A suicide drone

Abstract

The utility model discloses a kind of suicide unmanned aerial vehicle, including body, wing mechanism being arranged on the body, and power mechanism being arranged on the wing mechanism;Wing mechanism includes the front wing component and rear wing component of being respectively arranged around the front section and rear section of the body, and any one front wing component is aligned with one rear wing component along the axial direction of body;Power mechanism includes the power component of being arranged on the rear wing component, and the power component and the rear wing component equal in number;The axis of the power component is opposite the end of the front wing component away from body, and the body is also provided with heat dissipation channel.The utility model sets power mechanism on the leading edge of rear wing, and aligns the wing tip of front wing, effectively reduces the strongest wing tip vortex of front wing using propeller slipstream, and the semicircular wing tip design of front wing can effectively weaken the strength of wing tip vortex, which significantly reduces aerodynamic interference, improves overall flight efficiency and stability.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a suicide UAV. Background Technology

[0002] Suicide drones, also known as loitering munitions, are playing an increasingly important role in modern individual combat and small-scale conflicts. These drones require low cost, portability, ease of operation, and sufficient range and accuracy.

[0003] Existing suicide drones, especially high-end models, are prohibitively expensive, making large-scale deployment by individual soldiers difficult. Low-cost drones, in order to control costs, often compromise on aerodynamic design and heat dissipation. For example, most adopt a simple monoplane fixed-wing or quadcopter layout. To balance structural simplicity and long endurance, some designs employ front and rear wings (such as canards or tandem wings) to obtain a larger lift area.

[0004] However, this type of configuration has a significant drawback: the wake generated by the canard, especially the strong wingtip vortex, will directly impact the rear wing, severely disrupting the lifting surface flow field of the rear wing, resulting in a decrease in its aerodynamic efficiency and impaired flight stability. Utility Model Content

[0005] Based on this, the purpose of this utility model is to provide a suicide drone that aims to solve the problem that in the current layout of suicide drones, the wake generated by the forewing, especially the strong wingtip vortex, directly impacts the rear wing, seriously damaging the lifting surface flow field of the rear wing, resulting in a decrease in its aerodynamic efficiency and impaired flight stability.

[0006] To achieve the above objectives, this utility model is implemented through the following technical solution: a suicide drone, the suicide drone comprising a body, a wing mechanism disposed on the body, and a power mechanism disposed on the wing mechanism; The wing mechanism includes a plurality of forewing assemblies and a rearwing assemblies respectively surrounding the front and rear sections of the fuselage, wherein each forewing assembly is aligned with a rearwing assembly along the fuselage axis. The power mechanism includes several sets of power components disposed on the rear wing assembly, the number of power components being equal to the number of the rear wing assembly; The axis of the power unit is directly opposite the end of the forewing assembly away from the fuselage, and the fuselage is also provided with a heat dissipation channel.

[0007] According to one aspect of the above technical solution, a plurality of forewing assemblies surrounding the front section of the fuselage are arranged opposite each other in pairs. The forewing assembly includes a forewing on the fuselage and a wingtip at the end of the forewing away from the fuselage.

[0008] According to one aspect of the above technical solution, the wingtip is semi-circular, and the end of the wingtip away from the front wing is directly opposite the axis of the power assembly.

[0009] According to one aspect of the above technical solution, a plurality of rear wing assemblies surrounding the rear section of the fuselage are arranged opposite each other in pairs. The rear wing assembly includes a rear wing and a control surface located on the rear wing at the end away from the front wing.

[0010] According to one aspect of the above technical solution, the power assembly includes a motor mounted on the rear wing, and a propeller is mounted on the motor shaft of the motor, with the axis of the propeller facing the edge of the wingtip.

[0011] According to one aspect of the above technical solution, the heat dissipation channel includes a plurality of first air inlets and a plurality of second air inlets respectively located in the front and middle sections of the body, and a plurality of air outlets located in the rear section of the body, wherein the plurality of air inlets and the plurality of air outlets are arranged opposite each other with the body as the axis.

[0012] According to one aspect of the above technical solution, cameras are also installed between the symmetrically arranged first air inlets.

[0013] In summary, this invention provides a suicide drone. By placing the power mechanism on the leading edge of the rear wing and aligning it with the wingtip of the front wing, the propeller slipstream effectively reduces the strongest wingtip vortex on the front wing. Simultaneously, the semi-circular wingtip design of the front wing effectively weakens the intensity of the wingtip vortex. This structural combination significantly reduces aerodynamic interference and improves overall flight efficiency and stability. Utilizing ram air during flight, cool air is drawn in from the nose air intake and the embedded air intake in the mid-fuselage, flows through the electronic equipment bay in the mid-fuselage, and is finally exhausted from the tail exhaust, creating a highly efficient "through-draft" effect. This design eliminates the need for additional fans or other active cooling components, achieving zero-cost, zero-weight, and highly efficient heat dissipation. This prevents overheating and burnout of components due to excessively high temperatures inside the equipment bay, thus avoiding drone crashes.

