Dual powered electric aircraft

Abstract

The utility model is suitable for electric airplane field, provides a kind of dual-power electric airplane, the electric airplane includes fuselage with landing gear, wing unit is arranged in the middle part of the fuselage, empennage unit is arranged in the tail of the fuselage, front pull power unit is arranged on the wing unit and is placed in the head of wing unit, and rear push power unit is arranged on the wing unit and is placed in the wing root of wing unit, the front pull power unit with the rear push power unit is coaxial and is arranged oppositely.It aims at solving the technical problems of insufficient power redundancy of aircraft in the prior art, unable to utilize propeller slipstream to improve aerodynamic efficiency, and great challenge to the position of aircraft gravity center and internal space utilization rate caused by the installation position of power mechanism.

Description

Technical Field

[0001] This utility model belongs to the field of electric aircraft, and in particular relates to a dual-powered electric aircraft. Background Technology

[0002] Currently, existing electric aircraft use a single motor and propeller for power, which limits power output and results in insufficient safety redundancy. Furthermore, if either the motor or propeller fails, there is a risk of losing all power, making this approach less safe. Additionally, the aerodynamic efficiency and maneuverability of current electric aircraft need improvement. For example, there are two power layout options: a forward-pull layout, where the propeller slipstream only flows through the front of the fuselage, offering limited aerodynamic benefits to the wings and tail; and a tail-thrust layout, which, while improving nose visibility, can interfere with the tail section, leading to reduced maneuverability during flight. Moreover, a single high-power motor and its large propeller, whether located at the nose or tail, pose significant challenges to the aircraft's center of gravity and internal space utilization. Therefore, a power aircraft layout design that effectively improves power redundancy, aerodynamic efficiency, and flight stability is needed. Utility Model Content

[0003] The purpose of this invention is to provide a dual-powered electric aircraft, which aims to solve the technical problems of insufficient power redundancy in existing aircraft, the inability to improve aerodynamic efficiency by utilizing propeller slipstream, and the significant challenges to the aircraft's center of gravity and internal space utilization caused by the installation position of the power unit.

[0004] This invention is implemented as follows: a dual-powered electric aircraft, the electric aircraft including a fuselage with landing gear, a wing unit disposed in the middle of the fuselage, a tail unit disposed in the tail of the fuselage, a forward pull force unit disposed on the wing unit and located at the nose of the wing unit, and a rear thrust force unit disposed on the wing unit and located at the wing root of the wing unit, wherein the forward pull force unit and the rear thrust force unit are coaxially opposite each other.

[0005] A further technical solution of this utility model is: the wing unit includes a front fixed bracket and a rear fixed bracket disposed on the fuselage, and a wing disposed on the front fixed bracket and the rear fixed bracket.

[0006] A further technical solution of this utility model is: the wing is a delta wing with the angle between the two wings and the horizontal plane being 25°-30°, the tail ends of the two wings are provided with winglets, and the trailing edges of the tail ends of the two wings are provided with flaps.

[0007] A further technical solution of this utility model is: the tail wing unit includes a horizontal wing disposed on the fuselage and a vertical wing disposed on the fuselage.

[0008] A further technical solution of this utility model is: the forward pulling power unit includes a forward mounting bracket disposed on the wing unit, a forward power motor disposed on the forward mounting bracket, and a forward power propeller disposed on the forward power motor, wherein the forward power propeller has clockwise rotating blades.

[0009] A further technical solution of this utility model is: the rear propulsion unit includes an extended mounting shaft disposed on the wing unit, a rear mounting bracket disposed on the extended mounting shaft, a rear power motor disposed on the rear mounting bracket, and a rear power propeller disposed on the rear power motor, wherein the rear power propeller has counterclockwise rotating blades.

[0010] A further technical solution of this utility model is: the front thrust unit further includes a front fairing disposed on the front power propeller, and the rear thrust unit further includes a rear fairing disposed on the rear power propeller.

[0011] A further technical solution of this utility model is: the electric aircraft also includes a battery pack disposed on the fuselage and located inside the fuselage.

[0012] A further technical solution of this utility model is: the electric aircraft also includes a seat disposed on the fuselage and located inside the fuselage.

[0013] A further technical solution of this utility model is: the electric aircraft also includes a controller disposed on the fuselage, located inside the fuselage, and located on one side of the seat.

