Full-tilting electric vertical take-off and landing aircraft

Abstract

The invention provides a full-tilting electric vertical take-off and landing aircraft which comprises an aircraft body, front wings, tilting propeller mechanisms, rear supporting arms and rear wings, the front wings are installed on the two sides of the front end of the aircraft body respectively, each front wing is further provided with one front supporting arm, and the tilting propeller mechanisms are installed at the tail ends of the front wings and the tail ends of the front supporting arms respectively. Rear wings are installed on the two sides of the tail end of the aircraft body respectively, each rear wing is further connected with a rear supporting arm, and the tail ends of the rear wings and the tail ends of the rear supporting arms are each provided with a tiltable propeller mechanism. The tilting angle of the tilting propeller mechanism ranges from 0 degree to 100 degrees, when the tilting angle of the tilting propeller mechanism is 0 degree, the aircraft is in a vertical take-off and landing mode, when the tilting angle of the tilting propeller mechanism is 90 degrees, the aircraft is in a horizontal cruise mode, and the safety design that the projection plane of the propeller does not penetrate through a cabin is achieved; meanwhile, the aircraft is remarkably improved in the aspects of noise control, reliability, aerodynamic performance and the like.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft, and particularly relates to a fully tilting electric vertical takeoff and landing aircraft. Background Art

[0002] As an innovative aircraft design that combines vertical takeoff and landing with efficient cruising, the core technologies of a fully tilting electric vertical takeoff and landing aircraft (eVTOL) include a tilting mechanism, a flight control system, a power system, and an aerodynamic layout. The synergistic effect of these technologies endows the fully tilting eVTOL with excellent performance, but there are still technical defects in terms of safety and noise in practical applications, which directly affect its airworthiness and commercial promotion.

[0003] The traditional fully tilting eVTOL in the prior art has the following disadvantages in the design and operation process. First of all, the projection plane of the propeller usually passes through the cockpit, increasing the risk of personnel injury caused by propeller failure. When the propeller has a mechanical failure (such as blade breakage or material fatigue failure), the high-speed rotating blades or debris may break off and directly threaten the safety of the occupants in the cockpit. Although some designs adopt protective measures, due to the large kinetic energy of the propeller debris, it is difficult to completely absorb and resist the impact force under the condition of high-speed operation.

[0004] Secondly, the layout design with the propeller projection plane covering the cockpit also brings potential operation hazards. During takeoff, landing or ground taxiing, the cockpit is in the direct action area of the propeller, and the aerodynamic and mechanical noise problems of the fully tilting eVTOL are particularly prominent. During the tilting transition process, the aerodynamic environment of the rotor changes violently, resulting in a significant increase in the noise of eddies and unsteady airflows. At the same time, the interference between the rotor downwash airflow and the wing or other airframe components further amplifies the noise.

[0005] Based on this, a fully tilting electric vertical takeoff and landing aircraft is proposed. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a fully tilting electric vertical takeoff and landing aircraft in view of the deficiencies of the above-mentioned prior art, so as to solve the problems raised in the above background art.

[0007] To solve the above technical problem, the technical solution adopted by the present invention is: a fully tilting electric vertical takeoff and landing aircraft, including an airframe, a front support arm, a front wing, a tiltable propeller mechanism, a rear support arm, and a rear wing; The front wings are respectively installed on both sides of the front end of the airframe, and each front wing is further installed with a front support arm. A tiltable propeller mechanism is installed at the wingtip of the front wing and the tail end of the front support arm respectively; On both sides of the tail end of the fuselage, rear wings are respectively installed, and each rear wing is further connected with a rear arm. At the wingtip of each rear wing and the tail end of each rear arm, a tiltable propeller mechanism is respectively installed. A supporting flight control system and power system are also arranged inside the fuselage.

