Fuel-efficient aircraft utilizing windsurfing

Abstract

The present invention relates to an aircraft (1). More specifically, the present invention relates to an aircraft (1) having a main body (2), that conserves fuel by utilizing wind surfing. The aircraft comprises a nose section (3) that tapers towards the front end of the main body (2), and a tail section (4) that tapers towards the rear end of the main body (2). It also includes a vertical stabilizer (5) positioned centrally in the upper part, close to the tail section (4), two horizontal stabilizers (6) located on the lateral sides of the main body (2) near the nose section (3), at least two flaps (7) situated on the tail section (4), and at least two lateral engines (8) located on the lateral sides of the main body (2) that can rotate to provide thrust in different directions. Additionally, there is a main engine (9) located on the tail section (4) for forward thrust and at least two air trapping structures (10) that extend from the lower part of the nose section (3) to the beginning of the tail section (4), protruding towards the lower part of the main body (2). The surface area of the lower inclined section (3b) at the lower part of the nose section (3) is greater than the surface area of the upper inclined section (3a) at the upper part of the nose section (3) to allow air to be gathered towards the air trapping structures (10) when the aircraft is in motion. The present invention also relates to an aircraft (1) in which the nose section (3) is adapted to direct all incoming air towards the air trapping structures (10).

Description

[0001] FUEL-EFFICIENT AIRCRAFT UTILIZING WINDSURFING

[0002] Technical Field of the Invention

[0003] The present invention relates to aircraft. More particularly, the present invention relates to an aircraft with a main body, capable of windsurfing and providing fuel-efficiency.

[0004] Background of the Invention

[0005] In aircraft such as unmanned aerial vehicles and airplanes, take-off and hovering functions are generally carried out by means of the wings on the sides and the engines. Due to the difficulty, and sometimes the impossibility, of vertical take-off in these types of aircraft, along with the complex calculations required for wing design, the need to design and manufacture different types of aircraft in the relevant technical field has emerged.

[0006] The document CN 107244411 A relates to an aircraft based on a mixed wing-body configuration. The aircraft includes a forward thrust propeller, a wing-shaped body, and internal channels. The wing-shaped body is obtained by the longitudinal extension of a flat protruding wing profile. The internal channels are symmetrically arranged within the left and right interior portions of the wing-shaped body of the unmanned aerial vehicle. The internal channels include ducted propeller blades, support frames, and a gimbal ring.

[0007] The aerodynamic properties of wingless vehicles in the related art fail to meet the desired qualities due to their inability to use air effectively. This leads to higher fuel consumption, vibrations and turbulence during cruising, reduced flight safety, and stability issues. In order to solve these problems, an aircraft is presented within the scope of the present invention. By combining the elements provided within the scope of the present invention, a wingless aircraft is obtained that can perform vertical take-off and landing, provide fuel efficiency through windsurfing, and possess improved aerodynamic properties.

[0008] Brief Description of the Invention

[0009] The present invention relates to an aircraft with a main body, which provides fuel efficiency through windsurfing. The aircraft comprises a nose section tapering towards the front end of the main body and a tail section tapering towards the rear end of the main body, a vertical stabilizer centrally located on the back portion near the tail section, two horizontal stabilizers located on the side portions of the body near the nose section, at least two flaps located in the tail section, at least two lateral engines on the side portions of the main body that are capable of rotating to provide thrust in different directions for the aircraft, a main engine located in the tail section to provide forward thrust, and at least two air trapping structures located on both sides of the main body, protruding downward from the lower portion of the body and extending from the lower section of the nose section to the start of the tail section; wherein the nose section comprises an upper inclined section extending from the upper surface of the main body, with a surface inclined vertically, and a lower inclined section extending from the lower surface of the main body, with a surface inclined vertically; and, the surface area of the lower inclined section in the lower part of the nose section is greater than the surface area of the upper inclined section in the upper part of the nose section to allow air to be gathered towards the air trapping structures when the aircraft is in motion.

