An electric vertical take-off and landing aircraft

Abstract

The utility model relates to the technical field of aircraft, and disclose an electric vertical take-off and landing aircraft, including fuselage, the both sides of fuselage are provided with the wing, the bottom of both sides wing all is provided with the inner machine arm, the both sides of fuselage tail portion are provided with the horizontal tail, the horizontal tail with the inner machine arm is connected, can improve the structure rigidity of fuselage and inner machine arm rear portion, the tail portion of fuselage still is provided with the upper vertical tail and the lower vertical tail, and the total area and area ratio of upper vertical tail, lower vertical tail determine according to the lateral stability and the lateral control requirement of the heading stability limit after the fixed wing of whole machine. The utility model provides an electric vertical take-off and landing aircraft, has the advantages such as light structure weight, can change propeller arrangement mode according to different application scene and design index, solve the problem of relatively high cost of structure weight, new development for different application scene weight and design index.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an electric vertical takeoff and landing aircraft. Background Technology

[0002] Vertical takeoff and landing (VTOL) aircraft generally refer to a class of aircraft capable of taking off and landing vertically like helicopters, possessing hovering capabilities, and flying horizontally like fixed-wing aircraft. Benefiting from their convenient takeoff and landing and high flight efficiency, VTOL aircraft have significant military applications. There are three types of VTOL aircraft: rotorcraft, tiltrotorcraft, and tail-seatcraft. These types of aircraft can meet the needs of takeoff and landing in the confined spaces of urban areas. Their widespread application will contribute to the construction of urban three-dimensional transportation networks, effectively supplementing ground transportation and greatly alleviating the increasingly serious urban congestion problem. They represent a form of aircraft designed for future urban air traffic scenarios and are more in line with future integrated urban three-dimensional transportation systems.

[0003] Chinese invention patents with announcement number CN119611752A and application number CN202510032962.3 disclose an electric vertical takeoff and landing tiltrotor aircraft, including a fuselage, a front fixed wing, a rear fixed wing, a ducted coaxial dual-rotor tilting assembly, an aircraft landing gear, a power battery, and a flight control system. The electric vertical takeoff and landing tiltrotor aircraft provides directional thrust through the tilting of the ducted coaxial dual rotors. The aircraft can transition from hovering mode to transition mode, then to forward flight mode, and then back to hovering mode. This type of arrangement has a long force transmission path, resulting in a large structural weight of the aircraft. At the same time, the propeller arrangement of this type of aircraft generally only considers a single application scenario and design specifications, and developing new ones for different application scenarios and design specifications is costly.

[0004] Therefore, we propose an electric vertical takeoff and landing aircraft to solve the above problems. Utility Model Content

[0005] (a) Technical problems to be solved To address the shortcomings of existing technologies, this utility model provides an electric vertical takeoff and landing aircraft with advantages such as light structural weight and the ability to change the propeller arrangement according to different application scenarios and design specifications. It solves the problems of large structural weight, high cost of developing new designs for different application scenarios and design specifications.

[0006] (II) Technical Solution To achieve the aforementioned lightweight structure and the ability to modify the propeller arrangement according to different application scenarios and design specifications, this utility model provides the following technical solution: an electric vertical takeoff and landing (EVTOL) aircraft, comprising a fuselage, wings on both sides of the fuselage, and inner arms at the bottom of each wing; horizontal tail fins on both sides of the tail of the fuselage, connected to the inner arms to improve the structural rigidity of the fuselage and the rear of the inner arms; and upper and lower vertical tail fins at the tail of the fuselage, the total area and area ratio of the upper and lower vertical tail fins being determined according to the center of gravity limit of the fixed-wing aircraft in level flight. The requirements for stability, lateral stability, and directional maneuverability are determined. Depending on the specific requirements, only the upper or lower vertical tail may be installed. The wings and inner arms are equipped with power batteries, which can reduce the distance between the weight of the power batteries and the lift of the wings, thereby shortening the power transmission path. The front end of the inner arm is equipped with a tiltable first propeller. The wing ends away from the fuselage are each equipped with a first propeller mechanism. The top of the inner arm is equipped with a second propeller mechanism. The first propeller, the first propeller mechanism, and the second propeller mechanism are used to control the flight of the aircraft. The bottom of the fuselage is also equipped with landing gear.

