CN115432180A - Novel double-wing aircraft with wingtip propeller - Google Patents

Novel double-wing aircraft with wingtip propeller Download PDF

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Publication number
CN115432180A
CN115432180A CN202211263355.0A CN202211263355A CN115432180A CN 115432180 A CN115432180 A CN 115432180A CN 202211263355 A CN202211263355 A CN 202211263355A CN 115432180 A CN115432180 A CN 115432180A
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CN
China
Prior art keywords
wing
propeller
nacelle
lower wing
propellers
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202211263355.0A
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Chinese (zh)
Inventor
王耀坤
韦嘉宁
林招如
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Beihang University
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Beihang University
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Filing date
Publication date
Application filed by Beihang University filed Critical Beihang University
Priority to CN202211263355.0A priority Critical patent/CN115432180A/en
Publication of CN115432180A publication Critical patent/CN115432180A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces

Abstract

The invention provides a novel double-wing aircraft with wingtip propellers, which mainly aims at reducing the lift loss of the aircraft and improving the reliability of the operation of the aircraft. The plane of the invention adopts a double-wing design, thereby avoiding the lift loss caused by a horizontal tail wing in the conventional plane. The propellers are arranged at the wingtips of the wings, the flying attitude of the airplane is controlled by adjusting the pulling force of the propellers, the traditional control plane is replaced, and the control reliability of the airplane can be improved. The wingtip propeller is controlled to rotate in a predetermined direction, and the rotor slip flow is used to weaken the wingtip vortex and reduce the flight resistance.