[0010] In another aspect, the present invention relates to an aircraft with a main body that provides fuel efficiency through windsurfing. The aircraft in question comprises a nose section tapering towards the front end of the main body and a tail section tapering towards the rear end of the main body, a vertical stabilizer centrally located on the back portion near the tail section, two horizontal stabilizers located on the side portions of the body near the nose section, two flaps located in the tail section, at least two lateral engines on the side portions of the main body that are capable of rotating to provide thrust in different directions for the aircraft, a main engine located in the tail section to provide forward thrust, and at least two air trapping structures located on both sides of the main body, protruding downward from the lower portion of the body and extending from the lower section of the nose section to the start of the tail section; wherein the nose section is adapted to direct all incoming air towards the air trapping structures.

[0011] In a preferred embodiment, the aircraft according to the present invention may comprise vertical stabilizers and / or lateral stabilizers adapted to perform rotational movement about various axes, thereby enabling the aircraft to change direction while cruising and to execute abrupt maneuvers when necessary.

[0012] In a preferred embodiment of the aircraft according to the present invention, the air trapping structures may extend from the nose section to the tail section in a gradually widening manner.

[0013] In a preferred embodiment of the aircraft according to the present invention, the aircraft may comprise at least one stability control system to actively control the stability of the aircraft.

[0014] In a preferred embodiment of the aircraft according to the present invention, the air trapping structures may be adapted to have a curved shape that extends towards the main body.

[0015] In a preferred embodiment of the aircraft according to the present invention, the aircraft may comprise at least one braking flap located on the upper surface of the main body. In a preferred embodiment of the aircraft according to the present invention, the aircraft may comprise at least two landing gear located on the underside of the main body and / or on the underside of the air trapping structures.

[0016] In a preferred embodiment of the aircraft according to the present invention, the aircraft may comprise a navigation control system with at least one receiver and at least one transmitter that enables remote control of the aircraft.

[0017] Brief Description of the Figures

[0018] Figure 1 is a top and front perspective view of an aircraft according to one aspect of the present invention.

[0019] Figure 2 is a side view of an aircraft according to one aspect of the present invention.

[0020] Figure 3 is a bottom perspective view of an aircraft according to one aspect of the present invention.

[0021] References

[0022] 1. Aircraft

[0023] 2. Main body

[0024] 3. Nose section

[0025] 4. Tail section

[0026] 5. Vertical stabilizer

[0027] 6. Horizontal stabilizer

[0028] 7. Flap

[0029] 8. Lateral engine

[0030] 9. Main engine

[0031] 10. Air trapping structure

[0032] 3a. Upper inclined section

[0033] 3b. Lower inclined section

[0034] Detailed Description of the Invention

[0035] As seen in Figures 1, 2, and 3, the aircraft (1) comprises a nose section (3) tapering towards the front end of the main body (2) and a tail section (4) tapering towards the rear end of the main body (2). It also includes a vertical stabilizer (5) located in the upper part near the tail section (4), two horizontal stabilizers (6) positioned on the sides of the main body (2) close to the nose section (3), at least two flaps (7) located on the tail section (4), and at least two lateral engines (8) mounted on the sides of the main body (2), which can pivot to provide thrust in different directions. Additionally, the aircraft features a main engine (9) located on the tail section (4) to provide forward thrust, and at least two air trapping structures (10) protruding from both sides of the main body (2), extending from the lower part of the nose section (3) to the beginning of the tail section (4). The surface area of the lower inclined section (3b) of the nose section (3) is greater than that of the upper inclined section (3a) of the nose section (3) to allow the airflow to be directed towards the air trapping structures (10) while the aircraft is in motion.