[0007] As a further optimization of this utility model: the leading edge of the connection between the horizontal tail and the fuselage and the inner arm has an outer edge strip and an inner edge strip, respectively, which are used to improve the stall angle of attack of the horizontal tail, so that the stall of the horizontal tail is later than the stall of the wing, thereby improving the pitch stability of the whole aircraft at high angles of attack.

[0008] As a further optimization of this utility model: the leading and trailing edges of the connection between the upper vertical tail and the fuselage are respectively provided with a dorsal fin and an upper rudder, and the leading and trailing edges of the connection between the lower vertical tail and the fuselage are respectively provided with a ventral fin and a lower rudder. The dorsal fin, ventral fin, upper rudder and lower rudder are used to improve the stall angle of attack of the upper and lower vertical tails, thereby improving the heading stability of the whole aircraft at low speed and large sideslip angle.

[0009] As a further optimization of this utility model: the first propeller mechanism includes a second propeller, which can be tilted and mounted on the wing.

[0010] As a further optimization of this utility model: the first propeller mechanism includes an outer arm and a second propeller, the second propeller being tiltably disposed at both ends of the outer arm, and the middle part of the outer arm being connected to the wing.

[0011] As a further optimization of this utility model: the second propeller mechanism includes a third propeller, which is fixedly mounted on the inner arm.

[0012] As a further optimization of this utility model: the second propeller mechanism includes an arm vertical tail and a third propeller. The arm vertical tail is fixedly mounted on the inner arm, and the third propeller is tiltably mounted on the arm vertical tail. An arm rudder is also provided at the connection between the arm vertical tail and the inner arm. The vertical height length of the arm vertical tail is greater than the radius of the third propeller. If the arm vertical tail can provide satisfactory lateral and yaw stability and maneuverability, then the rear of the fuselage does not need to be equipped with a vertical tail and a lower vertical tail.

[0013] As a further optimization of this utility model: the power battery includes a left wing battery, an inner arm battery and a right wing battery. The left wing battery, the inner arm battery and the right wing battery are respectively distributed and installed on the wing and the inner arm. Some of the power batteries are installed at the front of the inner arm to facilitate the adjustment of the center of gravity.

[0014] As a further optimization of this utility model: the landing gear includes a nose landing gear and a main landing gear, the nose landing gear is located at the nose of the fuselage, and the main landing gear is located in the middle of the fuselage.

[0015] As a further optimization of this utility model, a tail propeller is also provided at the tail of the fuselage.

[0016] (III) Beneficial Effects Compared with the prior art, this utility model provides an electric vertical takeoff and landing aircraft, which has the following beneficial effects: 1. This electric vertical takeoff and landing aircraft, through modular design, can change the propeller arrangement according to different application scenarios and design specifications, which can reduce R&D costs, shorten the R&D cycle, and improve product competitiveness.

[0017] 2. This electric vertical takeoff and landing aircraft connects to the wing via a propeller using the shortest route, enabling a shared reinforcing structure and the shortest power transmission path. Compared to installing propellers on canards or V-tails, this significantly reduces the weight of the fuselage structure. Attached Figure Description

[0018] Figure 1 This is a top view of the overall structure of this utility model; Figure 2 This is a schematic diagram of the overall bottom view of the present invention; Figure 3 This is a schematic diagram of the power battery distribution structure of this utility model; Figure 4 , 5 This is a schematic diagram of the structure of a specific embodiment (1) of the present utility model; Figure 6 , 7 This is a schematic diagram of the structure of a specific embodiment (2) of the present utility model; Figure 8 , 9 This is a schematic diagram of the structure of a specific embodiment (3) of the present utility model; Figure 10 , 11 This is a schematic diagram of the structure of a specific embodiment (4) of the present utility model; Figure 12 , 13 This is a schematic diagram of the structure of a specific embodiment (5) of the present utility model; Figure 14 , 15 This is a schematic diagram of the structure of a specific embodiment (6) of the present utility model; Figure 16 , 17 This is a schematic diagram of the structure of a specific embodiment (7) of the present utility model; Figure 18 This is a schematic diagram of the structure of a specific embodiment (8) of the present utility model; Figure 19 This is a schematic diagram of the structure of a specific embodiment (9) of the present utility model.