[0014] The beneficial effects of this invention are as follows: Compared with existing technologies, this electric aircraft has extremely high safety redundancy. The dual-power system provides a "single-engine failure" safety backup; even if one engine fails completely, the other can still provide power, enabling the aircraft to safely return or make an emergency landing, greatly improving the safety level of the electric aircraft. It also boasts excellent aerodynamic efficiency. Firstly, the slipstream of the forward propeller accelerates the airflow at the wing root, increasing wing lift. Secondly, the slipstream of the rear propeller directly acts on the tail (especially the horizontal stabilizer), enhancing control surface efficiency. Especially at low speeds and high angles of attack (such as takeoff and landing), it provides better pitch control. Simultaneously, the combined effect of the forward and rear slipstreams is equivalent to… It provides the aircraft with a "blowing" lift effect, which can shorten the takeoff and landing distance; it also has excellent flight stability, and the arrangement of the front and rear power units helps to keep the aircraft's center of gravity within an ideal range. At the same time, by controlling the forward and reverse rotation of the front and rear power propellers, the counter-torque can be completely offset, and the aircraft does not need to rely on the lateral force of the vertical tail to balance, reducing sideslip and improving directional stability, which is especially beneficial for low-speed flight; and it is also structurally compact. Compared with a single large propeller, the use of two smaller diameter propellers has optimized the rotational speed, thus producing less noise. At the same time, the distributed arrangement of the front and rear power units frees up effective space in the middle of the fuselage, which is convenient for load arrangement and equipment installation. Attached Figure Description

[0015] Figure 1 This is an overall structural diagram of a dual-powered electric aircraft provided in an embodiment of the present invention; Figure 2 This is an overall side view of a dual-powered electric aircraft provided in an embodiment of the present invention; Figure 3 This is a cross-sectional view of the power unit structure of a dual-powered electric aircraft provided in an embodiment of this utility model. Detailed Implementation

[0016] Reference numerals: 1-Landing gear; 2-Fuselage; 3-Wing unit; 4-Tail unit; 5-Front thrust unit; 6-Rear thrust unit; 7-Front fixed bracket; 8-Rear fixed bracket; 9-Wing; 10-Winglet; 11-Flap; 12-Horizontal wing; 13-Vertical wing; 14-Front mounting bracket; 15-Front drive motor; 16-Front drive propeller; 17-Extension mounting shaft; 18-Rear mounting bracket; 19-Rear drive motor; 20-Rear drive propeller; 21-Front fairing; 22-Rear fairing; 23-Battery pack; 24-Seat; 25-Controller.

[0017] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model.

[0018] In the description of this utility model, it should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, in the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0019] Figure 1-3 The present invention provides a dual-powered electric aircraft, which includes a fuselage 2 with landing gear 1, a wing unit 3 disposed in the middle of the fuselage 2, a tail unit 4 disposed at the tail of the fuselage 2, a forward pull force unit 5 disposed on the wing unit 4 and located at the head of the wing unit 4, and a rear thrust force unit 6 disposed on the wing unit 4 and located at the wing root of the wing unit 4. The forward pull force unit 5 and the rear thrust force unit 6 are arranged coaxially opposite each other. The electric aircraft is supported on the ground by landing gear 1 and is powered by a dual-power system consisting of a forward pull power unit 5 and a rear thrust power unit 6 located at the nose and root of wing unit 3, respectively. The forward pull power unit 5 provides forward pull force to the electric aircraft, while the rear thrust power unit 6 provides forward thrust force. Because it is a dual-power system, if one power unit fails, it will not completely lose power. The other power unit can still support the electric aircraft to return safely or make an emergency landing, which greatly improves the safety level of the electric aircraft. The coaxial arrangement of the forward pull power unit 5 and the rear thrust power unit 6 ensures that the axes of the two power units coincide or are nearly coincident. This is conducive to the two power forces working together and prevents the two power forces from acting separately.

[0020] The wing unit 3 includes a front fixed bracket 7 and a rear fixed bracket 8 mounted on the fuselage 2, and a wing 9 mounted on the front fixed bracket 7 and the rear fixed bracket 8. The wing 9 is mounted on the fuselage 2 via the front and rear fixed brackets. The front and rear fixed brackets raise the mounting position of the wing 9, thereby freeing up the effective space of the fuselage 2, which facilitates load arrangement and equipment installation.

