate by the driving mechanism. In a specific implementation, the first propeller blade 220 and the second propeller blade 230 are fixed on both sides of the transmission connection part 210, and the entire propeller 200 is centrally symmetrical. The integrated blade structure of the propeller 200 makes the transmission more balanced, the control simpler, and there is no crosstalk between the blades.

[0017] like Figure 1 and Figure 2 As shown, the silicone component 300 includes two proximal silicone structures 310 and two distal silicone structures 320 which are symmetrically arranged on the propeller 200. The two proximal silicone structures 310 are respectively fixed at the connection between the two ends of the transmission connection part 210 and the first propeller blade 220 and the second propeller blade 230 and are respectively located on one side of the tail of the first propeller blade 220 and the second propeller blade 230. The two distal silicone structures 320 are respectively fixed on one end of the tail of the first propeller blade 220 and the second propeller blade 230 away from the transmission connection part 210. In a specific implementation, the weight of the proximal silicone structure 310 is greater than the weight of the distal silicone structure 320, and the external surface volume of the proximal silicone structure 310 is greater than the external surface volume of the distal silicone structure 320 (in this specific embodiment, the proximal silicone structure 310 and the distal silicone structure 320 are both solid streamlined structures, and the weight of the proximal silicone structure 310 is 0.002 grams). The two proximal silicone structures 310 and the two distal silicone structures 320 effectively relieve the airflow at the tail of the first propeller blade 220 and the second propeller blade 230, thereby reducing the vibration and noise of the entire propeller 200, with a simple structure and reasonable cost.

[0018] like Figure 2 and Figure 3As shown, the proximal silicone structure 310 includes an elliptical first silicone part 311 and a hemispherical second silicone part 312, one end of the circular cross-section of the second silicone part 312 is smoothly connected to the first silicone part 311, and the end of the first silicone part 311 away from the second silicone part 312 is smoothly connected to a smooth connecting rod 211 vertically and smoothly connected to the transmission connection part 210, and the distal silicone structure 320 includes a hemispherical third silicone part 321, a truncated cone-shaped fourth silicone part 322 and a hemispherical fifth silicone part 323, the outer diameter of the third silicone part 321 is smaller than the outer diameter of the fifth silicone part 323, and the fourth silicone part 322 is The diameters of the two ends are respectively the same as the diameters of the third silicone component 321 and the fifth silicone component 323 and are respectively connected to the circular cross-sections of the third silicone component 321 and the fifth silicone component 323 in a smooth manner. The middle parts of the third silicone component 321 and the fourth silicone component 322 included in the two distal silicone structures 320 are respectively fixed to the tails of the first propeller blade 220 and the second propeller blade 230 along the rotation direction of the propeller 200. The length of the first propeller blade 220 is 1.5 times the length of the transmission connection part 210. The distal silicone structure 320 is located at two-fifteenths of the side of the first propeller blade 220 away from the transmission connection part 210. In a specific implementation, when the propeller 200 rotates, when the airflow passes through the first propeller blade 220 and the second propeller blade 230, the streamlined and smooth outer surfaces of the proximal silicone structure 310 and the distal silicone structure 320 and the position distribution determined according to the test analysis effectively relieve the airflow, thereby reducing the vibration and noise of the propeller blades of the propeller 200.

[0019] On the basis of the above, if Figure 1 As shown, the front end of the aircraft body 100 is provided with a flash 500, a camera 600 and a thermal imaging component 700 which are wirelessly connected to a controller and controlled by the controller. The controller includes a display component and a communication transmission component for sharing information with an external platform.

[0020] In a specific implementation, the micro-aircraft can use a flash 500, a camera 600 and a thermal imaging component 700 to perform real-time observation and recording of photos and videos in conditions ranging from sufficient light to extremely weak light, and has daytime and nighttime reconnaissance capabilities, and can perform infrared reconnaissance on people, objects and mechanical equipment; a single person and a single machine can grasp the situation ahead in advance at a long distance, and has the ability to share and transmit videos and information in the background; in addition, multiple aircraft can be used to obtain information on the target situation from multiple angles and spaces, and at the same time provide background information sharing capabilities through communication transmission components.