[0019] In the diagram: 1. Inner arm; 2. Fuselage; 3. Wing; 4. Flapillar; 5. Outer strake; 6. Horizontal tail; 7. Dorsal fin; 8. Upper vertical tail; 9. Upper rudder; 10. Inner strake; 11. Elevator; 12. Arm rudder; 13. Arm vertical tail; 14. Lower rudder; 15. Lower vertical tail; 16. Ventral fin; 17. Main landing gear; 18. Nose landing gear; 19. Left wing battery; 20. Inner arm battery; 21. Right wing battery; 22. Outer arm; 23. Tail thruster; 24. Second propeller; 25. First propeller; 26. Third propeller. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0021] Please see Figure 1-3An electric vertical takeoff and landing (EVTOL) aircraft includes a fuselage 2, wings 3 on both sides of the fuselage 2, and inner arms 1 at the bottom of each wing 3. Horizontal tails 6 are located on both sides of the tail of the fuselage 2, connected to the inner arms 1, which improves the structural rigidity of the rear of the fuselage 2 and inner arms 1. The tail of the fuselage 2 also includes an upper vertical tail 8 and a lower vertical tail 15. The total area and area ratio of the upper vertical tail 8 and lower vertical tail 15 are determined according to the requirements of directional stability, lateral stability, and directional controllability at the center of gravity limit after the aircraft is in level flight. Specific requirements may include installing only the upper vertical tail 8 or the lower vertical tail 15. The wings 3 and the inner arm 1 are equipped with power batteries, which can reduce the distance between the weight of the power battery and the lift of the wings 3, thereby shortening the power transmission path. The front end of the inner arm 1 is equipped with a tiltable first propeller 25. The wing 3 is equipped with a first propeller mechanism at the end away from the fuselage 2. The top of the inner arm 1 is equipped with a second propeller mechanism. The first propeller 25, the first propeller mechanism, and the second propeller mechanism are used to control the flight of the aircraft. The bottom of the fuselage 2 is also equipped with landing gear.

[0022] The leading edges of the horizontal tail 6 where it connects to the fuselage 2 and the inner arm 1 are respectively equipped with outer strakes 5 and inner strakes 10, which are used to increase the stall angle of attack of the horizontal tail 6, so that the stall of the horizontal tail 6 is later than the stall of the wing 3, thereby improving the pitch stability of the whole aircraft at high angles of attack. The leading and trailing edges of the upper vertical tail 8 where it connects to the fuselage 2 are respectively equipped with a dorsal fin 7 and an upper rudder 9, and the leading and trailing edges of the lower vertical tail 15 where it connects to the fuselage 2 are respectively equipped with a ventral fin 16 and a lower rudder 14. The dorsal fin 7, ventral fin 16, upper rudder 9 and lower rudder 14 are used to increase the stall angle of attack of the upper vertical tail 8 and the lower vertical tail 15, thereby improving the directional stability of the whole aircraft at low speed and large sideslip angle.

[0023] The first propeller mechanism includes a second propeller 24, which is tiltably mounted on the wing 3; the first propeller mechanism includes an outer arm 22 and a second propeller 24, which is tiltably mounted at both ends of the outer arm 22, and the middle part of the outer arm 22 is connected to the wing 3.

[0024] The second propeller mechanism includes a third propeller 26, which is fixedly mounted on the inner arm 1. The second propeller mechanism includes an arm vertical tail 13 and a third propeller 26. The arm vertical tail 13 is fixedly mounted on the inner arm 1, and the third propeller 26 can be tilted and mounted on the arm vertical tail 13. An arm rudder 12 is also provided at the connection between the arm vertical tail 13 and the inner arm 1. The vertical length of the arm vertical tail 13 is greater than the radius of the third propeller 26. If the arm vertical tail 13 can provide satisfactory lateral and directional stability and maneuverability, the vertical tail 8 and the lower vertical tail 15 do not need to be installed on the rear of the fuselage.