Description

Novel double-wing aircraft with wingtip propeller
Technical Field
The invention relates to a novel double-wing airplane with wingtip propellers.
Background
The conventional aircraft comprises a fuselage, wings, a horizontal tail, a vertical tail and the like, and in order to keep the balance of the aircraft during the flight, the horizontal tail at the tail of the fuselage needs to provide downward aerodynamic force opposite to the direction of lift, so that the loss of the lift of the whole aircraft is brought about, as shown in fig. 1. In addition, the conventional aircraft has a complex structure and low reliability of control surfaces such as ailerons, elevators, and rudders, as shown in fig. 2.
Disclosure of Invention
In order to avoid the problem of lift loss caused by a horizontal tail wing in a conventional aircraft and improve the reliability of the aircraft in maneuvering, the invention provides a novel double-wing aircraft with wingtip propellers.
In the design of the invention, a horizontal tail wing which generates downward aerodynamic force in a conventional airplane needs to be cancelled, so that the aerodynamic forces generated by the upper and lower pairs of wing surfaces are all used for providing lift force, and the loss of the lift force is avoided. Meanwhile, a control surface in a conventional airplane needs to be cancelled, propellers are arranged at the wing tips of the wings, and the flying attitude of the airplane is controlled by utilizing the moment formed by the tension difference of the four propellers, so that the control reliability of the airplane is improved. Therefore, the invention designs a novel double-wing aircraft with wingtip propellers.
According to one aspect of the present invention, there is provided a novel twin-wing aircraft having wingtip propellers, characterized by comprising:
an upper wing, a lower wing and a fuselage,
a first nacelle and a second nacelle respectively provided at both end portions of the upper wing,
a third nacelle and a fourth nacelle respectively provided at both end portions of the lower wing,
first to fourth propellers respectively arranged in front of the first to fourth nacelles,
wherein:
the upper wing is connected with the V-shaped empennage at the rear part of the fuselage,
the lower wing is connected with the front part of the fuselage,
the upper wing and the lower wing are spaced at a certain distance along the height direction, and the upper wing and the lower wing are staggered at a certain distance along the front-back direction, so that the air flow interference between the upper wing and the lower wing is reduced,
in the flying process, the upper wing and the lower wing both generate upward lift force, and the lift force generated by the upper wing and the lift force generated by the lower wing can keep the airplane balanced,
compared with the first nacelle and the second nacelle at the two ends of the upper wing, the third nacelle and the fourth nacelle at the two ends of the lower wing are inclined at a certain angle,
in the flying process, the rotating speeds of the first propeller, the second propeller, the third propeller, the fourth propeller and the fourth propeller are respectively adjusted to enable the first propeller, the second propeller, the third propeller and the fourth propeller to respectively generate different pulling forces, and the moment formed by the difference of the pulling forces of the first propeller, the second propeller and the fourth propeller is utilized to control the flying attitude of the airplane.
Drawings
FIG. 1 is a schematic diagram of forces experienced by a conventional aircraft, wherein: full lift = wing lift-aerodynamic force down the horizontal tail.
Fig. 2 is a picture of an example of a complex structural arrangement of a conventional aircraft wing control surface.
Fig. 3 is a perspective view of a new twin wing aircraft having wingtip propellers according to one embodiment of the present invention.
Figure 4 is a side view of a new dual wing aircraft having wingtip propellers according to one embodiment of the present invention.
Fig. 5 is a front view of a new twin wing aircraft with wingtip propellers according to one embodiment of the invention.
Fig. 6 is a top view of a novel two wing aircraft having wingtip propellers according to one embodiment of the present invention.
Fig. 7 is a schematic view of the airflow effect in the case of no propeller arranged in front of the left lower wing nacelle.
Fig. 8 is a schematic view of the airflow effect in the case where a propeller is arranged in front of the nacelle of the lower left wing according to an embodiment of the present invention.
Fig. 9 is a schematic fuselage view of a new dual wing aircraft having wingtip propellers according to one embodiment of the present invention.
Detailed Description
As shown in fig. 3, the novel two-wing aircraft with wingtip propellers according to one embodiment of the present invention includes an upper wing (1), a lower wing (2), and a fuselage (3). The upper wing (1) is connected with a V-shaped empennage (14) at the rear part of the fuselage (3), and the lower wing (2) is connected with the front part of the fuselage (3). A first nacelle (4) and a second nacelle (6) are respectively arranged at two ends of the upper wing (1), a third nacelle (8) and a fourth nacelle (10) are respectively arranged at two ends of the lower wing (2), and first to fourth propellers (5, 7,9, 11) are respectively arranged in front of the first to fourth nacelles (4, 6,8, 10).
Wing
The side view of the airplane is shown in fig. 4, the upper wing (1) and the lower wing (2) are spaced at a certain distance along the height direction, and the upper wing (1) and the lower wing (2) are staggered at a certain distance along the front-back direction, so that the air flow interference between the upper wing (1) and the lower wing (2) is reduced. In the flight process, the upper wing (1) and the lower wing (2) generate upward lift force, and the lift force generated by the upper wing (1) and the lift force generated by the lower wing (2) can keep the balance of the airplane.
As shown in the side view of the aircraft in fig. 4, the third nacelle (8) and the fourth nacelle (10) at the end of the lower wing (2) are angled upwards compared to the first nacelle (4) and the second nacelle (6) of the upper wing (1). During the flight, the rotating speed of the propellers (5, 7,9, 11) at the ends of the upper wing (1) and the lower wing (2) is adjusted, so that the first propeller (5), the fourth propeller (7, 9, 11) can generate different pulling forces, and the flying attitude of the airplane is controlled by utilizing the moment formed by the pulling force difference of the first propeller (5), the fourth propeller (5, 7,9, 11).
As shown in fig. 7, taking the left lower wing (2) as an example, if no propeller (9) is arranged in front of the third nacelle (8) at the tip of the left lower wing (2) during the flight of a conventional aircraft, when viewed from the nose to the rear, the tip of the left lower wing (2) generates a tip vortex (12) in a counterclockwise direction, so that the aircraft drag is increased, and the energy of the aircraft is consumed. A front view of an aircraft according to one embodiment of the invention is shown in fig. 5 and 6, from which the first propeller (5) on the left side of the upper wing (1) and the third propeller (9) on the left side of the lower wing (2) rotate in a clockwise direction and the second propeller (7) and the fourth propeller (11) on the right side rotate in a counter-clockwise direction. As shown in fig. 8, taking the left lower wing (2) as an example, if the third propeller (9) is arranged in front of the third nacelle (8) and the third propeller (9) is rotated in a specified direction, a strong propeller slipstream (13) is formed behind the third propeller (9), and the direction of the propeller slipstream (13) is opposite to the rotation direction of the wing tip vortex (12), so that the wing tip vortex (12) is weakened and the flight resistance is reduced.
Fuselage body
The fuselage (3) of the new two-wing aircraft with wingtip propellers is shown in fig. 9. The fuselage (3) is streamlined and can be used for loading equipment required by flight. The rear part of the machine body (3) is connected with a V-shaped empennage (14). The V-shaped tail wing (14) is connected with the upper wing (1), so that a whole body for providing lift force can be formed, and the supporting strength of the upper wing (1) can be increased.
Advantageous effects
The advantages and beneficial effects of the invention include:
1) The design of the upper pair of wings and the lower pair of wings is adopted, so that the aerodynamic force of the wings is completely used for providing lift force, and the loss of the lift force generated by the horizontal tail wing in the conventional airplane is avoided.
2) The propellers arranged at the wingtips not only provide power required by the flight of the airplane, but also can control the flight attitude of the airplane by adjusting the pulling force of each propeller, thereby replacing the traditional control surface and improving the reliability of the airplane control. And provides a novel control mode.
3) The propeller arranged at the wing tip can inhibit the wing tip vortex and reduce the flight resistance while generating the pulling force.
4) The two wings are pulled apart by a certain distance in the front-back direction and the up-down direction, so that the aerodynamic interference between the wings is reduced.
5) The design of the V-shaped tail wing can increase the supporting strength of the upper wing.