[0021] The wing 9 is a delta wing with an angle of 25°-30° to the horizontal plane. Both wings of the wing 9 have winglets 10 at their tail ends, and both wings have flaps 11 at their trailing edges. The angle between the wings and the horizontal plane primarily optimizes flight performance by altering the geometry of the wing 9, improving stall characteristics and making the electric aircraft more stable at low speeds. It also reduces air resistance during cruise. The winglets 10 block upward airflow around the lower surface of the wing 9, reducing lift loss and induced drag. The winglets 10 also dissipate wingtip vortices; two vortices intertwine and interfere with each other, eventually dispersing into several vortices. This not only reduces induced drag but also minimizes the harm to following electric aircraft. The winglets 10 increase lift and forward thrust. The distorted flow field at the wingtip of wing 9 can be used to generate an inward lateral force, which can be decomposed into lift and forward thrust. The winglet 10 can delay airflow separation on the surface of wing 9 and increase stall angle of attack. When the air on the surface of upper wing 9 reaches the negative pressure peak and then recovers pressure, it will cause airflow separation and cause the aircraft to stall. As long as the winglet 10 is properly positioned, the pressure change at the wingtip of wing 9 will no longer be sharp and steep, reducing airflow separation and improving stall performance. The winglet 10 can effectively break wingtip vortices, increase the flight speed of electric aircraft, and shorten the flight time of the route. At the same time, due to the reduction of flight drag, the power consumption will also be reduced accordingly. The function of flap 11 is to increase lift by changing the airfoil camber, increasing the area of ​​wing 9, and maintaining laminar flow, especially increasing the lift of electric aircraft in low-speed phases such as takeoff and landing.

[0022] The tail unit 4 includes a horizontal wing 12 mounted on the fuselage 2 and a vertical wing 13 mounted on the fuselage 2. The tail unit 4 adopts a design of horizontal wing 12 plus vertical wing 13 to better utilize the slipstream of the rear-powered propeller, thereby increasing control surface efficiency and providing better pitch control for the electric aircraft at low speeds and high angles of attack.

[0023] The forward thrust unit 5 includes a forward mounting bracket 14 mounted on the wing unit 3, a forward motor 15 mounted on the forward mounting bracket 14, and a forward propeller 16 mounted on the forward motor 15. The forward propeller 16 has clockwise rotating blades. The forward thrust unit 5 is mounted on the wing unit 3 via the forward mounting bracket 14 and is powered by the forward motor 15 mounted on the forward mounting bracket 14 to drive the forward propeller 16 to rotate, thereby providing thrust to the electric aircraft. The clockwise rotating blades of the forward propeller 16 are chosen to counteract the torque of the rear propeller 20.

[0024] The rear thrust unit 6 includes an extended mounting shaft 17 mounted on the wing unit 3, a rear mounting bracket 18 mounted on the extended mounting shaft 17, a rear power motor 19 mounted on the rear mounting bracket 18, and a rear power propeller 20 mounted on the rear power motor 19. The rear power propeller 20 has counterclockwise rotating blades. The rear thrust unit 6 is mounted on the wing unit 3 via the extended mounting shaft 17 and the rear mounting bracket 18, and is powered by the rear power motor 19 mounted on the rear mounting bracket 18 to drive the rear power propeller 20 to rotate, thereby providing thrust to the electric aircraft. The counterclockwise rotating blades of the rear power propeller 20 are chosen to counteract the torsional balance with the front power propeller 16.

[0025] When selecting a power motor, the same model of motor is chosen, which greatly simplifies maintenance and parts management.

[0026] The front thrust unit 5 also includes a front fairing 21 mounted on the front propeller 16, and the rear thrust unit 6 also includes a rear fairing 22 mounted on the rear propeller 20. The fairings are used to adjust airflow and reduce air resistance, and also to protect the power motor from damage.

[0027] The electric aircraft also includes a battery pack 23 mounted on and located inside the fuselage 2. The battery pack 23 is installed to provide power to the various components that require power.

[0028] The electric aircraft also includes a seat 24 mounted on and located inside the fuselage 2. The seat 24 facilitates seating for passengers.

[0029] The electric aircraft also includes a controller 25 mounted on the fuselage 2, located inside the fuselage 2, and situated to one side of the seat 24. The electric aircraft connects to the front drive motor 15 and the rear drive motor 19 via the controller 25, allowing for independent or coordinated control of the power output of the two motors. The controller 25 is configured with multiple operating modes, including: a normal mode where the front and rear thrust units work together in a preset power ratio (e.g., 50% / 50%); a single-engine failure mode where, if one power unit fails, the power of the other power unit is automatically increased, and control surface adjustments are made to maintain flight; an efficient cruise mode where, during cruise, the power of one power unit is appropriately reduced to allow the electric aircraft to operate at its optimal aerodynamic efficiency point; and an anti-torque balance mode where the front or rear propellers are controlled to rotate in opposite directions to counteract the anti-torque generated by the propellers, reducing yaw and improving directional stability.

