Electric tilt rotor aircraft

Abstract

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft shape design and control technology, and relates to an electric tiltrotor aircraft. Background Technology

[0002] An electric tiltrotor aircraft is a type of aircraft that combines the characteristics of helicopters and fixed-wing aircraft, achieving vertical takeoff and landing (VTOL) and efficient horizontal flight through tilting rotors. Its design typically employs multiple electric propulsion systems to improve flight efficiency, reduce noise, and decrease carbon emissions. The core technology of the tiltrotor lies in achieving a smooth transition from VTOL to horizontal cruise mode by adjusting the tilt angle of the rotor. This type of aircraft is suitable for urban air mobility (UAM), cargo transport, and emergency rescue, and has significant technological potential and application prospects.

[0003] The existing layout of aircraft has the following problems:

[0004] (1) When the rotor is installed on the tail fin, the airflow interference between the tilt rotor and the tail fin is large, which can easily cause pitch control difficulties during the tilt transition phase.

[0005] (2) A fixed rotor with a large number of blades is not conducive to drag reduction design during the cruise phase. Utility Model Content

[0006] To address the aforementioned technical problems, this utility model provides an electric tiltrotor aircraft that can achieve vertical take-off and landing, tilt transition, and cruise flight functions.

[0007] To achieve the above-mentioned technical objectives, this utility model provides the following technical solution:

[0008] An electric tiltrotor aircraft includes: a fuselage, two wings located on both sides of the fuselage, a tail, several struts located under the wings, and rotors located at both ends of the struts;

[0009] The rotor includes several tilting rotors and several fixed rotors;

[0010] The number of the struts is even, and they are arranged symmetrically on both sides of the fuselage in two equal groups; a tilting rotor is provided at the front end of each strut; and a fixed rotor is provided at the rear end of each strut.

[0011] The tilting rotor is connected to the front end of the support rod via a tilting mechanism, and the tilting mechanism is used to adjust the orientation of the tilting rotor.

[0012] Furthermore, the orientation of the tilt rotor can be adjusted within a 90° range from forward to upward;

[0013] A base is provided at the top of the rear end of the support rod, and the fixed rotor and the motor for driving the fixed rotor are mounted on the base, with all fixed rotors facing upwards.

[0014] Furthermore, the tilting rotor is a three-bladed variable-pitch rotor, and the fixed rotor is a two-bladed rotor.

[0015] Furthermore, the bottom of the tilt rotor is connected to a motor for driving the tilt rotor, and the motor for driving the tilt rotor is connected to a torque converter.

[0016] Furthermore, the tilting mechanism includes: a fixed end platform, a tilting end, a rotating spindle, an electric actuator, and an electric actuator controller;

[0017] One end of the fixed end frame is connected to the front end of the support rod, and the other end is rotatably connected to the tilting end via the rotating main shaft; and the electric actuator is connected to the tilting end; the electric actuator is used to drive the tilting end to rotate around the tilting main shaft;

[0018] The electric actuator is connected to the electric actuator controller, and the electric actuator controller is used to control the electric actuator;

[0019] The tilting end is connected to the motor used to drive the tilting rotor and the torque converter.

[0020] Furthermore, the number of struts is four, six, or eight; all struts are located below the wings, and the struts are arranged symmetrically in two groups on both sides of the fuselage, with the central axis of each strut parallel to the central axis of the fuselage; the number of tilt rotors and the number of fixed rotors are the same as the number of struts.

[0021] Furthermore, the number of support rods is four, and the number of tilting rotors and fixed rotors are both four.

[0022] Furthermore, the wing adopts a high-mounted gull-wing configuration.

[0023] Furthermore, the electric tiltrotor aircraft adopts a three-point landing gear.

[0024] Furthermore, the tail fin of the electric tiltrotor aircraft is an H-shaped tail fin.