[0025] The power battery includes a left wing battery 19, an inner arm battery 20, and a right wing battery 21. The left wing battery 19, the inner arm battery 20, and the right wing battery 21 are respectively distributed and installed on the wing 3 and the inner arm 1. Some power batteries are also installed at the front of the inner arm 1 to facilitate the adjustment of the center of gravity. The landing gear includes a nose landing gear 18 and a main landing gear 17. The nose landing gear 18 is located at the nose of the fuselage 2, and the main landing gear 17 is located in the middle of the fuselage 2. A tail thruster 23 is also provided at the tail of the fuselage 2.

[0026] Operating principle: When the first propeller 25, the second propeller 24, and the third propeller 26 are in a vertical position, vertical takeoff and landing and hovering in the air are possible. When the first propeller 25, the second propeller 24, and the third propeller 26 are tilted to an angle between vertical and horizontal, forward flight in the air and short takeoff and landing on the ground are possible. When the first propeller 25, the second propeller 24, and the third propeller 26 are tilted forward to a horizontal position, the aircraft can fly horizontally in the air like a conventional fixed-wing aircraft, and can also achieve horizontal takeoff and landing on the ground.

[0027] When flying forward, the overall control method is the same as that of a conventional fixed-wing aircraft. When flying at low speed and hovering, the control method is the same as that of a multi-propeller aircraft. The thrust of each propeller can be adjusted by changing the rotation speed and collective pitch.

[0028] The bending moment at the wing root of wing 3 caused by fuselage 2 and its internal loads will also be reduced, as will the load on the fuselage frame and beams, thereby reducing structural weight. Since wing 3 can withstand the entire weight of the aircraft and normal overload, all propellers can be connected to the wing via the shortest path, enabling a shared reinforcing structure and minimizing the force transmission path. Compared to installing propellers on canards or V-tails, this significantly reduces the structural weight of the fuselage.

[0029] To adapt to different application scenarios and design specifications, reduce R&D risks and costs, and improve product competitiveness, multiple implementation and installation methods are provided. The specific implementation methods are as follows: (1) Remove the vertical tail 13 of the arm and directly install the non-tilting third propeller 26 on the inner arm 1 to form a 6-propeller 4-tilting configuration. When flying forward, only the wingtip of the wing 3 and the four first propellers 25 and the second propeller 24 at the front of the inner arm 1 tilt forward to a horizontal state, such as Figure 4 and Figure 5 As shown.

[0030] (2) Remove the first propeller 25 at the wingtip of wing 3, and install an outer arm 22 at the wingtip of wing 3, wherein the front end of the outer arm 22 is equipped with a tiltable first propeller 25, and the rear end is equipped with a tiltable first propeller 25, forming an 8-propeller 8-tilt configuration, as shown. Figure 6 and Figure 7 As shown.

[0031] (3) Remove the first propeller 25 at the wingtip of wing 3, and install an outer arm 22 at the wingtip of wing 3. The front end of the outer arm 22 is equipped with a tiltable first propeller 25, and the rear end is equipped with a non-tiltable first propeller 24, forming an 8-propeller, 6-tilt configuration. Figure 8 and Figure 9 As shown.

[0032] (4) Remove the vertical tail 13 of the arm and directly install the non-tilting third propeller 26 onto the inner arm 1. At the same time, remove the first propeller 25 at the wingtip of the wing 3 and install the outer arm 22 at the wingtip of the wing 3. The front end of the outer arm 22 is equipped with the tilting first propeller 25, and the rear end is equipped with the tilting first propeller 25, forming an 8-propeller 6-tilting configuration two, as shown. Figure 10 and Figure 11 As shown.

[0033] (5) Remove the vertical tail 13 of the arm and directly install the non-tilting third propeller 26 onto the inner arm 1. At the same time, remove the first propeller 25 at the wingtip of the wing 3 and install the outer arm 22 at the wingtip of the wing 3. The front end of the outer arm 22 is equipped with the tilting first propeller 25, and the rear end is equipped with the non-tilting first propeller 25, forming an 8-propeller 4-tilting configuration. Figure 12 and Figure 13 As shown.

[0034] (6) Remove the first propeller 25 at the wingtip of wing 3, and install an outer arm 22 at the wingtip of wing 3, wherein the first non-tilting propeller 25 is installed at both the front and rear ends of the outer arm 22, forming an 8-propeller 4-tilting configuration two, as shown. Figure 14 and Figure 15 As shown.