[0030] The controller 25 can receive control commands from the pilot and signals from various sensors (such as pitot tube and attitude indicator), and control the front and rear power motors. The controller 25 has multiple operating mode logics pre-stored. For example, during takeoff, the "normal mode" is activated, and both the front and rear power motors operate at maximum or high power. After entering cruise, it can switch to the "high-efficiency cruise mode", reducing the power of the front pull power unit 5 to 70% and the rear thrust unit 6 to 60% to find the optimal energy consumption point. If the sensor detects a sudden drop in the speed of the front pull power unit 5, it immediately switches to the "single-engine failure mode", increasing the power of the rear thrust unit 6 to 100% and automatically fine-tuning the rudder to compensate for asymmetric thrust, and vice versa.

[0031] Compared to existing technologies, this type of electric aircraft boasts extremely high safety redundancy. Its dual-power system provides a "single-engine failure" safety backup; even if one engine fails completely, the other can still provide power, enabling the aircraft to safely return or make an emergency landing, significantly enhancing the safety level of electric aircraft. It also exhibits superior aerodynamic efficiency. Firstly, the slipstream of the forward propeller accelerates the airflow at the wing root, increasing wing lift. Secondly, the slipstream of the rear propeller directly acts on the tail (especially the horizontal stabilizer), enhancing control surface efficiency, particularly at low speeds and high angles of attack (such as takeoff and landing), providing better pitch control. The combined effect of the forward and rear slipstreams effectively provides the aircraft with… The "blowing" lift effect can shorten takeoff and landing distances; it also provides excellent flight stability, and the arrangement of the front and rear power units helps to keep the aircraft's center of gravity within an ideal range. At the same time, by controlling the forward and reverse rotation of the front and rear power propellers, the counter-torque can be completely offset, and the aircraft does not need to rely on the lateral force of the vertical tail for balance, reducing sideslip and improving directional stability, which is especially beneficial for low-speed flight. Furthermore, it is structurally compact, and compared to a single large propeller, the use of two smaller diameter propellers optimizes the rotational speed, thus producing less noise. In addition, the distributed arrangement of the front and rear power units frees up effective space in the middle of the fuselage, facilitating load placement and equipment installation.

[0032] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A dual-powered electric aircraft, characterized in that: The electric aircraft includes a fuselage with landing gear, a wing unit located in the middle of the fuselage, a tail unit located at the tail of the fuselage, a forward pull force unit located on the wing unit and at the nose of the wing unit, and a rear thrust force unit located on the wing unit and at the wing root of the wing unit. The forward pull force unit and the rear thrust force unit are arranged coaxially opposite each other.

2. The electric aircraft according to claim 1, characterized in that, The wing unit includes a front fixed bracket and a rear fixed bracket mounted on the fuselage, and a wing mounted on the front fixed bracket and the rear fixed bracket.

3. The electric aircraft according to claim 2, characterized in that, The wing is a delta wing with an angle of 25°-30° between the two wings and the horizontal plane. Both wings are provided with winglets at their tail ends and flaps at their trailing edges.

4. The electric aircraft according to claim 3, characterized in that, The tail fin unit includes a horizontal wing disposed on the fuselage and a vertical wing disposed on the fuselage.

5. The electric aircraft according to any one of claims 1-4, characterized in that, The forward thrust unit includes a forward mounting bracket mounted on the wing unit, a forward thrust motor mounted on the forward mounting bracket, and a forward thrust propeller mounted on the forward thrust motor. The forward thrust propeller has clockwise rotating blades.

6. The electric aircraft according to claim 5, characterized in that, The rear propulsion unit includes an extended mounting shaft mounted on the wing unit, a rear mounting bracket mounted on the extended mounting shaft, a rear power motor mounted on the rear mounting bracket, and a rear power propeller mounted on the rear power motor. The rear power propeller has counterclockwise rotating blades.

7. The electric aircraft according to claim 6, characterized in that, The front thrust unit also includes a front fairing mounted on the front propeller, and the rear thrust unit also includes a rear fairing mounted on the rear propeller.

8. The electric aircraft according to claim 7, characterized in that, The electric aircraft also includes a battery pack disposed on the fuselage and located inside the fuselage.

9. The electric aircraft according to claim 8, characterized in that, The electric aircraft also includes a seat mounted on the fuselage and located inside the fuselage.

10. The electric aircraft according to claim 9, characterized in that, The electric aircraft also includes a controller that is mounted on the fuselage, located inside the fuselage, and positioned to the side of the seat.

Images