[0025] The beneficial effects of this utility model are:

[0026] This utility model provides an electric tiltrotor aircraft with a novel layout, including a fuselage, wings (high-mounted gull-wing arrangement), struts, and an H-tail system, employing a tricycle landing gear and an eight-rotor configuration: four tiltrotor rotors (three-bladed variable-pitch rotors) and four fixed rotors (two-bladed rotors). In this layout design, the tiltrotor rotors are mounted at the front end of the struts, away from the tail. This layout effectively avoids airflow interference to the tail during operation, thereby improving the aerodynamic efficiency of the tail and maintaining stability in different flight modes. Furthermore, during the tilt transition phase, due to the forward-positioned rotors, the pitch moment is easier to control. The flight control system can adjust the rotor thrust distribution to achieve smoother pitch attitude adjustments, avoiding instability caused by turbulent airflow.

[0027] The electric tiltrotor aircraft provided by this invention features a two-bladed rotor at the rear end of its strut, which is kept in a feathered configuration during cruise flight, meaning the blades are parallel to the incoming airflow. This design minimizes aerodynamic drag on the rotor during cruise mode, improving flight efficiency. Furthermore, the rotor's location on the leeward side of the fuselage further reduces its adverse impact on overall aerodynamic performance, thereby minimizing energy loss, extending range, and enhancing the aircraft's cruise capability. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of an electric tiltrotor aircraft according to an embodiment of the present invention;

[0029] Figure 2 This is a schematic diagram of the connection between the tilting rotor and the strut in an embodiment of this utility model;

[0030] Figure 3 This is a schematic diagram of the tilting mechanism in an embodiment of the present invention.

[0031] Reference numerals: 1. Fuselage; 2. Wing; 3. Tail; 4. Strut; 5. Rotor; 6. Tilting mechanism; 7. Tilting end; 8. Electric actuator; 9. Rotating spindle; 10. Fixed end stand; 11. Motor; 12. Electric actuator controller; 13. Torque converter. Detailed Implementation

[0032] The technical solution of this utility model will be further described below with reference to specific embodiments and accompanying drawings.

[0033] Example 1: An electric tiltrotor aircraft, such as Figure 1 As shown, it includes: fuselage 1, two wings 2 located on both sides of the fuselage, tail 3, several struts 4 located under the wings, and rotors 5 located at both ends of the struts;

[0034] The rotor includes several tilting rotors and several fixed rotors; specifically, the number of tilting rotors and fixed rotors is the same, which is equal to the number of struts;

[0035] The number of the struts is even, and they are arranged symmetrically on both sides of the fuselage in two equal groups; a tilting rotor is provided at the front end of each strut (i.e., the end near the nose of the fuselage); and a fixed rotor is provided at the rear end of each strut (i.e., the end near the tail of the fuselage).

[0036] The tilting rotor is connected to the front end of the support rod via a tilting mechanism, and the tilting mechanism is used to adjust the orientation of the tilting rotor.

[0037] In this embodiment, the orientation of the tilt rotor can be adjusted within a range of 90° from forward to upward;

[0038] A base is provided at the top of the rear end of the support rod. The fixed rotor and the motor for driving the fixed rotor are mounted on the base, and all the fixed rotors are facing upwards. Specifically, the motor for driving the fixed rotor is fixedly connected to the base via a flange.

[0039] "Forward" refers to the direction facing the nose of the aircraft and parallel to the fuselage's central axis; "Upward" refers to the direction opposite to the direction of gravity when the aircraft is parked horizontally; specifically, all fixed rotors are set on the same horizontal plane; and when all tilt rotors are oriented in the same direction (such as all forward or all upward), all tilt rotors are on the same horizontal plane.

[0040] In this embodiment, the tilting rotor is a three-bladed variable-pitch rotor, and the fixed rotor is a two-bladed rotor.

[0041] Specifically, the three-bladed variable-pitch rotor used in this invention refers to a variable-pitch rotor with three blades, which is a conventional technology. The variable-pitch function allows the rotor to adjust the blade angle according to flight requirements to adapt to different flight modes (vertical takeoff, tilt transition, cruise, etc.).

[0042] In this embodiment, the bottom of the tilt rotor is connected to the motor driving the tilt rotor, and the motor driving the tilt rotor is connected to a torque converter. Specifically, the motor driving the tilt rotor and the motor driving the fixed rotor, both located on the same strut, are each connected to a battery, or to the same battery, with the battery positioned in the middle of the interior of the respective strut. The struts in the electric tilt rotor aircraft provided by this invention not only support the arrangement of the rotor system but also serve to house the battery, improving space utilization efficiency. In an electric tilt rotor aircraft, the battery is the primary energy source, and its placement directly affects the center of gravity and flight performance. By integrating the battery within the strut, this invention allows for a more rational weight distribution, improving overall weight balance and structural compactness. Furthermore, this layout reduces the need for additional fuselage structural design, making the aircraft lighter and improving endurance and payload capacity.