[0035] (7) Remove the vertical stabilizer 13 of the arm and directly install the non-tilting third propeller 26 onto the inner arm 1. At the same time, remove the first propeller 25 at the wingtip of the wing 3 and install the outer arm 22 at the wingtip of the wing 3, wherein the non-tilting first propeller 25 is installed at both the front and rear ends of the outer arm 22, forming an 8-propeller 2-tilting configuration, as shown. Figure 16 and Figure 17 As shown.

[0036] (8) Multiple non-tilting first propellers 25 and third propellers 26 mounted on the inner arm 1 or outer arm 22 can be used to provide lift for vertical takeoff and hovering. A tail thruster 23 is added at the tail of the fuselage 2 to provide thrust during forward flight, and the vertical tail 13 of the arm is removed, thus forming a compound wing configuration of lift propeller + thrust propeller, such as Figure 18 As shown.

[0037] (9) Remove the vertical stabilizer 13 and the outer arm 22, adjust the area of ​​the upper vertical stabilizer 8 and the lower vertical stabilizer 15 on the fuselage 2, and arrange the non-tilting second propeller 24 only at the front of the inner arm 1, such as Figure 19 As shown, this configuration can form a conventional electric twin-engine fixed-wing aircraft.

[0038] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An electric vertical takeoff and landing aircraft, comprising a fuselage, characterized in that: The fuselage (2) is provided with wings (3) on both sides, and an inner arm (1) is provided at the bottom of each wing (3). Horizontal tail fins (6) are provided on both sides of the tail of the fuselage (2), and the horizontal tail fins (6) are connected to the inner arm (1). The tail of the fuselage (2) is also provided with an upper vertical tail (8) and a lower vertical tail (15). Power batteries are provided on the top of the wings (3) and the inner arm (1). A tiltable first propeller (25) is provided at the front end of the inner arm (1). A first propeller mechanism is provided at the end of the wing (3) away from the fuselage (2). A second propeller mechanism is provided on the top of the inner arm (1). The first propeller (25), the first propeller mechanism, and the second propeller mechanism are used to control the flight of the aircraft. Landing gear is also provided at the bottom of the fuselage (2).

2. The electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The leading edge of the horizontal tail (6) at the connection with the fuselage (2) and the inner arm (1) has an outer edge strip (5) and an inner edge strip (10) respectively, which are used to increase the stall angle of attack of the horizontal tail (6).

3. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The upper vertical tail (8) is provided with a dorsal fin (7) and an upper rudder (9) at the front and rear edges where it connects to the fuselage (2), and the lower vertical tail (15) is provided with a ventral fin (16) and a lower rudder (14) at the front and rear edges where it connects to the fuselage (2). The dorsal fin (7), ventral fin (16), upper rudder (9) and lower rudder (14) are used to increase the stall angle of attack of the upper vertical tail (8) and the lower vertical tail (15).

4. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The first propeller mechanism includes a second propeller (24), which is tiltably mounted on the wing (3).

5. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The first propeller mechanism includes an outer arm (22) and a second propeller (24). The second propeller (24) is tiltably disposed at both ends of the outer arm (22), and the middle part of the outer arm (22) is connected to the wing (3).

6. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The second propeller mechanism includes a third propeller (26), which is fixedly mounted on the inner arm (1).

7. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The second propeller mechanism includes a boom tail (13) and a third propeller (26). The boom tail (13) is fixedly mounted on the inner boom (1), and the third propeller (26) is tiltably mounted on the boom tail (13). A boom rudder (12) is also provided at the connection between the boom tail (13) and the inner boom (1).

8. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The power battery includes a left wing battery (19), an inner arm battery (20), and a right wing battery (21), which are respectively installed on the wing (3) and the inner arm (1).

9. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The landing gear includes a nose landing gear (18) and a main landing gear (17), with the nose landing gear (18) located at the head of the fuselage (2) and the main landing gear (17) located in the middle of the fuselage (2).

10. An electric vertical takeoff and landing aircraft according to claim 1, characterized in that: The tail of the fuselage (2) is also provided with a tail thruster (23), and the top of the wing (3) is also provided with a flaperon (4).

Images