Claims (6)

1. A new twin-wing aircraft with wingtip propellers, characterized in that it comprises:
an upper wing (1), a lower wing (2) and a fuselage (3),
a first nacelle (4) and a second nacelle (6) respectively arranged at both ends of the upper wing (1),
a third nacelle (8) and a fourth nacelle (10) respectively arranged at both ends of the lower wing (2),
first to fourth propellers (5, 7,9, 11) arranged in front of the first to fourth nacelles (4, 6,8, 10), respectively,
wherein:
the upper wing (1) is connected with a V-shaped empennage (14) at the rear part of the fuselage (3),
the lower wing (2) is connected with the front part of the fuselage (3),
the upper wing (1) and the lower wing (2) are spaced at a certain distance along the height direction, and the upper wing (1) and the lower wing (2) are staggered at a certain distance along the front-back direction, so that the air flow interference between the upper wing (1) and the lower wing (2) is reduced,
in the flying process, the upper wing (1) and the lower wing (2) both generate upward lift force, and the lift force generated by the upper wing (1) and the lift force generated by the lower wing (2) can keep the airplane balanced,
compared with the first nacelle (4) and the second nacelle (6) at the two ends of the upper wing (1), the third nacelle (8) and the fourth nacelle (10) at the two ends of the lower wing (2) are inclined upwards by a certain angle,
during the flight, the rotation speed of the first propeller (5) to the fourth propeller (5, 7,9, 11) is respectively adjusted to enable the first propeller (5) to the fourth propeller (7, 9, 11) to respectively generate different pulling forces, and the flying attitude of the airplane is controlled by utilizing the moment formed by the pulling force difference of the first propeller (5) to the fourth propeller (7, 9, 11).
2. The new twin wing aircraft with wingtip propellers of claim 1, characterized in that:
from the front view of the airplane, the first propeller (5) on the left side of the upper wing (1) and the third propeller (9) on the left side of the lower wing (2) rotate along the anticlockwise direction, the second propeller (7) and the fourth propeller (11) on the right side rotate along the clockwise direction, a propeller slip flow (13) is formed behind the third propeller (9), the direction of the propeller slip flow (13) is opposite to the rotation direction of the wingtip vortex (12), and the wingtip vortex (12) is weakened, so that the flight resistance is reduced.
3. The new twin-wing aircraft with wingtip propellers according to claim 1 or 2, characterized in that:
the fuselage (3) is streamline and is used for loading equipment required by flight.
4. A method of attitude control for a novel twin-wing aircraft having wingtip propellers, the novel twin-wing aircraft comprising:
an upper wing (1), a lower wing (2) and a fuselage (3),
a first nacelle (4) and a second nacelle (6) respectively arranged at both ends of the upper wing (1),
a third nacelle (8) and a fourth nacelle (10) respectively arranged at both ends of the lower wing (4),
first to fourth propellers (5, 7,9, 11) arranged in front of the first to fourth nacelles (4, 6,8, 10), respectively,
wherein:
the upper wing (1) is connected with a V-shaped empennage (14) at the rear part of the fuselage (3),
the lower wing (2) is connected with the front part of the fuselage (3),
the upper wing (1) and the lower wing (2) are spaced at a certain distance along the height direction, and the upper wing (1) and the lower wing (2) are staggered at a certain distance along the front-back direction, so that the air flow interference between the upper wing (1) and the lower wing (2) is reduced,
in the flying process, the upper wing (1) and the lower wing (2) both generate upward lift force, and the lift force generated by the upper wing (1) and the lift force generated by the lower wing (2) can keep the airplane balanced,
it is characterized by comprising:
compared with the first nacelle (4) and the second nacelle (6) at the two ends of the upper wing (1), the third nacelle (8) and the fourth nacelle (10) at the two ends of the lower wing (2) are inclined upwards by a certain angle,
during the flight, the rotation speed of each of the first to fourth propellers (5, 7,9, 11) is adjusted so that the first to fourth propellers (5, 7,9, 11) generate different pulling forces, and the flying attitude of the airplane is controlled by using the moment formed by the pulling force difference of the first to fourth propellers (5, 7,9, 11).
5. The attitude control method according to claim 4, characterized by further comprising:
when viewed from the front of the airplane, the first propeller (5) on the left side of the upper wing (1) and the third propeller (9) on the left side of the lower wing (2) rotate along the anticlockwise direction, the second propeller (7) on the right side and the fourth propeller (11) rotate along the clockwise direction, and therefore a propeller slipstream (13) is formed behind the third propeller (9), the direction of the propeller slipstream (13) is opposite to the rotation direction of the wingtip vortex (12), and the wingtip vortex (12) is weakened, so that the flight resistance is reduced.
6. The attitude control method according to claim 4 or 5, characterized in that:
the fuselage (3) is streamline and is used for loading equipment required by flight.
CN202211263355.0A 2022-10-15 2022-10-15 Novel double-wing aircraft with wingtip propeller Pending CN115432180A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211263355.0A CN115432180A (en) 2022-10-15 2022-10-15 Novel double-wing aircraft with wingtip propeller

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211263355.0A CN115432180A (en) 2022-10-15 2022-10-15 Novel double-wing aircraft with wingtip propeller

Publications (1)

Publication Number Publication Date
CN115432180A true CN115432180A (en) 2022-12-06

Family

ID=84251250

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211263355.0A Pending CN115432180A (en) 2022-10-15 2022-10-15 Novel double-wing aircraft with wingtip propeller

Country Status (1)

Country Link
CN (1) CN115432180A (en)

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