[0036] By combining the said elements, the aircraft (1) with improved aerodynamic characteristics can effectively utilize the airflow coming from below / front during cruising, thanks to the at least two air trapping structures (10) protruding from the lower part of the main body (2), enabling windsurfing. This results in fuel savings, especially at high altitudes where pressure is low, and provides a vehicle that can also be used in low orbits where atmospheric pressure is very low. The design of the aircraft (1) also enables takeoff and landing operations in short runways and vertical takeoff / landing areas. The aircraft (1) can be adapted for various uses, including as a UAV / UCAV, short and medium-range taxi, long-distance passenger aircraft, satellite and base station for low orbits, air ambulance, firefighting aircraft, agricultural aircraft (for example, crop dusting), and fighter aircraft, following necessary modifications dictated by relevant technology.

[0037] The vertical stabilizer (5) and / or horizontal stabilizers (6) can be configured to allow the aircraft (1) to change direction during cruising and to perform abrupt maneuvers when necessary. Thus, for instance, if the aircraft (1) is configured as a UAV or fighter aircraft, a more advantageous structure is obtained. Likewise, the lateral engines (8) are also designed to provide thrust in different directions as needed. For example, during vertical takeoff and landing, these engines (8) can be directed downward to facilitate the operations. Preferably, the lateral engines (8) can be adapted to provide thrust in all directions, meaning they can rotate 360 degrees. The main engine (9) provides forward thrust while cruising. Furthermore, the surface area of the lower inclined section (3b) of the nose section (3) is greater than that of the upper inclined section (3a) of the nose section (3), meaning that, as illustrated in Figure 2, the upper part of the nose section (3) is steeper than the lower part, and the inclined area created in the lower part of the nose section (3) is longer than that in the upper part. This configuration allows a significant portion of the airflow directed towards the front of the aircraft (1) to be redirected towards the underside of the aircraft (1) and consequently towards the air trapping structures (10), creating a concentrated airflow region between the air trapping structures (10). This allows the aircraft (1) to utilize air and the lift force of the air more effectively. According to a preferred advantageous structure, the tip section dividing the nose section (3) can be positioned such that one-third of the nose section (3) is on the top and two-thirds on the bottom. This arrangement further enhances the effectiveness of the airflow directed towards the nose section (3) during cruising. The flaps (7) can also enable the aircraft (1) to maneuver up ward / down ward when necessary. These flaps (7) can operate either in a synchronized manner or independently.

[0038] In another aspect, the present invention relates to an aircraft (1) in which the nose section (3) is configured to direct all incoming airflow from the front towards the air trapping structures (10). In this aircraft (1), the tip section of the nose (3) is integrally connected to the upper surface of the aircraft (1), and the nose section (3) slopes downward towards the lower part of the aircraft (1), directing all airflow towards the air trapping structures (10).

[0039] According to an advantageous embodiment presented for the aircraft (1), the air trapping structures (10) can extend from the nose section (3) towards the tail section (4). This arrangement creates a narrower area at the rear of the aircraft (1) between the air trapping structures (10) and captures the airflow moving from the front to the rear beneath the aircraft (1).

[0040] According to a preferred embodiment presented for the aircraft (1), the aircraft (1) may include at least one stability control system (ESC, ESP, DSC) to actively control the stability of the aircraft (1). This way, stability issues arising from turbulence during cruising can be automatically corrected.

[0041] For an advantageous embodiment, the air trapping structures (10) may have an inwardly curved structure towards the main body (2). This allows the airflow coming beneath the aircraft (1) to be retained more efficiently between the curved air trapping structures (10), enabling the aircraft (1) to make better use of the lift force of the air.

[0042] In another embodiment, the aircraft (1) may include at least one braking flap (not shown) located on the upper surface of the main body (2). This braking flap / flaps can be deployed upward when necessary, creating a slowing and stopping effect on the aircraft (1) through friction and deflection.

[0043] In another embodiment, the aircraft (1) may include at least two landing gear (not shown) located on the bottom of the main body (2) and / or the bottom of the air trapping structures (10). The landing gear can be in a wheeled arrangement or similar to the surface landing gear used in helicopters within the relevant technology. In another embodiment, the aircraft (1) may include at least one receiver and at least one transmitter for remote control capabilities, along with a navigation control system.

