A three-wing unmanned aerial vehicle

Abstract

This utility model relates to the field of rotary-wing unmanned aerial vehicle (UAV) technology, specifically to a triplane UAV, which includes a frame and three radially distributed arms on the frame. A power unit is located at the end of each arm furthest from the frame. Landing gear is located at the bottom of the frame. A housing is fixed between the frame and the landing gear, situated between two adjacent arms. A battery is housed within the housing and electrically connected to the power unit. The rigid connection between the frame and landing gear via the housing enhances the overall structural strength. Simultaneously, the independent housing structure of the battery promotes a more balanced load distribution, effectively reducing the risk of deformation of the frame and landing gear under stress.

Description

Technical Field

[0001] This utility model relates to the field of rotary-wing unmanned aerial vehicle (UAV) technology, and in particular to a triplane UAV. Background Technology

[0002] In traditional drone architecture, the battery is typically built into the frame. While this simplifies the overall construction, it has significant technical drawbacks: First, because the battery pack directly occupies the core load-bearing area of ​​the frame, the mechanical structure of critical parts of the fuselage is weakened, making it prone to localized stress concentration under complex flight conditions, thus affecting the overall structural strength and impact resistance. Second, the method of fixing the built-in battery usually relies on rigid connectors. When the frame deforms due to manufacturing errors or external forces, it is difficult to achieve precise leveling of the flight platform through simple adjustments, severely restricting the drone's operational efficiency and flight stability. Utility Model Content

[0003] The purpose of this invention is to provide a triplane drone to solve the problem of poor structural strength in traditional drones with built-in batteries in the prior art.

[0004] The technical solution of this utility model is: a triplane unmanned aerial vehicle (UAV), comprising: a frame and three arms radially distributed on the frame, a power unit being provided at the end of each arm away from the frame, a landing gear being provided at the bottom of the frame, a housing being fixed between the frame and the landing gear, the housing being located between two adjacent arms, a battery being provided inside the housing, and the battery being electrically connected to the power unit.

[0005] Preferably, the frame includes an upper housing and a lower housing, a plurality of connecting blocks are fixedly disposed on the top of the lower housing, the upper housing is fixedly disposed on the top of the connecting blocks, and the machine arm is fixedly connected to the connecting blocks accordingly.

[0006] Preferably, the landing gear includes a first frame and a second frame. The first frame is fixedly provided with a first support rod, and the second frame is fixedly provided with a second support rod. The top of both the first support rod and the second support rod are horizontally fixedly provided with support plates. The bottom of the cabin is fixedly provided on the support plates, and the side of the cabin is fixedly connected to the upper shell.

[0007] Preferably, the three arms are located on the same horizontal plane, and the extension lines of the three arms intersect within the frame. Among the three included angles formed between the three arms, two included angles are the same and are greater than the third included angle. The arm shared by the two same included angles is the main shaft arm, and there are two hoppers located on both sides of the main shaft arm.

[0008] Preferably, the power assembly includes an electronic speed controller (ESC) and a propeller, with the ESC fixed to the arm and the propeller fixed to the output end of the ESC.

[0009] Preferably, each of the robotic arms is fixed with two sets of the power components, and the two sets of the power components are distributed in the vertical direction.

[0010] Preferably, the top of the compartment is open, the battery is inserted into the compartment from the top, and the surface of the compartment has several holes.

[0011] Preferably, both the first frame and the second frame are approximately trapezoidal structures, and the opposite sides of the first frame and the second frame are inclined.

[0012] Compared with the prior art, the advantages of this utility model are: The rigid connection between the frame and landing gear through the housing enhances the overall structural strength. Meanwhile, the independent housing structure of the battery makes the load distribution more balanced, effectively reducing the risk of stress deformation of the frame and landing gear. In addition, this layout moves the battery installation position down between the landing gear and the frame, which provides greater adjustment margin for the UAV leveling while ensuring structural compactness, significantly improving attitude stability and maintenance convenience during take-off and landing in complex terrain. Attached Figure Description

[0013] The present invention will be further described below with reference to the accompanying drawings and embodiments: Figure 1 This is a schematic diagram of the mechanism of a triplane unmanned aerial vehicle (UAV) according to the present invention; Figure 2 This is a cross-sectional structural diagram of a triplane unmanned aerial vehicle (UAV) according to the present invention; Figure 3 This is a schematic diagram of the structure of the silo body described in this utility model.

