A vertical take-off and landing aircraft for air racing

Abstract

The utility model provides a vertical take -off and landing aircraft for aerial racing, including aircraft body, set up in the NACA air intake heat dissipation channel subassembly of aircraft body, set up in the battery box of aircraft body, NACA air intake heat dissipation channel subassembly includes the air inlet channel body of Y shape, is equipped with two air inlets in the front end of air inlet channel body, its rear end is equipped with the air outlet, and the battery box is linked together with air inlet channel body, through design Y's NACA air intake heat dissipation channel, be used for the high -speed airflow high -efficiently import the fuselage inside, and this air duct directly guides the airflow to blow to the battery box surface in the middle part of fuselage, thereby greatly improved the heat dissipation effect of high -power battery pack, thereby avoids the battery efficiency attenuation, guarantees the limit performance of aircraft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft, and more specifically, to a vertical take-off and landing aircraft for aerial racing. Background Technology

[0002] With the development of electric vertical takeoff and landing (eVTOL) technology, aerial racing is becoming an emerging extreme sport. Existing multi-rotor aircraft or simply modified VTOL aircraft used for racing generally suffer from thermal management bottlenecks. Racing aircraft typically use high-power battery packs, which generate a significant amount of heat during racing. Conventional cooling duct designs are often crude, resulting in high drag and low heat dissipation efficiency, leading to battery performance degradation and even thermal runaway, thus limiting the aircraft's maximum performance output.

[0003] Therefore, it is necessary to improve existing vertical takeoff and landing aircraft used for air racing to overcome the aforementioned shortcomings. Utility Model Content

[0004] The main objective of this application is to provide a vertical takeoff and landing aircraft for aerial racing with good battery pack heat dissipation.

[0005] To achieve the above objectives, in a first aspect, this application provides a vertical takeoff and landing aircraft for aerial racing, including an aircraft body, a NACA air intake and heat dissipation channel assembly disposed within the aircraft body, and a battery box disposed within the aircraft body. The NACA air intake and heat dissipation channel assembly includes a Y-shaped air intake channel body, with two air inlets at the front end and an air outlet at the rear end. The battery box is connected to the air intake channel body.

[0006] Optionally, the air inlet adopts a lip design.

[0007] Optionally, an air intake fan is provided at the air outlet.

[0008] Optionally, the air inlet channel is provided with a plurality of heat dissipation holes, which are connected to the battery box.

[0009] Optionally, a heat dissipation grille is also provided between the air intake channel and the battery box.

[0010] Optionally, the NACA air intake cooling channel assembly is embedded in the aircraft body.

[0011] Optionally, the aircraft body is wing-shaped.

[0012] Optionally, propeller assemblies are provided on both the front and rear sides of the aircraft body.

[0013] Optionally, an integrally formed T-shaped roll cage is provided above and behind the cockpit of the aircraft body.

[0014] Optionally, the two air inlets are symmetrically arranged on both sides of the aircraft body.

[0015] This utility model provides a vertical takeoff and landing aircraft for aerial racing. Compared with the prior art, its advantages are as follows: by designing a Y-shaped NACA air intake and heat dissipation channel, high-speed airflow is efficiently introduced into the fuselage. This air duct directly guides the airflow to the surface of the battery box located in the middle of the fuselage, thereby greatly improving the heat dissipation effect of the high-power battery pack, thus avoiding battery efficiency degradation and ensuring the extreme performance of the aircraft. Attached Figure Description

[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of the application and to make other features, objects, and advantages of the application more apparent. The illustrative embodiments and descriptions of this application are used to explain the application and do not constitute an undue limitation of the application. In the drawings: Figure 1 This is a schematic diagram of the present invention; Figure 2 This is a diagram of the NACA intake cooling channel. Figure 1 ; Figure 3 This is a diagram of the NACA intake cooling channel. Figure 2 .

[0017] The components include: 1. Aircraft body; 2. Propeller assembly; 3. T-shaped roll cage; 4. Air intake duct body; 5. Battery box; 6. Air inlet; 7. Air outlet; 8. Heat dissipation grille; 9. Intake fan. Detailed Implementation

[0018] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0019] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0020] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0021] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0022] In addition, the term "multiple" should mean two or more.

[0023] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0024] like Figures 1-3 As shown, a vertical takeoff and landing (VTOL) aircraft for aerial racing includes an aircraft body 1, a NACA (Aircraft Carrier Air Circulation) intake and cooling channel assembly disposed within the aircraft body 1, and a battery box 5 disposed within the aircraft body 1. The NACA intake and cooling channel assembly includes a Y-shaped air intake channel body 4, with two air inlets 6 at the front end and an air outlet 7 at the rear end. The battery box 5 is connected to the air intake channel body 4. Preferably, the two air inlets 6 are symmetrically arranged on both sides of the aircraft body 1. By symmetrically arranging the two air inlets 6, the high-speed airflow introduced into the fuselage is more balanced, thereby ensuring the heat dissipation effect.

