Distributed vector exhaust ducted fan box type wing eVTOL

Abstract

The invention relates to the field of electric vertical take-off and landing aircrafts, and discloses a distributed vector exhaust ducted fan box-type wing eVTOL, which comprises a box-type wing, a front wing main wing, a front wing aileron and a rear wing are connected through a joint flange, and the box-type wing is fused with a fuselage to form a closed box-shaped structure; the V-shaped empennage is positioned at the tail and forms a main lift part of the aircraft with the box-type wings; the plurality of electric ducted fans with the guide vane type vector exhaust devices are longitudinally arranged along the two sides of the aircraft body, the included angle between each electric ducted fan with the guide vane type vector exhaust device on one side and the horizontal direction of the aircraft body is a set angle, and a power unit of the aircraft is formed in a distributed power form. Through the combination of a guide vane type vector exhaust technology and a longitudinal distributed power system, large-range thrust direction adjustment is achieved, the requirements of vertical take-off and landing and efficient cruise are met, and the power unit has the characteristics of low noise, high redundancy and modularization and is particularly suitable for urban air traffic and short-distance logistics transportation.

Description

Technical Field

[0001] The present invention relates to the field of electric vertical take-off and landing aircraft, and in particular to a distributed vector exhaust ducted fan box-type wing eVTOL. Background Art

[0002] With the rapid development of Urban Air Mobility (UAM), electric vertical take-off and landing aircraft (eVTOL) has become a key development direction for future urban air mobility due to its fast and safe vertical take-off and landing capabilities and efficient cruising performance. The traditional eVTOL vector tilt technology has the problems of high mechanical complexity, low transmission efficiency and power unit death. As a vertical take-off and landing power unit, the electric ducted fan with a guide vane vector exhaust device can change the thrust vector direction by deflecting the guide vanes, significantly improving the efficient switching of eVTOL between vertical take-off and landing and horizontal cruising modes.

[0003] The existing eVTOL aerodynamic layout faces obvious limitations in optimizing the aircraft layout due to low battery energy density, and the traditional aerodynamic layout is difficult to take into account the performance requirements of vertical take-off and landing and horizontal cruising. As an advanced aerodynamic layout, the box-wing configuration has gradually attracted widespread attention due to its unique advantages of high lift-to-drag ratio and lightweight structure. Distributed propulsion system (DPS) has also become an important development direction due to its flexible thrust distribution and high redundancy. However, current research focuses on the lateral layout of distributed power, while there is less research on the longitudinal layout, and the design scheme for distributed power aircraft with box-wing configuration is even more scarce. Therefore, there is an urgent need for an eVTOL design that combines a distributed power system with an innovative aerodynamic layout (such as a box-wing configuration) to meet the technical requirements of future urban air traffic for high efficiency and long endurance. This design will provide an innovative and practical solution for the future development of the aviation field. Summary of the invention

[0004] In view of the above-mentioned technical deficiencies, the technical problem to be solved by the present invention is to provide a distributed vector exhaust ducted fan box-type wing eVTOL, which aims to optimize the thrust distribution and improve the power efficiency, stability and controllability of the electric vertical take-off and landing aircraft through the integration of guide vane vector exhaust technology and distributed power system with the box-type wing configuration.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions: The present invention provides a distributed vector exhaust ducted fan box-wing eVTOL, comprising: a box-wing, which is connected by a front wing main wing, a front wing aileron and a rear wing through a joint wing edge, and is integrated with a fuselage to form a closed box-shaped structure; The V-shaped tail, located at the tail of the aircraft and forming the main lifting part of the aircraft with the box wing; Several electric ducted fans with guide vane vector exhaust devices are arranged longitudinally along both sides of the fuselage. Each electric ducted fan with a guide vane vector exhaust device on one side has a set angle with the horizontal direction of the fuselage, forming the power unit of the aircraft in the form of distributed power.

[0006] Furthermore, each electric ducted fan with a guide vane vector exhaust device on one side has an angle of 30° with the horizontal direction of the fuselage.

[0007] Furthermore, the electric ducted fan with a guide vane vector exhaust device includes: New aerodynamic lip inlet, ducted fan rotor and guide vane vectored exhaust; Among them, the ducted fan rotor is located in the duct, the inlet of the duct is connected to the outlet of the novel pneumatic lip air intake device, and the outlet of the duct is connected to the guide vane vector exhaust device.

