Low-noise composite wing unmanned aerial vehicle for complex terrain inspection

Abstract

The utility model discloses a low noise composite wing unmanned plane for complex topography inspection relates to unmanned plane technical field, this low noise composite wing unmanned plane for complex topography inspection, including fuselage, fuselage adopts aviation carbon fiber composite material, has streamline aerodynamic shape, and the both sides of fuselage integrative forming has the wing, and the downside fixed setting of wing has support rod, and the tail end fixed setting of support rod has tail wing, and the both ends of support rod and the rear end of fuselage all integrated installation have the noise reduction power mechanism. The utility model discloses through the sound absorption honeycomb layer of the outside skin of fuselage inside laying, through its special material combination effectively reduced the noise propagation, secondly, the tip portion of paddle is provided with a plurality of microperforation, these microperforation help to disperse airflow, reduce the noise caused by air turbulence, in addition, the motor seat is connected between the fuselage through the damping pad, can absorb the vibration produced when brushless motor works, thereby further reduced the operating noise.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a low-noise compound wing UAV for inspection of complex terrain. Background Technology

[0002] With the continuous development of drone technology, its application in complex terrain environments such as power line inspection, geological exploration, and emergency rescue is becoming increasingly widespread. However, traditional drones still have many shortcomings in terms of structural design and noise control. On the one hand, conventional take-off and landing mechanisms mostly use fixed supports or simple shock absorption devices, which can easily cause the fuselage to tilt or be damaged when taking off and landing on rough ground, affecting flight safety and operational efficiency. On the other hand, the power system operation and aerodynamic noise are relatively large, limiting their ability to perform covert missions in urban or residential areas.

[0003] In addition, existing drones use relatively limited sound-absorbing and noise-reducing materials and have limited means of controlling propeller aerodynamic noise, making it difficult to achieve good low-noise performance. Utility Model Content

[0004] This utility model provides a low-noise composite wing UAV for inspection of complex terrain, including a fuselage made of aerospace carbon fiber composite material with a streamlined aerodynamic shape. The fuselage has wings integrally formed on both sides, and a support rod is fixedly installed on the lower side of the wing. A tail fin is fixedly installed at the tail end of the support rod. Noise reduction power mechanism is integrated at both ends of the support rod and the rear end of the fuselage. An adaptive take-off and landing mechanism is installed at the bottom of the fuselage, and an inspection module is installed on the belly of the fuselage.

[0005] Preferably, the noise reduction power mechanism includes a motor base, which is fixed to the machine body. A brushless motor is installed inside the motor base, and the output shaft of the brushless motor is connected to the blades. Heat dissipation fins are distributed on the outer side of the motor base.

[0006] Preferably, the motor mount is connected to the motor body via a damping pad.

[0007] Preferably, the blade tip has several micro-perforations.

[0008] Preferably, the inspection module includes a gimbal that is bolted to the bottom of the machine body, and an infrared thermal imager and a camera are mounted on the gimbal.

[0009] Preferably, a plurality of ultrasonic obstacle avoidance sensors are arranged in a ring on the outer skin surface of the fuselage, and the probes of the ultrasonic obstacle avoidance sensors are exposed and flush with the skin.

[0010] Preferably, the infrared thermal imager and camera are electrically connected to the flight control system integrated inside the fuselage via a data cable, and form a linkage mechanism with the ultrasonic obstacle avoidance sensor. When the ultrasonic obstacle avoidance sensor detects an obstacle in front, the flight control system automatically adjusts the gimbal angle so that the infrared thermal imager and camera are aimed at the obstacle for real-time image acquisition.

[0011] Preferably, a sound-absorbing honeycomb layer is laid inside the outer skin of the fuselage.

[0012] Preferably, the adaptive landing mechanism includes a hydraulic cylinder connected to the fuselage, the piston end of the hydraulic cylinder being connected to the middle of the bottom rod, buffer assemblies being provided on both sides of the hydraulic cylinder, one end of the buffer assembly being hinged to one end of the second connecting rod, the other end of the second connecting rod being hinged to the first fork, the lower end of the first fork being hinged to one end of the second fork, the other end of the second fork being rotatably connected to the middle of the bottom rod, and a transition rod being hinged to one end of the hydraulic cylinder, the lower end of the transition rod being hinged to the upper end of the bottom rod, and a roller being installed at the lower end of the bottom rod.