[0025] To reduce resistance when guiding high-speed airflow, the air inlet 6 adopts a lip design. This lip design refers to designing the edge of the air inlet 6 as a smooth, streamlined arc or tapering lip structure, rather than a right-angled, acute-angled, or rough right-angled edge. This optimizes the edge morphology of the air inlet 6 through hydrodynamics, allowing airflow to enter the equipment more smoothly. Common lip cross-sectional shapes include circular arc, elliptical arc, and a combination of expanding and contracting shapes. If the air inlet 6 has a right-angled edge, the airflow will experience boundary layer separation due to the sudden turn at the edge, forming numerous disordered vortices on the inside or outside of the inlet. These vortices consume the kinetic energy of the airflow, resulting in energy loss and increased wind resistance. The streamlined arc structure of the lip guides the airflow smoothly along the lip edge, gradually changing direction, preventing sudden separation of the airflow from the inlet wall, significantly suppressing vortex generation, and thus reducing wind resistance caused by vortices.

[0026] In order to better draw airflow into the air duct, an air intake fan 9 is installed at the air outlet 7.

[0027] To ensure uniform heat dissipation of the battery box 5, a number of heat dissipation holes are provided on the air inlet channel, and the heat dissipation holes are connected to the battery box 5. A heat dissipation grille 8 is also provided between the air inlet channel and the battery box 5.

[0028] To reduce the aircraft's drag, the NACA air intake cooling channel assembly is embedded in the aircraft body 1. This embedded design ensures that the NACA air intake maximizes heat dissipation for the battery pack while minimizing air resistance. This ensures that the battery can maintain its optimal operating temperature range even under continuous high power output, avoiding power limitations or safety risks caused by overheating, and improving the reliability and performance limits of the aircraft.

[0029] To reduce induced drag and exhaust drag, and significantly improve acceleration, top speed, and energy efficiency, the aircraft body 1 is airfoil-shaped. This airfoil composite fuselage combines functionality and aerodynamics, providing structural volume while simultaneously becoming a lifting body. Compared to conventional aircraft fuselages with simple rod or cylindrical structures, which generate significant parasitic drag during high-speed forward flight, severely impacting racing performance and endurance, the fuselage's cross-section is airfoil-shaped, similar to the streamlined profile of an aircraft wing. This fuselage is manufactured using a single piece of carbon fiber composite material, achieving lightweight design. Its airfoil shape generates additional aerodynamic lift during high-speed forward flight and significantly reduces frontal drag. The airfoil fuselage integrates the battery compartment, main cables, and some control equipment, creating a natural flow correction effect.

[0030] Preferably, propeller assemblies 2 are provided on both the front and rear sides of the aircraft body 1.

[0031] An integrated T-shaped roll cage 3 is installed above and behind the cockpit of the aircraft body 1. Racing sports are inherently high-risk, especially in the event of rollovers or collisions. Traditional aircraft cockpit designs provide insufficient protection for the occupants' heads and necks, posing serious safety hazards. This integrated T-shaped roll cage 3, made of composite material, extends vertically from the rear of the cockpit upwards, while its lateral portion passes horizontally behind the occupants' heads and is securely connected to the top of the vertical portion, forming a robust T-shaped support structure. This structure ensures that in the event of a rollover or overturning, the aircraft prioritizes contact with the ground or obstacles, effectively absorbing impact energy and providing crucial survival space for the occupants' heads.

[0032] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A vertical takeoff and landing aircraft for aerial racing, characterized in that, The device includes an aircraft body, a NACA air intake and heat dissipation channel assembly disposed within the aircraft body, and a battery box disposed within the aircraft body. The NACA air intake and heat dissipation channel assembly includes a Y-shaped air intake channel body, with two air inlets at the front end and an air outlet at the rear end. The battery box is connected to the air intake channel body.

2. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: The air inlet adopts a lip design.

3. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: An air intake fan is installed at the air outlet.

4. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: The air intake channel has several heat dissipation holes, which are connected to the battery box.

5. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: A heat dissipation grille is also provided between the air intake channel and the battery box.

6. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: The NACA air intake cooling channel assembly is embedded in the aircraft body.

7. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: The aircraft body is wing-shaped.

8. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: The aircraft body is equipped with propeller assemblies on both the front and rear sides.

9. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: An integrally formed T-shaped roll cage is installed above and behind the cockpit of the aircraft body.

10. A vertical takeoff and landing aircraft for aerial racing as described in claim 1, characterized in that: The two air inlets are symmetrically arranged on both sides of the aircraft body.

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