[0008] Furthermore, the novel pneumatic lip air intake device ensures a smooth transition of airflow from the outside to the inside by adding a guide plate to the air intake lip, and is used to provide an effective air intake area in vertical take-off and landing and horizontal cruising modes; The ducted fan rotor is composed of a plurality of blades and is used to generate thrust; The guide vane vector exhaust device is composed of a plurality of exhaust guide vanes, and is used to adapt to the requirements of different flight conditions by deflecting the exhaust guide vanes within a range of 0 to 90 degrees, and to provide additional control torque to enhance the accuracy of attitude control.

[0009] Furthermore, in the vertical take-off and landing mode, the exhaust guide vanes of the guide vane vector exhaust device are deflected to a maximum angle of 90°, with the guide vanes pointing vertically downward; In the horizontal cruising mode, the exhaust guide vanes of the guide vane vector exhaust device are deflected to a minimum angle of 0°, and the guide vanes are horizontally facing backwards.

[0010] Furthermore, the deflection angle of the exhaust guide vanes of the guide vane vector exhaust device at the front and rear parts of the fuselage is adjusted through differential control to change the direction of the thrust vector, thereby generating a torque around the horizontal axis to achieve a pitch attitude.

[0011] Furthermore, the exhaust guide vane angles of the left and right guide vane vector exhaust devices of the fuselage are adjusted to change the direction of the thrust vector, thereby generating a torque around the longitudinal axis to achieve a rolling attitude.

[0012] Furthermore, the vector differential of the left and right ducted fan rotors of the fuselage is adjusted to generate a torque around the vertical axis to achieve a yaw attitude.

[0013] The beneficial effects of the present invention are as follows: through the combination of guide vane vector exhaust technology and longitudinal distributed power system, a wide range of adjustment of the thrust direction of the aircraft is innovatively achieved, taking into account the performance requirements of vertical take-off and landing and efficient cruising. At the same time, the smaller power unit has the characteristics of low noise, high redundancy and modularity, which is particularly suitable for application scenarios such as urban air traffic and short-distance logistics transportation. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0015] Figure 1 A top view of a distributed vector exhaust ducted fan box-wing eVTOL provided in an embodiment of the present invention.

[0016] Figure 2 This is a schematic diagram of the box wing structure.

[0017] Figure 3 A side view of a distributed vector exhaust ducted fan box-wing eVTOL.

[0018] Figure 4 Schematic diagram of an electric ducted fan with a guide vane vectored exhaust device.

[0019] Figure 5 Schematic diagram of the guide vane vector exhaust device in vertical take-off and landing mode.

[0020] Figure 6 Schematic diagram of the guide vane vector exhaust device in horizontal cruise mode.

[0021] Figure 7 Schematic diagram of vector thrust control.

[0022] Explanation of the reference numerals: 1. fuselage, 2. canard main wing, 3. canard aileron, 4. joint wing, 5. rear wing, 6. V-shaped tail, 7. electric ducted fan with guide vane vector exhaust device, 71. air intake device with new aerodynamic lip, 72. ducted fan rotor, 73. guide vane vector exhaust device. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] Example 1

[0025] like Figure 1 to Figure 7 As shown, this embodiment provides a distributed vector exhaust ducted fan box-wing eVTOL, including: Figure 2 The box-shaped wing shown is connected by the front wing main wing 2, the front wing aileron 3 and the rear wing 5 through the joint wing edge 4, and is integrated with the fuselage 1 to form a closed box-shaped structure; the V-shaped tail 6 is located at the tail and constitutes the main lift part of the aircraft with the box-shaped wing. It should be noted that this layout significantly improves the lift-to-drag ratio, reduces induced drag, and enhances structural strength and rigidity, which helps to improve the flight efficiency of the aircraft; in addition, the V-shaped tail 6 optimizes the airflow distribution, which not only improves the flight stability, but also significantly improves the control performance.

[0026] like Figure 3 As shown, six electric ducted fans 7 with guide vane vector exhaust devices are arranged longitudinally along both sides of the fuselage. Each electric ducted fan 7 with a guide vane vector exhaust device on one side is at an angle of 30° with the horizontal direction of the fuselage, forming the power unit of the aircraft in the form of distributed power. It should be noted that this longitudinal distributed design can highly coordinate the thrust and aerodynamic layout, effectively improve the aerodynamic efficiency, and at the same time has high redundancy and safety. Even if a single power unit fails, other power units can still operate stably. The aircraft can still maintain normal flight by allocating the remaining power units through flight control. In addition, this layout can adapt to a variety of flight modes, including vertical take-off and landing, hovering and efficient cruising, etc., providing excellent performance support for the aircraft.