[0008] As a further description of the present invention, the fuselage is the central load-bearing component of the aircraft, with a streamlined design. A cockpit is also arranged inside the fuselage. The front end of the fuselage is a transparent window, and the rear end of the fuselage is connected with the rear arm.

[0009] As a further description of the present invention, the tilt angle of the tiltable propeller mechanism is between 0° and 100°. When the tilt angle of the tiltable propeller mechanism is 0°, the eight sets of tiltable propeller mechanisms jointly provide lift, and at this time it is the vertical takeoff and landing mode of the aircraft. When the tilt angle of the tiltable propeller mechanism is 90°, the eight sets of tiltable propeller mechanisms jointly provide all the thrust required during the cruise stage, and at this time it is the horizontal cruise mode of the aircraft. At the same time, attitude control is carried out in cooperation with the differential speed of the tiltable propeller mechanism.

[0010] As a further description of the present invention, the power distribution system includes a battery module, an engine and a power transmission device; Among them, the battery module supplies energy to the engine, and the power generated by the engine is distributed to the propellers of each set of tiltable propeller mechanisms through the power transmission device, realizing independent thrust control of the tiltable propeller mechanisms.

[0011] The flight control system monitors the state of the propellers of the tiltable propeller mechanism in real time and controls the tilt angle of the tiltable propeller mechanism to enable the aircraft to switch between the vertical takeoff and landing mode and the horizontal cruise mode.

[0012] The present invention has the following advantages compared with the prior art: In the present invention, front wings are respectively installed on both sides of the front end of the fuselage, and each front wing is further installed with a front arm. At the wingtip of each front wing and the tail end of each front arm, a tiltable propeller mechanism is respectively installed. Rear wings are respectively installed on both sides of the tail end of the fuselage, and each rear wing is further connected with a rear arm. At the wingtip of each rear wing and the tail end of each rear arm, a tiltable propeller mechanism is respectively installed. The tilt angle of the tiltable propeller mechanism is between 0° and 100°. When the tilt angle of the tiltable propeller mechanism is 0°, the eight sets of tiltable propeller mechanisms jointly provide lift, and at this time it is the vertical takeoff and landing mode of the aircraft. When the tilt angle of the tiltable propeller mechanism is 90°, the eight sets of tiltable propeller mechanisms jointly provide all the thrust required during the cruise stage, and at this time it is the horizontal cruise mode of the aircraft. At the same time, attitude control is carried out in cooperation with the differential speed of the tiltable propeller mechanism.

[0013] In the present invention, the tiltable propeller mechanism is installed in the outer region of the wing of the airframe, ensuring that its projection plane does not overlap with the cockpit area in all flight modes. In the vertical takeoff and landing mode, the propeller tilt angle of the tiltable propeller mechanism is 0°, and the projection plane is completely located outside the wing of the airframe without crossing the cockpit area, generating the lift required for vertical takeoff. In the horizontal cruise mode, the propeller tilt angle of the tiltable propeller mechanism is 90°, and the axis of the propeller is parallel to the cockpit, providing forward thrust and further reducing the potential risk to the cockpit in case of failure.

[0014] The tilting mechanism of the tiltable propeller mechanism in the present invention adopts a high-precision hinge mechanism or an electric servo system, supporting continuous tilting of the propeller within the tilt angle range from 0° to 100°, ensuring the smoothness and rapidity of flight mode switching. The tilt angle is adjusted in real time through the flight control system, combined with sensor feedback data, to ensure a smooth transition between the vertical takeoff and landing mode and the horizontal cruise mode of the aircraft. The tiltable propeller mechanism takes into account aerodynamic interference, reduces the interference drag during the tilting process, and ensures excellent stability and controllability of the aircraft during mode conversion.

[0015] The propellers of the tiltable propeller mechanism in the present invention are installed in the outer region of the wing far from the airframe cockpit, reducing the influence of airflow disturbance on the cockpit and reducing noise at the source.