[0014] Additional aspects and advantages of this invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of a suicide drone in one embodiment of the present invention; Figure 2 This is a side view of a suicide drone in one embodiment of the present invention; Figure 3 This is a front view of a suicide drone in one embodiment of the present invention; Figure 4This is a rear view of a suicide drone in one embodiment of the present invention.

[0016] Component symbol explanation in the attached diagram: 1-Airframe, 2-Camera, 3-Forward wing, 31-Wingtip, 4-Rear wing, 41-Control surfaces, 5-Power unit, 51-Electric motor, 52-Propeller, 6-First air inlet, 7-Second air inlet, 8-Air outlet. Detailed Implementation

[0017] To make the objectives, features, and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model are described in detail below with reference to the accompanying drawings. Several embodiments of this utility model are shown in the drawings. However, this utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to make the disclosure of this utility model more thorough and complete.

[0018] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected" to another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," "upper," "lower," and similar expressions used herein are for illustrative purposes only and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

[0019] In this utility model, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances. The term "and / or" as used herein includes any and all combinations of one or more of the related listed items.

[0020] Please see Figures 1-4 The diagram shows a structural schematic of a suicide drone according to an embodiment of the present invention. The suicide drone includes a body 1, a wing mechanism disposed on the body 1, and a power mechanism disposed on the wing mechanism, wherein: In this embodiment, the fuselage 1 is the core load-bearing structure, which adopts a cylindrical design and is divided into three parts: front section, middle section and rear section. The top of the front section is used to install the camera 2 for reconnaissance, target identification and strike guidance. The middle section of the fuselage 1 is responsible for accommodating the warhead, airborne battery, flight control board, electronic speed controller and servo motors. The rear section and middle section of the fuselage 1 are provided with separation surfaces to facilitate the installation of equipment when they are separated.

[0021] Furthermore, the wing mechanism includes a plurality of forewing assemblies and a rearwing assemblies respectively surrounding the front and rear sections of the fuselage 1. Each forewing assembly is aligned with a rearwing assembly along the axial direction of the fuselage 1. This embodiment uses four forewing assemblies and four rearwing assemblies as an example for illustration. The four forewing assemblies and four rearwing assemblies are respectively arranged in pairs opposite to each other on the front and rear sections of the fuselage 1, and one forewing assembly and one rearwing assembly are aligned along the axial direction of the fuselage 1.

[0022] Furthermore, the forewing assembly includes a forewing 3 mounted on the fuselage 1 and wingtips 31 located at the end of the forewing 3 furthest from the fuselage 1. The four forewings 3 adopt a symmetrical airfoil design with a sweep angle, divided into two pairs, and are fixedly connected to the mid-front section of the fuselage. The tips of all four wingtips adopt a semi-circular wingtip design to reduce vortex intensity at the wingtips 31. The rear wing assembly includes a rear wing 4 and control surfaces 41 located at the end of the rear wing 4 furthest from the forewing 3. The four rear wing assemblies adopt a symmetrical airfoil design with a sweep angle and control surfaces 41, divided into two pairs, and are fixedly connected to the mid-rear section of the fuselage. Each rear wing 4 has a power unit 5 at its leading edge and a control surface 41 at its trailing edge for controlling the UAV's flight attitude. Specifically, the wings in this embodiment can adopt symmetrical airfoils such as NACA0012, with a sweep angle of 8-10 degrees, and are made of carbon fiber composite material.

[0023] The power assembly 5 includes a motor 51 mounted on the rear wing 4, and a propeller 52 mounted on the motor shaft of the motor 51, with the axis of the propeller 52 directly opposite the edge of the wingtip 31. The power assembly 5 is located at the intersection of the extended line of the wingtip 31 and the leading edge of the rear wing 4, with the end of the wingtip 31 furthest from the forewing 3 directly opposite the axis of the power assembly 5, forming a forward-pull power layout. The slipstream effect of the propeller 52 reduces the aerodynamic interference of the forewing 3 on the rear wing 4.