[0043] In this embodiment, as Figures 2-3 As shown, the tilting mechanism 6 includes: a fixed end frame 10, a tilting end 7, a rotating main shaft 9, an electric actuator 8, and an electric actuator controller 12;

[0044] One end of the fixed end frame is connected to the front end of the support rod (preferably by bolts), and the other end is rotatably connected to the tilting end via the rotating main shaft; and the electric actuator is connected to the tilting end; the electric actuator is used to drive the tilting end to rotate around the tilting main shaft;

[0045] The electric actuator is connected to the electric actuator controller, and the electric actuator controller is used to control the electric actuator;

[0046] The tilting end 7 is connected to the motor 11 for driving the tilting rotor and the torque converter 13.

[0047] In this invention, the tilting mechanism is connected to a motor and a pitch-changing machine at the tilting end to bear and transmit external loads; and to a tilting main shaft and an electric actuator at the rear end, rotating around the tilting main shaft under the drive of the electric actuator.

[0048] Specifically, the electric actuator includes a motor and a guide rod, the guide rod being a screw. A nut adapted to the screw is fixedly installed on the tilting end. The electric actuator is threadedly connected to the tilting end via the guide rod. The electric actuator controller controls the rotation direction and rotation time of the motor in the electric actuator, thereby controlling the rotation direction and rotation time of the guide rod. By controlling the rotation of the guide rod, the tilting end in the tilting mechanism is controlled to rotate around the tilting main axis. The guide rod is provided with horizontal and vertical limit points. When the nut on the tilting end reaches the horizontal limit point on the guide rod, the tilting rotor faces forward, and at this time, the central axis of the tilting rotor is parallel to the central axis of the support rod. When the nut on the tilting end reaches the vertical limit point on the guide rod, the tilting rotor faces upward, and at this time, the central axis of the tilting rotor is perpendicular to the central axis of the support rod. Preferably, the main body of the electric actuator (motor housing) is fixedly installed on the front end of the fixed end platform or the support rod, and the electric actuator controller is installed at the front end of the support rod. In this embodiment, the tilting mechanism at the front end of each strut has the same structure.

[0049] Specifically, the electric actuator and actuator controller are connected in a one-to-one manner, powered by 28VDC, and controlled by the host computer via a CAN bus. The power supply and control cables of the motors (including the motors for driving the tilt rotor and the motors for driving the fixed rotor) and the pitch converter pass through the tilt mechanism and are connected to the aircraft's energy system and signal control system, respectively.

[0050] In this embodiment, the number of support rods is four, six, or eight; specifically, the number of support rods is determined based on the fuselage weight. All support rods are located below the wings, and are arranged symmetrically in two groups on both sides of the fuselage, with the central axis of each support rod parallel to the fuselage's central axis. The number of tilt rotors and fixed rotors is the same as the number of support rods. Preferably, the number of support rods is four, and the number of tilt rotors and fixed rotors is also four.

[0051] In this embodiment, the wing adopts a high-mounted gull-wing configuration; the electric tiltrotor aircraft uses a tricycle landing gear; and the tail of the electric tiltrotor aircraft is an H-shaped tail. The electric tiltrotor aircraft provided by this invention employs an H-shaped tail design, utilizing the endplate effect to enhance the lift effect of the horizontal tail and improve pitch control capability. The essence of the endplate effect is to create a pressure difference on both sides of the tail, reducing fluid leakage and increasing lift efficiency, thereby enabling the tail to provide a larger pitch control moment within a smaller size. Furthermore, the twin vertical tail structure of the H-shaped tail can provide more stable directional control, allowing the aircraft to maintain good directional stability and crosswind resistance in different flight modes.