[0013] Preferably, the buffer assembly includes a hollow sleeve fixed to the outside of the hydraulic cylinder, a damper is installed inside the hollow sleeve, one end of the damper is movably connected to one end of connecting rod one, and the other end of connecting rod one is hinged to the other end of connecting rod two.

[0014] This utility model provides a low-noise compound-wing UAV for inspecting complex terrain, which, compared with the prior art:

[0015] 1. This utility model effectively reduces noise transmission through the sound-absorbing honeycomb layer applied inside the outer skin of the fuselage, using its special material combination. Secondly, several micro-perforations are opened at the tip of the propeller blades, which help to disperse airflow and reduce noise caused by air turbulence. In addition, the motor mount is connected to the fuselage through a damping pad, which can absorb the vibration generated when the brushless motor is working, thereby further reducing operating noise, improving the stealth of the UAV when performing missions, and reducing the impact on the surrounding environment.

[0016] 2. This utility model connects the hydraulic cylinder to the middle of the bottom rod, and the roller is installed at the lower end of the bottom rod. It makes priority contact with the ground during landing, adapting to uneven terrain. The damper in the buffer assembly gradually absorbs the impact force through the structure of connecting rod one, connecting rod two and fork rod, effectively reducing the transmission of vibration to the fuselage. The transition rod connects the hydraulic cylinder and the bottom rod, and the uniform distribution of auxiliary force improves the stability during take-off and landing. The above structures work together to improve the adaptability and operational safety of the UAV in complex terrain. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of one embodiment of the present utility model;

[0019] Figure 2 This is a second schematic diagram of the overall structure of an embodiment of the present utility model;

[0020] Figure 3 This is a schematic diagram showing the disassembled structure of the noise reduction power mechanism according to an embodiment of the present utility model;

[0021] Figure 4 This is a partial schematic diagram of the blade structure according to an embodiment of the present utility model;

[0022] Figure 5 This is a schematic diagram of the sound-absorbing honeycomb layer structure according to an embodiment of the present invention;

[0023] Figure 6 This is a schematic diagram of the adaptive lifting mechanism structure according to an embodiment of the present utility model;

[0024] Figure 7 This is a schematic diagram of the connecting rod secondary structure in an embodiment of the present utility model;

[0025] Figure 8 This is a cross-sectional view of the buffer component structure according to an embodiment of the present invention.

[0026] Figure label:

[0027] 1. Fuselage; 11. Ultrasonic obstacle avoidance sensor; 12. Sound-absorbing honeycomb layer; 2. Wing; 3. Noise-reducing power mechanism; 31. Motor mount; 32. Heat dissipation fins; 33. Damping pad; 34. Brushless motor; 35. Propeller blade; 36. Micro-perforation; 4. Support rod; 5. Tail fin; 6. Adaptive landing mechanism; 61. Hydraulic cylinder; 62. Hollow sleeve; 621. Damper; 63. Link 1; 64. Link 2; 65. Fork 1; 66. Fork 2; 67. Bottom rod; 68. Transition rod; 69. Roller; 7. Gimbal; 8. Infrared thermal imager; 9. Camera. Detailed Implementation

[0028] The following detailed description, in conjunction with the accompanying drawings, outlines some embodiments of the present invention. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0029] Please refer to Figures 1-8 This utility model provides a low-noise composite wing UAV for inspection of complex terrain, including a fuselage 1. The fuselage 1 is made of aerospace carbon fiber composite material, which has good strength and lightweight characteristics. The overall streamlined aerodynamic shape design reduces flight drag and optimizes aerodynamic performance.

[0030] On both sides of the fuselage 1, there are integrally formed wings 2, which are used to provide the lift required for fixed-wing flight. A support rod 4 is fixedly installed on the lower side of the wing 2. The end of the support rod 4 is fixedly connected to the tail fin 5, forming a complete tail stabilization structure. Noise reduction power mechanism 3 is integrated and installed at both ends of the support rod 4 and the rear end of the fuselage 1, which is used to drive the drone to fly.