[0044] The foregoing disclosure and description of the aircraft according to the present invention are intended to be illustrative and explanatory. Other alternative arrangements related to the present invention and modifications that can be made based on the field and sector in which the aircraft will be used may be implemented by experts in the relevant technical field without departing from the spirit of the invention.

Claims

CLAIMS1. An aircraft (1) that conserves fuel by utilizing wind surfing, having a main body (2), characterized in that the aircraft comprises; a nose section (3) that tapers towards the front end of the main body (2) and a tail section (4) at the rear end of the main body (2), a vertical stabilizer (5) positioned centrally in the upper part, close to the tail section (4), two horizontal stabilizers (6) located on the lateral sides of the main body (2) near the nose section (3), at least two flaps (7) situated on the tail section (4), at least two lateral engines (8) located on the lateral sides of the main body (2) that can rotate to provide thrust in different directions for the aircraft (1), a main engine (9) located on the tail section (4) for forward thrust, and at least two air trapping structures (10) that extend from the lower part of the nose section (3) to the beginning of the tail section (4), protruding towards the lower part of the main body (2); wherein the nose section (3) comprises: an upper inclined section (3 a) extending from the upper surface of the main body (2), with a surface inclined vertically, a lower inclined section (3b) extending from the lower surface of the main body (2), with a surface inclined vertically; and wherein, the surface area of the lower inclined section (3b) is greater than the surface area of the upper inclined section (3a), such that while the aircraft is in motion, air is directed towards and gathered between the air trapping structures (10).

2. An aircraft (1) that conserves fuel by utilizing wind surfing, having a main body (2), characterized in that the aircraft comprises; a nose section (3) that tapers towards the front end of the main body (2) and a tail section (4) at the rear end of the main body (2), a vertical stabilizer (5) positioned centrally in the upper part, close to the tail section (4), two horizontal stabilizers (6) located on the lateral sides of the main body (2) near the nose section (3), at least two flaps (7) situated on the tail section (4), at least two lateral engines (8) located on the lateral sides of the main body (2) that can rotate to provide thrust in different directions for the aircraft (1), a main engine (9) located on the tail section (4) for forward thrust, and at least two air trapping structures (10) that extend from the lower part of the nose section (3) to the beginning of the tail section (4), protruding towards the lower part of the main body (2); wherein the nose section (3 ) is adapted to direct all incoming air towards the air trapping structures (10).

3. The aircraft (1) according to claim 1 or 2, characterized in that the vertical stabilizer (5) and / or the lateral stabilizers (6) are adapted to perform rotational movement about various axes to enable the aircraft (1) to change direction during cruising and perform abrupt maneuvers when necessary.

4. The aircraft (1) according to any one of the preceding claims, characterized in that the tail section (4) tapers towards the rear end of the main body (2).

5. The aircraft (1) according to any one of the preceding claims, characterized in that the air trapping structures (10) extend from the nose section (3) towards the tail section (4) in a gradually widening manner.

6. The aircraft (1) according to any one of the preceding claims, characterized in that the aircraft (1) comprises at least one stability control system to actively control the stability of the aircraft.

7. The aircraft (1) according to any one of the preceding claims, characterized in that the air trapping structures (10) are curved towards the main body (2).

8. The aircraft (1) according to any one of the preceding claims, characterized in that the aircraft (1) comprises at least one braking flap located on the upper surface of the main body (2).

9. The aircraft (1) according to any one of the preceding claims, characterized in that the aircraft (1) comprises at least two landing gears located on the underside of the main body (2) and / or on the underside of the air trapping structures (10).

10. The aircraft (1) according to any one of the preceding claims, characterized in that the aircraft (1) comprises a navigation control system with at least one receiver and at least one transmitter to enable remote control of the aircraft (1).

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