[0027] like Figure 4 As shown, the electric ducted fan 7 with a guide vane vector exhaust device includes: a new type of pneumatic lip air intake device 71, a ducted fan rotor 72 and a guide vane vector exhaust device 73; wherein, the ducted fan rotor 72 is located in the duct, the inlet of the duct is connected to the outlet of the new type of pneumatic lip air intake device 71, and the outlet of the duct is connected to the guide vane vector exhaust device 73.

[0028] Specifically, the new aerodynamic lip air intake device 71 ensures a smooth transition of the airflow from the outside to the inside by adding a guide plate to the air intake lip, so as to provide an effective air intake area in vertical take-off and landing and horizontal cruise modes; the ducted fan rotor 72 is composed of a plurality of blades and is used to generate thrust; the guide vane vector exhaust device 73 is composed of a plurality of exhaust guide vanes and is used to adapt to the requirements of different flight states by deflecting its exhaust guide vanes within the range of 0 to 90 degrees, and to provide additional control torque to enhance the accuracy of attitude control; the exhaust guide vanes in the guide vane vector exhaust device 73 can be deflected at 0-90 degrees according to the different modes of vertical take-off and landing and horizontal cruise of the aircraft to meet the requirements of different flight states.

[0029] like Figure 5 As shown, it is a schematic diagram of the exhaust guide vane deflection in the guide vane type vector exhaust device 73 in the vertical take-off and landing mode. In this mode, the guide vane deflection angle is the maximum deflection angle of 90°, and the streamline enters the duct from the circumferential direction directly above the air intake device with a new pneumatic lip 71. At this time, the new air intake lip on the left and right of the air intake device with a new pneumatic lip 71 can be used as the effective area of ​​the air intake duct; like Figure 6 As shown, it is a schematic diagram of the exhaust guide vane deflection in the guide vane vector exhaust device 73 in the horizontal cruising mode. The guide vane deflection angle of this mode is the minimum deflection angle of 0°, and the guide vane is horizontally backward; the streamline passes through the horizontal flow of the novel aerodynamic lip air intake device 71, deflected more than 90°, enters the duct fan rotor 72, and finally is discharged from the duct fan through the exhaust guide vane deflected less than 90°. On the right side of the novel aerodynamic lip air intake device 71, due to the existence of the separation vortex, the flow channel is blocked, and the streamline can smoothly enter the duct through the novel aerodynamic lip air intake device 71 in the horizontal cruising mode; therefore, the novel aerodynamic lip air intake device 71 not only meets the air intake area of ​​the duct fan during vertical take-off and landing, but also meets the air intake area of ​​the duct fan during horizontal cruising.

[0030] like Figure 7 As shown, the deflection angle of the exhaust guide vanes in the guide vane vector exhaust device 73 at the front and rear parts of the fuselage 1 is adjusted through differential control to change the direction of the thrust vector, thereby generating a torque around the Y-axis in the horizontal axis corresponding to the figure, thereby realizing the pitch attitude; the angle of the left and right vector exhaust guide vanes of the fuselage 1 is adjusted to change the direction of the thrust vector, thereby generating a torque around the X-axis in the vertical axis corresponding to the figure, thereby realizing the roll attitude; the vector differential of the left and right ducted fans of the fuselage 1 is adjusted to generate a torque around the Z-axis in the vertical axis corresponding to the figure, thereby realizing the yaw attitude.

[0031] It can be seen that the exhaust guide vanes in the guide vane vector exhaust device 73 of this embodiment change the thrust vector by adjusting the exhaust direction of the engine, thereby improving the maneuverability and efficiency of the aircraft; by adjusting the exhaust direction, the aircraft can smoothly transition between vertical take-off and landing, hovering and forward flight cruise, shortening the transition time. The exhaust guide vanes in the guide vane vector exhaust device 73 can optimize the thrust direction, making the aerodynamic force distribution in different flight modes more reasonable and improving the overall efficiency; the exhaust guide vanes in the guide vane vector exhaust device 73 provide additional control torque, especially in the low-speed and hovering stages, to improve the accuracy of attitude control.