[0031] The noise reduction power mechanism 3 includes a motor mount 31, which is fixed to the fuselage 1 by a damping pad 33. High-strength bolts are used to pass through the damping pad 33 and the mounting holes on the motor mount 31 and tighten them into the corresponding holes on the fuselage 1 to effectively isolate the transmission of noise caused by motor vibration. A brushless motor 34 is installed inside the motor mount 31, and its output shaft is connected to the propeller blade 35 to provide flight power. Several micro-perforations 36 are opened at the tip of the propeller blade 35, preferably with a size of 0.5 to 1.2 mm, to weaken airflow disturbance and thus reduce aerodynamic noise. Heat dissipation fins 32 are provided on the outside of the motor mount 31 to enhance the heat dissipation efficiency of the motor during operation.

[0032] To further enhance the noise reduction effect, the inner layer of the outer skin of the fuselage 1 is covered with a sound-absorbing honeycomb layer 12. The sound-absorbing honeycomb layer 12 is composed of multiple layers of composite materials, which can effectively absorb the environmental noise generated during flight and improve the low noise performance of the whole aircraft.

[0033] The bottom of the fuselage 1 is equipped with an adaptive take-off and landing mechanism 6, which is used to ensure stable take-off and landing of the UAV in complex terrain, such as... Figures 6 to 8 As shown, the adaptable landing mechanism 6 includes a hydraulic cylinder 61. One end of the hydraulic cylinder 61 is connected to the fuselage 1, and the piston rod at the other end is movably connected to the middle of the bottom rod 67. A roller 69 is installed at the lower end of the bottom rod 67, which can contact the ground before other components and adapt to uneven terrain.

[0034] The hydraulic cylinder 61 is equipped with buffer components on both sides. The buffer components include a hollow sleeve 62, in which a damper 621 is installed. One end of the damper 621 is hinged to a connecting rod 64 via a connecting rod 63. The connecting rod 64 is then hinged to a fork 65 and a fork 66 in sequence, and finally forms a linkage structure with the bottom rod 67. This structure can absorb and disperse the landing impact force step by step, reducing the direct impact on the fuselage 1.

[0035] In addition, the hydraulic cylinder 61 is hinged to the bottom rod 67 via the transition rod 68, which further assists in the even distribution of force and improves stability during the lifting and lowering process.

[0036] An inspection module is installed on the underside of the fuselage 1 to perform inspection tasks such as power lines and geological features. The inspection module includes a gimbal 7 that is detachably mounted on the bottom of the fuselage 1 by bolts. An infrared thermal imager 8 and a camera 9 are integrated on the gimbal 7, which can be used for all-weather image acquisition and temperature detection.

[0037] The infrared thermal imager 8 and camera 9 are electrically connected to the flight control system integrated inside the fuselage 1 via a data cable, and form a linkage mechanism with multiple ultrasonic obstacle avoidance sensors 11 arranged in a ring on the outside of the fuselage 1. When the ultrasonic obstacle avoidance sensor 11 detects an obstacle in front, the flight control system automatically adjusts the angle of the gimbal 7 so that the infrared thermal imager 8 and camera 9 are aimed at the obstacle for real-time image acquisition and analysis, and can transmit the data to the ground control terminal through the wireless communication module to realize autonomous identification and remote inspection functions.

[0038] In summary, the working principle of the low-noise composite wing UAV for complex terrain inspection according to this utility model embodiment is as follows: When performing inspection tasks, the propeller blades 35 are first driven by the noise reduction power mechanism 3 to generate flight power. The fuselage 1 adopts carbon fiber material and streamlined design, combined with sound-absorbing honeycomb layer 12 and micro-perforated structure 36 to effectively reduce flight noise. The adaptive take-off and landing mechanism 6 works in concert with hydraulic cylinder 61, buffer component and roller 69 to enable the UAV to take off and land stably in complex terrain. During flight, ultrasonic obstacle avoidance sensor 11 detects obstacles in real time and links with flight control system to automatically adjust the angle of gimbal 7, control infrared thermal imager 8 and camera 9 to collect and transmit images of the target, realize intelligent and remote inspection operation.