[0014] Explanation of reference numerals in the attached figures: 1. Frame; 11. Upper housing; 12. Lower housing; 13. Connecting block; 14. Controller; 2. Arm; 3. Power unit; 31. Electronic speed controller; 32. Propeller; 4. Landing gear; 41. First frame; 42. Second frame; 43. First support rod; 44. Second support rod; 45. Support plate; 5. Cabin; 6. Battery. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0016] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this utility model, and should not be construed as limiting this utility model.

[0017] In the description of this utility model, it should be understood that the terms "upper", "lower", "front", "rear", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0018] like Figures 1 to 3 As shown, a tri-rotor unmanned aerial vehicle (UAV) includes a frame 1 and three sets of radially distributed arms 2 on the frame 1. Power units 3 are located at the ends of the arms 2 furthest from the frame 1, forming the main structure of the tri-rotor UAV. Landing gear 4 is located at the bottom of the frame 1. A housing 5 is fixed between the frame 1 and the landing gear 4, situated between adjacent arms 2. A battery 6 is housed within the housing 5 and is electrically connected to the power units 3. The housing 5 serves not only as a functional compartment for the battery 6 but also as a structural component, connecting and reinforcing the frame 1 and the landing gear 4, significantly improving the UAV's vertical rigidity and bending resistance.

[0019] The frame 1 includes an upper housing 11 and a lower housing 12. A plurality of connecting blocks 13 are fixedly mounted on the top of the lower housing 12, distributed along its top edge. The upper housing 11 is fixedly mounted on top of the connecting blocks 13. Preferably, both the upper housing 11 and the lower housing 12 are made of carbon fiber sheet. In this embodiment, there are three connecting blocks 13, with the arm 2 fixedly connected to each block 13 in a one-to-one correspondence. The connecting blocks 13 have a hollow structure, and the cables of the power assembly 3 pass through the connecting blocks 13 and converge towards the center of the frame 1.

[0020] In this embodiment, the lower housing 12 is fixedly equipped with a controller 14, and the battery 6 and the power assembly 3 are both electrically connected to the controller 14. Preferably, the upper housing 11 has a clearance hole in the center, and the controller 14 extends out of the clearance hole to facilitate the operator to adjust the controller 14.

[0021] One end of arm 2 is fixed to connecting block 13, and power assembly 3 is fixed to the end of arm 2 away from connecting block 13. The three arms 2 are located on the same horizontal plane, and their extensions intersect within frame 1. In this embodiment, the three arms 2 form three included angles, two of which are the same and larger than the third. The arm 2 sharing the two identical included angles is the main shaft arm. Based on this structure, each of the two main shaft arms is provided with a housing 5, while the included angles away from the main shaft arm are left empty to precisely match the center of gravity, avoiding the need for additional counterweight for balancing, thereby optimizing flight performance and battery 6 range.

[0022] The power unit 3 includes an electronic speed controller (ESC) 31 and a propeller 32. The ESC 31 is fixed to the arm 2, and the propeller 32 is fixed to the output end of the ESC 31. The ESC 31 drives the propeller 32 to rotate. The cable of the ESC 31 is connected to the controller 14 through the hollow inner wall of the arm 2 and the connecting block 13. Preferably, each arm 2 is equipped with two sets of power units 3, which are distributed vertically. That is, the two propellers 32 rotate in parallel and opposite directions, and the counter-torque generated by one propeller 32 is canceled out by the counter-torque of the other propeller 32. For the asymmetrical layout of the tri-rotor UAV, efficient yaw control can be achieved simply by precisely adjusting the speed difference between the upper and lower propellers 32.

[0023] The landing gear 4 includes a first frame 41 and a second frame 42, which are respectively located on both sides of the frame 1 with the main shaft arm as the axis of symmetry. Both the first frame 41 and the second frame 42 are approximately trapezoidal structures, and are tilted towards opposite sides to provide stable support for the frame 1, improve the lateral stability of the UAV, and effectively prevent the UAV from tipping over when landing on sloping ground or when subjected to crosswinds.

[0024] The first frame 41 is fixedly equipped with a first support rod 43, and the second frame 42 is fixedly equipped with a second support rod 44. Both the first support rod 43 and the second support rod 44 are horizontally arranged. A support plate 45 is fixedly installed on the top of the first support rod 43 and the top of the second support rod 44. The support plate 45 is horizontally arranged and partially extends out of the first support rod 43 and the second support rod 44 to support the compartment 5. The bottom of one compartment 5 is fixed to the support plate 45 located at the top of the first support rod 43, and the side of this compartment 5 is fixedly connected to the upper shell 11. The bottom of the other compartment 5 is fixed to the support plate 45 located at the top of the second support rod 44, and the side of this compartment 5 is fixed to the side of the upper shell 11.