[0032] The basic principle of the present invention is: each power unit adopts an electric ducted fan 7 with a guide vane vector exhaust device, and its core feature is that it can achieve a large range of 0-90° deflection of the thrust direction. During vertical take-off and landing, the guide vane exhaust device is vertically downward to provide vertical downward thrust; in horizontal cruise mode, the guide vane vector exhaust device deflects a maximum angle of 90°, and the thrust vector is horizontally backward, and the eVTOL achieves the effect of level flight cruise; when switching between the two modes, there is no need to tilt the entire power unit, and the change of thrust direction can be completed by adjusting the vector exhaust guide vane at 0-90° deflection. This design not only significantly improves the reliability and response speed of the system, but also enables the aircraft to have higher control flexibility; in addition, in conjunction with the new pneumatic lip intake device 71, it can meet the efficient capture of airflow by the intake device during vertical take-off and landing and horizontal cruise. The electric ducted fan 7 with a guide vane vector exhaust device is driven by a high-efficiency DC motor, combined with the optimized design of the new pneumatic lip and the low-resistance duct structure, which significantly improves the power output efficiency. The power unit is also lightweight and modular, which is not only easy to install and maintain, but also further enhances the overall performance of the aircraft. With the intelligent control system, the aircraft can achieve precise control of pitch, roll and yaw through the thrust vector function, and at the same time, the V-shaped tail improves flight stability; with the support of the flight control algorithm, the aircraft can quickly switch between multiple flight modes such as vertical take-off and landing, hovering and horizontal cruising, significantly improving control sensitivity.

[0033] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A distributed vector exhaust ducted fan box-wing eVTOL, characterized in that: include: The box wing is composed of a front wing main wing (2), a front wing aileron (3) and a rear wing (5) connected by a joint wing edge (4) and fused with a fuselage (1) to form a closed box-shaped structure; A V-shaped tail (6), located at the tail of the aircraft and constituting the main lift part of the aircraft with the box-shaped wing; A plurality of electric ducted fans (7) with guide vane vector exhaust devices are arranged longitudinally along both sides of the fuselage, and each electric ducted fan (7) with a guide vane vector exhaust device on one side has a set angle with the horizontal direction of the fuselage, forming a power unit of the aircraft in the form of distributed power.

2. A distributed vector exhaust ducted fan box-wing eVTOL according to claim 1, characterized in that: Each electric ducted fan (7) with a guide vane vector exhaust device on one side has an angle of 30° with the horizontal direction of the fuselage.

3. The distributed vector exhaust ducted fan box-wing eVTOL according to claim 1, characterized in that: The electric ducted fan (7) with a guide vane vector exhaust device comprises: A novel aerodynamic lip air intake device (71), a ducted fan rotor (72) and a guide vane vector exhaust device (73); The ducted fan rotor (72) is located in the duct, the inlet of the duct is connected to the outlet of the novel pneumatic lip air intake device (71), and the outlet of the duct is connected to the guide vane vector exhaust device (73).

4. A distributed vector exhaust ducted fan box-wing eVTOL according to claim 3, characterized in that: The novel pneumatic lip air intake device (71) ensures a smooth transition of airflow from the outside to the inside by adding a guide plate to the air intake lip, and is used to provide an effective air intake area in vertical take-off and landing and horizontal cruising modes; The ducted fan rotor (72) is composed of a plurality of blades and is used to generate thrust; The guide vane vector exhaust device (73) is composed of a plurality of exhaust guide vanes, and is used to adapt to the requirements of different flight states by deflecting the exhaust guide vanes within a range of 0 to 90 degrees, and to provide additional control torque to enhance the accuracy of attitude control.

5. A distributed vector exhaust ducted fan box-wing eVTOL according to claim 4, characterized in that: In the vertical take-off and landing mode, the exhaust guide vanes of the guide vane type vector exhaust device (73) are deflected to a maximum angle of 90°, with the guide vanes pointing vertically downward; In the horizontal cruising mode, the exhaust guide vanes of the guide vane type vector exhaust device (73) are deflected to a minimum angle of 0°, with the guide vanes facing horizontally backwards.

6. A distributed vector exhaust ducted fan box-wing eVTOL according to claim 4, characterized in that: The deflection angle of the exhaust guide vanes of the guide vane type vector exhaust device (73) at the front and rear parts of the fuselage is adjusted by differential control to change the direction of the thrust vector, thereby generating a torque around the horizontal axis and achieving a pitch attitude.

7. The distributed vector exhaust ducted fan box-wing eVTOL according to claim 4, characterized in that: The exhaust guide vane angles of the left and right guide vane vector exhaust devices (73) of the fuselage (1) are adjusted to change the direction of the thrust vector, thereby generating a moment around the longitudinal axis to achieve a rolling attitude.

8. The distributed vector exhaust ducted fan box-wing eVTOL according to claim 4, characterized in that: The vector differential of the left and right ducted fan rotors (72) of the fuselage (1) is adjusted to generate a torque around the vertical axis to achieve a yaw attitude.

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