[0039] The above are merely preferred embodiments of this utility model and are not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A low-noise compound-wing unmanned aerial vehicle (UAV) for inspection of complex terrain, characterized in that: The fuselage (1) is made of aerospace carbon fiber composite material and has a streamlined aerodynamic shape. The fuselage (1) has wings (2) integrally formed on both sides. A support rod (4) is fixedly installed on the lower side of the wing (2). A tail fin (5) is fixedly installed at the tail end of the support rod (4). Noise reduction power mechanism (3) is integrated at both ends of the support rod (4) and the rear end of the fuselage (1). An adaptive take-off and landing mechanism (6) is installed at the bottom of the fuselage (1). An inspection module is installed on the belly of the fuselage (1).

2. The low-noise compound-wing UAV for complex terrain inspection according to claim 1, characterized in that: The noise reduction power mechanism (3) includes a motor base (31), which is fixed on the fuselage (1). A brushless motor (34) is installed inside the motor base (31). The output shaft of the brushless motor (34) is connected to the blade (35). Heat dissipation fins (32) are distributed on the outer side of the motor base (31).

3. The low-noise compound-wing UAV for complex terrain inspection according to claim 2, characterized in that: The motor mount (31) is connected to the body (1) via a damping pad (33).

4. The low-noise compound-wing UAV for complex terrain inspection according to claim 3, characterized in that: The blade (35) has several micro-perforations (36) at its tip.

5. The low-noise compound-wing UAV for complex terrain inspection according to claim 1, characterized in that: The inspection module includes a gimbal (7) that is bolted to the bottom of the fuselage (1), and an infrared thermal imager (8) and a camera (9) are mounted on the gimbal (7).

6. The low-noise compound-wing UAV for complex terrain inspection according to claim 5, characterized in that: Several ultrasonic obstacle avoidance sensors (11) are arranged in a ring on the outer skin surface of the fuselage (1). The probes of the ultrasonic obstacle avoidance sensors (11) are exposed and flush with the skin.

7. The low-noise compound-wing UAV for complex terrain inspection according to claim 6, characterized in that: The infrared thermal imager (8) and camera (9) are electrically connected to the flight control system integrated inside the fuselage (1) via a data cable, and form a linkage mechanism with the ultrasonic obstacle avoidance sensor (11). When the ultrasonic obstacle avoidance sensor (11) detects an obstacle in front, the flight control system automatically adjusts the angle of the gimbal (7) so that the infrared thermal imager (8) and camera (9) are aimed at the obstacle for real-time image acquisition.

8. The low-noise compound-wing UAV for complex terrain inspection according to claim 1, characterized in that: The outer skin of the fuselage (1) is lined with a sound-absorbing honeycomb layer (12).

9. The low-noise compound-wing UAV for complex terrain inspection according to claim 1, characterized in that: The adaptive landing mechanism (6) includes a hydraulic cylinder (61) connected to the fuselage (1). The piston end of the hydraulic cylinder (61) is connected to the middle of the bottom rod (67). Buffer components are provided on both sides of the hydraulic cylinder (61). One end of the buffer component is hinged to one end of the connecting rod (64). The other end of the connecting rod (64) is hinged to the fork (65). The lower end of the fork (65) is hinged to one end of the fork (66). The other end of the fork (66) is rotatably connected to the middle of the bottom rod (67). A transition rod (68) is hinged to one end of the hydraulic cylinder (61). The lower end of the transition rod (68) is hinged to the upper end of the bottom rod (67). A roller (69) is installed at the lower end of the bottom rod (67).

10. The low-noise compound-wing UAV for complex terrain inspection according to claim 9, characterized in that: The buffer assembly includes a hollow sleeve (62) fixed to the outside of the hydraulic cylinder (61). A damper (621) is installed inside the hollow sleeve (62). One end of the damper (621) is movably connected to one end of the first connecting rod (63), and the other end of the first connecting rod (63) is hinged to the other end of the second connecting rod (64).

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