[0021] On the basis of the above, if Figure 1As shown, the wireless communication distance between the aircraft body 100 and the controller is greater than 2 kilometers, so the aircraft can be operated to effectively monitor targets within 2 kilometers.

[0022] The specific embodiments described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific 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 principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A micro-aircraft, comprising an aircraft body (100) and a controller for wirelessly controlling the aircraft body, wherein a driving mechanism is arranged inside the aircraft body (100), and a propeller (200) and a tail wing (400) driven by the driving mechanism are arranged above and on the rear side of the aircraft body (100), respectively, wherein: The propeller (200) is a double-bladed single propeller, the propeller blades of the propeller (200) are fluid double-sided twisted structures, the tail wing (400) is a single-sided double-bladed propeller, and streamlined silicone components (300) for shock absorption and noise reduction are arranged at multiple locations on one side of the tail of the propeller blades of the propeller (200), the length of the propeller (200) is less than 125 millimeters, the total weight of the silicone components (300) is less than 0.008 grams, and the total weight of the aircraft body (100) is less than 32 grams; The propeller (200) is centrally symmetrical and comprises a transmission connection portion (210) and a first propeller blade (220) and a second propeller blade (230) respectively fixed at two ends of the transmission connection portion (210); a middle portion of the transmission connection portion (210) is connected to a driving mechanism and is driven to rotate by the driving mechanism; The silicone component (300) comprises two proximal silicone structures (310) and two distal silicone structures (320) which are centrally symmetrically arranged on the propeller (200); the two proximal silicone structures (310) are respectively fixed at the connection points between the two ends of the transmission connection part (210) and the first propeller blade (220) and the second propeller blade (230) and are respectively located on one side of the tail of the first propeller blade (220) and the second propeller blade (230); and the two distal silicone structures (320) are respectively fixed at one end of the tail of the first propeller blade (220) and the second propeller blade (230) away from the transmission connection part (210); The proximal silicone structure (310) comprises an elliptical first silicone portion (311) and a hemispherical second silicone portion (312); one end of the circular cross-section of the second silicone portion (312) is smoothly connected to the first silicone portion (311); one end of the first silicone portion (311) away from the second silicone portion (312) is smoothly connected to a smooth connecting rod (211) vertically and smoothly connected to the transmission connection portion (210); the distal silicone structure (320) comprises a hemispherical third silicone component (321), a truncated cone-shaped fourth silicone component (322) and a hemispherical fifth silicone component (323); the outer diameter of the third silicone component (321) is smaller than the outer diameter of the fifth silicone component (323); the fourth silicone component (322) has two outer diameters. The diameters of the ends are respectively the same as the diameters of the third silicone component (321) and the fifth silicone component (323), and are respectively connected to the circular cross-sections of the third silicone component (321) and the fifth silicone component (323) in a smooth manner. The middle parts of the third silicone component (321) and the fourth silicone component (322) included in the two distal silicone structures (320) are respectively fixed to the tails of the first propeller blade (220) and the second propeller blade (230) along the rotation direction of the propeller (200). The length of the first propeller blade (220) is 1.5 times the length of the transmission connection part (210). The distal silicone structure (320) is located at two-fifteenths of the first propeller blade (220) on the side away from the transmission connection part (210).

2. A micro aerial vehicle according to claim 1, characterized in that: The front end of the aircraft body (100) is provided with a flashlight (500), a camera (600) and a thermal imaging component (700) which are wirelessly connected to a controller and controlled by the controller, and the controller includes a display component and a communication transmission component for sharing information with an external platform.

3. A micro aerial vehicle according to claim 1, characterized in that: The wireless communication distance between the aircraft body (100) and the controller is greater than 2 kilometers.

Images