[0052] Specifically, in this embodiment, a cabin is arranged inside the fuselage in a 1+2+1 layout; and an additional luggage compartment is added near the third row of passengers to increase the overall safety of the cabin and prevent luggage from endangering passenger safety during severe shaking. 。

[0053] This utility model provides an electric tiltrotor aircraft capable of vertical takeoff and landing, tilt transition, and cruise flight. In vertical takeoff and landing mode, all rotors of the aircraft are in an upright position, similar to a traditional helicopter. At this time, the lift generated by the propellers is used entirely to overcome gravity, enabling the aircraft to take off or land vertically. During control, the thrust is adjusted by the throttle (motor or engine power), while the aircraft's attitude is fine-tuned through differential control of the rotors or auxiliary control surfaces (such as flaps and tail fins) to maintain stability and directional control.

[0054] After the aircraft completes vertical takeoff and ascends to a certain altitude, the tilt rotor gradually tilts forward, converting some of the thrust into forward propulsion, while the wings gradually begin to generate lift.

[0055] When the tiltrotor is fully tilted to a horizontal position, the aircraft enters cruise mode, and its flight behavior is similar to that of a fixed-wing aircraft. Lift is mainly provided by the wings, while the propeller is used entirely for forward propulsion. At this time, the aircraft relies on traditional aerodynamic control surfaces (such as ailerons, elevators, and rudders) to maintain attitude and directional control.

[0056] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. For those skilled in the art, they can still modify or improve the technical solutions described above, and these modifications and improvements are all within the protection scope of the present utility model.

Claims

1. An electric tiltrotor aircraft, characterized in that, include: The fuselage, two wings located on both sides of the fuselage, tail, several struts located under the wings, and rotors located at both ends of the struts; The rotor includes several tilting rotors and several fixed rotors; The number of the struts is even, and they are arranged symmetrically on both sides of the fuselage in two equal groups; a tilting rotor is provided at the front end of each strut; and a fixed rotor is provided at the rear end of each strut. The tilting rotor is connected to the front end of the support rod via a tilting mechanism, and the tilting mechanism is used to adjust the orientation of the tilting rotor.

2. The electric tiltrotor aircraft according to claim 1, characterized in that, The orientation of the tilt rotor can be adjusted within a 90° range from forward to upward; A base is provided at the top of the rear end of the support rod, and the fixed rotor and the motor for driving the fixed rotor are mounted on the base, with all fixed rotors facing upwards.

3. The electric tiltrotor aircraft according to claim 1, characterized in that, The tilting rotor is a three-bladed variable-pitch rotor, and the fixed rotor is a two-bladed rotor.

4. The electric tiltrotor aircraft according to claim 3, characterized in that, The bottom of the tilt rotor is connected to a motor for driving the tilt rotor, and the motor for driving the tilt rotor is connected to a torque converter.

5. An electric tiltrotor aircraft according to claim 4, characterized in that, The tilting mechanism includes: a fixed end frame, a tilting end, a rotating spindle, an electric actuator, and an electric actuator controller; One end of the fixed end frame is connected to the front end of the support rod, and the other end is rotatably connected to the tilting end via the rotating main shaft; and the electric actuator is connected to the tilting end; the electric actuator is used to drive the tilting end to rotate around the tilting main shaft; The electric actuator is connected to the electric actuator controller, and the electric actuator controller is used to control the electric actuator; The tilting end is connected to the motor used to drive the tilting rotor and the torque converter.

6. The electric tiltrotor aircraft according to claim 1, characterized in that, The number of struts is four, six, or eight; all struts are located below the wings, and the struts are arranged symmetrically in two groups on both sides of the fuselage, with the central axis of each strut parallel to the central axis of the fuselage; the number of tilt rotors and the number of fixed rotors are the same as the number of struts.

7. An electric tiltrotor aircraft according to claim 6, characterized in that, The number of support rods is four, and the number of tilting rotors and fixed rotors is also four.

8. An electric tiltrotor aircraft according to claim 1, characterized in that, The wing adopts a high-mounted gull-wing configuration.

9. An electric tiltrotor aircraft according to claim 1, characterized in that, The electric tiltrotor aircraft uses a three-point landing gear.

10. An electric tiltrotor aircraft according to claim 1, characterized in that, The tail of the electric tiltrotor aircraft is an H-shaped tail.

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