[0016] The power distribution system in the present invention includes a battery module, an engine, and a power transmission device. The battery module supplies energy to the engine, and the power generated by the engine is distributed to the propellers of each tiltable propeller mechanism through the power transmission device, realizing independent thrust control of the tiltable propeller mechanism and ensuring efficient energy utilization and thrust redundancy of the aircraft. Description of the Drawings

[0017] Figure 1 is the top view of the overall vertical takeoff and landing mode of the present invention; Figure 2 is the side view of the overall vertical takeoff and landing mode of the present invention; Figure 3 is the top view of the overall horizontal cruise mode of the present invention; Figure 4 is the side view of the overall horizontal cruise mode of the present invention; Figure 5 is the rear view of the overall horizontal cruise mode of the present invention; Description of the Reference Numerals: 1 - airframe; 2 - front wing; 21 - front support arm; 3 - tiltable propeller mechanism; 4 - rear support arm; 5 - rear wing. Detailed Embodiment

[0018] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0019] As Figures 1-5 shown, the present invention provides a technical solution: a fully tilt-rotor electric vertical takeoff and landing aircraft, including a fuselage 1, a front wing 2, a tilt-rotor mechanism 3, a rear arm 4, and a rear wing 5; The fuselage 1 is the central load-bearing component of the aircraft, designed in a streamlined shape, and a cockpit is also provided inside the fuselage 1. The front end of the fuselage 1 is a transparent window, and the rear end of the fuselage 1 is connected to the rear arm 4, which is used to provide the main load-bearing space of the aircraft. The optimized streamlined design enables the fuselage itself to have high aerodynamic efficiency.

[0020] The front wings 2 are respectively installed on both sides of the front end of the fuselage 1, and a front arm 21 is also installed on each front wing 2. A tilt-rotor mechanism 3 is respectively installed at the wingtip of the front wing 2 and the tail end of the front arm 21; The rear wings 5 are respectively installed on both sides of the rear end of the fuselage 1, and the rear arms 4 are respectively connected to each rear wing 5. A tilt-rotor mechanism 3 is respectively installed at the wingtip of the rear wing 5 and the tail end of the rear arm 4; A matching flight control system and power system are also provided inside the fuselage 1.

[0021] The tilt angle of the tilt-rotor mechanism 3 is between 0 - 100°. When the tilt angle of the tilt-rotor mechanism 3 is 0°, the eight tilt-rotor mechanisms 3 jointly provide lift. At this time, it is the vertical takeoff and landing mode of the aircraft. When the tilt angle of the tilt-rotor mechanism 3 is 90°, the eight tilt-rotor mechanisms 3 jointly provide all the thrust required during the cruise stage. At this time, it is the horizontal cruise mode of the aircraft, and attitude control is simultaneously performed in combination with the differential speed of the tilt-rotor mechanism 3.

[0022] The tilt-rotor mechanism 3 is installed in the external area of the wing of the fuselage 1 to ensure that its projection plane does not overlap with the cockpit area in all flight modes.

[0023] In the vertical takeoff and landing mode, the propeller tilt angle of the tilt-rotor mechanism 3 is 0°, and the projection plane is completely located outside the fuselage 1 without crossing the cockpit area, generating the lift required for vertical takeoff.

[0024] In the horizontal cruise mode, the propeller inclination angle of the tiltable propeller mechanism 3 is 90°, and the axis of the propeller is parallel to the cockpit, providing forward thrust to further reduce the potential risk to the cockpit in case of failure.

[0025] Moreover, the propellers of the tiltable propeller mechanism 3 are installed in the external wing area far from the cockpit of the airframe 1, reducing the influence of airflow disturbance on the cockpit and reducing noise from the source.