[0024] The heat dissipation channel includes several first air inlets 6 and several second air inlets 7 respectively located at the front and middle sections of the fuselage 1, and several air outlets 8 located at the rear section of the fuselage 1. The air inlets and outlets 8 are arranged in pairs relative to each other with the fuselage 1 as an axis. The first air inlets 6 can be rectangular strip-shaped air inlets, the second air inlets 7 can be triangular embedded air ducts located on the left and right sides of the middle section of the fuselage 1, and the air outlets 8 can be four runway-shaped air outlets symmetrically located at the top, bottom, left, and right of the rear section of the fuselage. The first air inlets 6, second air inlets 7, and air outlets 8 together form a heat dissipation channel penetrating the fuselage, ensuring that the UAV can smoothly draw air into the fuselage during flight and effectively expel hot air from the fuselage, significantly improving heat dissipation efficiency. Preferably, the long axes of the first air inlets 6, second air inlets 7, and air outlets 8 are parallel to the fuselage axis, which helps reduce aerodynamic drag during flight. During flight, the external cooling airflow enters the fuselage through the first air inlet 6, which is symmetrically located at the front of the fuselage 1, and the second air inlet 7, which is symmetrically located at the middle of the fuselage 1 and parallel to the fuselage axis. The airflow flows to the heat-generating areas such as the battery, ESC, and flight control board. After heat exchange, the airflow is discharged to the surrounding areas from the air outlet 8, which is symmetrically located at the rear of the fuselage, completing the heat dissipation cycle.

[0025] In practical applications, a single soldier can carry / deploy this drone and control its flight through a ground terminal or a preset program; Camera 2 is responsible for capturing images in real time and guiding the drone to the target area in combination with the control rate algorithm; The heat dissipation structure and aerodynamic layout work together to ensure that the drone has stable performance and reliable endurance during reconnaissance and strike operations.

[0026] In summary, this invention provides a suicide drone. By placing the power mechanism on the leading edge of the rear wing and aligning it with the wingtip of the front wing, the propeller slipstream effectively reduces the strongest wingtip vortex on the front wing. Simultaneously, the semi-circular wingtip design of the front wing effectively weakens the intensity of the wingtip vortex. This structural combination significantly reduces aerodynamic interference and improves overall flight efficiency and stability. Utilizing ram air during flight, cool air is drawn in from the nose air intake and the embedded air intake in the mid-fuselage, flowing through the electronic equipment bay in the mid-fuselage and finally exiting from the tail exhaust, creating a highly efficient "through-draft" effect. This design eliminates the need for additional fans or other active cooling components, achieving zero-cost, zero-weight, and highly efficient heat dissipation. It avoids overheating and component burnout caused by excessively high temperatures inside the equipment bay, preventing drone crashes. The overall structure of this invention features a simple cylindrical fuselage and symmetrical wing surfaces, facilitating mass production and assembly. Its compact design allows for easy assembly, carrying, and rapid deployment by individual soldiers, making it ideal for the modern battlefield's demand for low-cost, high-efficiency equipment.

[0027] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0028] The above-described embodiments are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of this utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A suicide drone, characterized in that, The suicide drone includes a body, a wing mechanism on the body, and a power mechanism on the wing mechanism; The wing mechanism includes a plurality of forewing assemblies and a rearwing assemblies respectively surrounding the front and rear sections of the fuselage, wherein each forewing assembly is aligned with a rearwing assembly along the fuselage axis. The power mechanism includes several sets of power components disposed on the rear wing assembly, the number of power components being equal to the number of the rear wing assembly; The axis of the power unit is directly opposite the end of the forewing assembly away from the fuselage, and the fuselage is also provided with a heat dissipation channel.

2. The suicide drone according to claim 1, characterized in that, Several forewing assemblies are arranged in pairs facing each other around the front section of the fuselage. Each forewing assembly includes a forewing on the fuselage and a wingtip at the end of the forewing away from the fuselage.

3. The suicide drone according to claim 2, characterized in that, The wingtip is semi-circular, and the end of the wingtip away from the forewing is directly opposite the axis of the power unit.

4. The suicide drone according to claim 1, characterized in that, Several rear wing assemblies surrounding the rear section of the fuselage are arranged in pairs facing each other. Each rear wing assembly includes a rear wing and a control surface located on the rear wing at the end away from the front wing.

5. The suicide drone according to claim 1, characterized in that, The power unit includes a motor mounted on the rear wing, with a propeller mounted on the motor shaft, the axis of the propeller being directly opposite the wingtip edge.

6. The suicide drone according to claim 1, characterized in that, The heat dissipation channel includes a plurality of first air inlets and a plurality of second air inlets respectively located at the front and middle sections of the body, and a plurality of air outlets located at the rear section of the body. The plurality of air inlets and the plurality of air outlets are arranged in pairs relative to each other with the body as the axis.

7. The suicide drone according to claim 6, characterized in that, A camera is also installed between the symmetrically arranged first air inlets.

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