[0025] In this embodiment, the first support rod 43 and the second support rod 44, together with the support plate 45 on top, form a robust load-bearing tray. The bottoms of the two compartments 5 are directly fixed to the support plates 45 below them, thus obtaining vertical support from the landing gear 4. At the same time, the side of each compartment 5 is firmly connected to the side wall of the upper shell 11, which is the main structure of the fuselage, so that each compartment 5 is simultaneously supported from below and tensioned from the side, thus forming a highly torsional three-dimensional triangular box structure together with the upper shell 11 and the landing gear 4. The compartment 5 itself is thus transformed from a simple functional container into a core structural support component connecting the top of the fuselage and the bottom of the landing gear 4, greatly enhancing the rigidity and integrity of the entire aircraft.

[0026] Preferably, the top of the compartment 5 is open, allowing the battery 6 to be inserted into the compartment 5 from the top, enabling quick installation and replacement of the battery 6. Top operation provides better visibility and more hand space, making it more convenient and safer to explore the narrow bottom of the device compared to traditional battery compartments. Several holes are provided on the surface of the compartment 5 to minimize the amount of material used while ensuring structural strength.

[0027] The above embodiments are only for illustrating the technical concept and features of this utility model, and are intended to enable those skilled in the art to understand the content of this utility model and implement it accordingly. They should not be construed as limiting the scope of protection of this utility model. It is obvious to those skilled in the art that this utility model is not limited to the details of the above exemplary embodiments, and that it can be implemented in other specific forms without departing from the spirit or basic characteristics of this utility model. Therefore, the embodiments should be considered exemplary and non-limiting in all respects. The scope of this utility model is defined by the appended claims rather than the foregoing description, and therefore, all changes falling within the meaning and scope of the equivalents of the claims are intended to be included within this utility model.

Claims

1. A triplane unmanned aerial vehicle, characterized in that, include: A frame (1) and three radially distributed arms (2) on the frame (1). The ends of the arms (2) away from the frame (1) are provided with power units (3). The bottom of the frame (1) is provided with landing gear (4). A cabin (5) is fixed between the frame (1) and the landing gear (4). The cabin (5) is located between two adjacent arms (2). A battery (6) is provided inside the cabin (5). The battery (6) is electrically connected to the power unit (3).

2. A triplane unmanned aerial vehicle according to claim 1, characterized in that: The frame (1) includes an upper shell (11) and a lower shell (12). A plurality of connecting blocks (13) are fixedly provided on the top of the lower shell (12). The upper shell (11) is fixedly provided on the top of the connecting blocks (13). The arm (2) is fixedly connected to the connecting blocks (13).

3. A triplane unmanned aerial vehicle according to claim 2, characterized in that: The landing gear (4) includes a first frame (41) and a second frame (42). The first frame (41) is fixedly provided with a first support rod (43), and the second frame (42) is fixedly provided with a second support rod (44). The top of the first support rod (43) and the second support rod (44) are both horizontally fixedly provided with support plates (45). The bottom of the cabin (5) is fixedly provided on the support plate (45), and the side of the cabin (5) is fixedly connected to the upper shell (11).

4. A triplane unmanned aerial vehicle according to claim 3, characterized in that: The three arms (2) are located on the same horizontal plane, and the extension lines of the three arms intersect in the frame (1). Among the three included angles formed between the three arms (2), two included angles are the same and are greater than the third included angle. The arm (2) shared by the two same included angles is the main shaft arm. There are two hoppers (5) and they are located on both sides of the main shaft arm.

5. A triplane unmanned aerial vehicle according to claim 1, characterized in that: The power unit (3) includes an electronic speed controller (31) and a propeller (32). The electronic speed controller (31) is fixed on the arm (2), and the propeller (32) is fixed at the output end of the electronic speed controller (31).

6. A triplane unmanned aerial vehicle according to claim 5, characterized in that: Each of the arms (2) is fixed with two sets of the power components (3), which are distributed in the vertical direction.

7. A triplane unmanned aerial vehicle according to claim 1, characterized in that: The top opening of the compartment (5) allows the battery (6) to be inserted into the compartment (5) from the top, and the surface of the compartment (5) is provided with several holes.

8. A triplane unmanned aerial vehicle according to claim 3, characterized in that: Both the first frame (41) and the second frame (42) are approximately trapezoidal structures, and the two opposite sides of the first frame (41) and the second frame (42) are inclined.

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