[0026] The tilting mechanism of the tiltable propeller mechanism 3 adopts a high-precision hinged mechanism or an electric servo system, supporting continuous tilting of the propeller within the tilting angle range from 0° to 100°, ensuring the smoothness and rapidity of flight mode switching. The tilting angle is adjusted in real time through the flight control system, combined with sensor feedback data, to ensure a smooth transition of the aircraft between the vertical takeoff and landing mode and the horizontal cruise mode. The tiltable propeller mechanism 3 takes into account aerodynamic interference, reduces the interference drag during the tilting process, and ensures excellent stability and controllability of the aircraft during mode conversion.

[0027] The power distribution system includes a battery module, an engine, and a power transmission device; Among them, the battery module supplies energy to the engine, and the power generated by the engine is distributed to the propellers of each tiltable propeller mechanism 3 through the power transmission device, realizing independent thrust control of the tiltable propeller mechanism 3, ensuring efficient energy utilization and thrust redundancy of the aircraft.

[0028] The flight control system monitors the state of the propellers of the tiltable propeller mechanism 3 in real time and controls the tilting angle of the tiltable propeller mechanism 3 to switch the aircraft between the vertical takeoff and landing mode and the horizontal cruise mode, realizing a safety design in which the projection plane of the propellers of the tiltable propeller mechanism 3 does not pass through the cockpit of the airframe 1. At the same time, significant improvements are achieved in multiple aspects such as noise control, reliability, and aerodynamic performance, ensuring the feasibility of the actual application and commercialization of the aircraft.

[0029] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device.

[0030] Although embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A fully tilting electric vertical takeoff and landing aircraft, characterized in that: It includes a fuselage (1), a front wing (2), a tiltable propeller mechanism (3), a rear arm (4) and a rear wing (5); On both sides of the front end of the fuselage (1), the front wings (2) are respectively installed. On each of the front wings (2), a front arm (21) is also installed. At the wingtip of the front wing (2) and the tail end of the front arm (21), a tiltable propeller mechanism (3) is respectively installed; On both sides of the rear end of the fuselage (1), the rear wings (5) are respectively installed. On each of the rear wings (5), a rear arm (4) is respectively connected. At the wingtip of the rear wing (5) and the tail end of the rear arm (4), a tiltable propeller mechanism (3) is respectively installed; A matching flight control system and power system are also arranged inside the fuselage (1).

2. The fully tilt-rotor electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The fuselage (1) is the central load-bearing component of the aircraft, with a streamlined design. A cockpit is also arranged inside the fuselage (1). The projection plane of the tiltable propeller mechanism (3) does not overlap with the cockpit area in all flight modes. The front end of the fuselage (1) is a transparent window, and the rear end of the fuselage (1) is connected to the rear arm (4).

3. The fully tilt-rotor electric vertical takeoff and landing aircraft according to claim 1, wherein The tilt angle of the tiltable propeller mechanism (3) is between 0 - 100°. When the tilt angle of the tiltable propeller mechanism (3) is 0°, the eight sets of tiltable propeller mechanisms (3) jointly provide lift. At this time, it is the vertical takeoff and landing mode of the aircraft. When the tilt angle of the tiltable propeller mechanism (3) is 90°, the eight sets of tiltable propeller mechanisms (3) jointly provide all the thrust required during the cruise stage. At this time, it is the horizontal cruise mode of the aircraft, and attitude control is carried out in cooperation with the differential speed of the tiltable propeller mechanism (3).

4. A fully tiltable electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The power distribution system includes a battery module, an engine and a power transmission device; Among them, the battery module supplies energy to the engine, and the power generated by the engine is distributed to the propellers of each tiltable propeller mechanism (3) through the power transmission device to realize the independent thrust control of the tiltable propeller mechanism (3).

5. A fully tilt-rotor electric vertical takeoff and landing aircraft according to claim 1, characterized in that, The flight control system monitors the propeller state of the tiltable propeller mechanism (3) in real time and controls the tilt angle of the tiltable propeller mechanism (3) to switch the aircraft between the vertical takeoff and landing mode and the horizontal cruise mode.

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