All-electric, vertical take-off and landing, high-capacity aircraft with folding double-flap wings

Abstract

A fully electric, vertical take-off and landing, high-capacity aircraft with folding bi-flapping wings, characterized in that it comprises a fuselage; the fuselage is provided with a cockpit on the upper surface of the forward end; the fuselage is provided with double rows of flapping wings, each arranged one behind the other on both sides of the upper surface of the fuselage; the fuselage is provided with multiple rudder rotors on both sides, located below the flapping wings; the fuselage is provided with multiple tail rotors at the rear end of the fuselage; and the fuselage is provided with landing gear below the fuselage.

Description

Technical area

[0001] The present invention relates to the field of ornithopters, in particular to a purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings. State of the art

[0002] Ornithopters are bionic aircraft that differ from fixed-wing and rotary-wing aircraft and mimic the wing beat of birds. Ornithopters are characterized by good flexibility, high efficiency, light weight, low noise, and good stealth. However, there is no high-capacity ornithopter for heavy transport, and the carrying capacity of ornithopters needs to be improved. Content of the invention

[0003] The technical problem to be solved by the present invention is to overcome the deficiencies of the above-mentioned technology and to provide a high-capacity, all-electric, vertical take-off and landing aircraft with folding double-flapping wings. A high-capacity, all-electric, vertical take-off and landing aircraft with folding double-flapping wings, comprising a fuselage; the fuselage is provided with a cockpit at the top of the front end; the fuselage is provided with double rows of flapping wings, each arranged one behind the other on both sides of the top of the fuselage; the fuselage is provided with a plurality of side rotors on both sides located below the flapping wings; the fuselage is provided with a plurality of tail rotors at the rear end of the fuselage; and the fuselage is provided with landing devices below the fuselage.

[0004] Furthermore, the hull has high capacity and large space and is made of titanium alloy and carbon fiber hull materials.

[0005] Furthermore, the center section of the fuselage features continuous rotor compartment airflow control devices to ensure vertical lift and descent performance and aerodynamic balance.

[0006] Furthermore, the side rotors and tail rotors can be rotated and folded.

[0007] Furthermore, the driving devices are wheel devices that are arranged at the front and rear of the lower part of the hull.

[0008] Furthermore, the propulsion devices of the entire aircraft include rotor devices, gear drive devices, hydraulic drive devices and auxiliary drive devices for propelling the aircraft.

[0009] Furthermore, the entire aircraft is also equipped with a control and operating module.

[0010] Furthermore, there are access doors and observation windows on both sides of the hull accommodation space.

[0011] Advantages of the invention are as follows: the invention has a reasonable structure, high capacity, large space and strong carrying capacity; the body made of titanium alloy, carbon fiber and other lightweight materials can effectively reduce the dead weight and improve the load; the double rows of flapping wings make full use of the aerodynamic forces, thereby enhancing the functions in flight and improving the efficiency of flight; the double rows of flapping wings can be folded, making it more convenient to retract and store. Short description of the drawings Fig. 1 is a three-dimensional schematic representation of an all-electric, high-capacity, vertical takeoff and landing aircraft with folding double flapping wings of the present invention; Fig. 2 is a schematic main view of an all-electric, high-capacity, vertical takeoff and landing aircraft with folding double flapping wings of the present invention; Fig. 3 is a schematic plan view of an all-electric, high-capacity, vertical takeoff and landing aircraft with folding double flapping wings of the present invention; Fig. 4 is a schematic bottom view of an all-electric, high-capacity, vertical takeoff and landing aircraft with folding double flapping wings of the present invention; Fig. 5 is a schematic right view of an all-electric, high-capacity, vertical takeoff and landing aircraft with folding double flapping wings of the present invention; Fig. 6 is a schematic illustration of a folded state of flapping wings of a high-capacity all-electric vertical takeoff and landing aircraft with folding double flapping wings of the present invention.

[0012] As shown in the figures: 1, fuselage; 2, cockpit; 3, flapping wing; 4, vertical rotor; 5, tail rotor; 6, wheel assembly; 7, access door; 8, observation window; 9, rotor compartment airflow guide device. Detailed description of the preferred embodiments

[0013] In describing the invention, it is to be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "top", "bottom", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate an orientation or positional relationship based on the orientation or positional relationship illustrated in the accompanying drawings and are used only to facilitate and simplify the description of the invention and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed, and function in a particular orientation, and are therefore not to be construed as limiting the invention.

[0014] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate a relative importance or implicitly specify the number of technical features specified. Thus, the features qualified as "first" and "second" may explicitly or implicitly include one or more such features, and in the description of the invention, "plural" means two or more, unless expressly and specifically limited.

[0015] When in the description of the embodiments of the present invention a feature is referred to as being "set," "fixed," "connected," or "mounted" on another feature, it may be set, fixed, connected, or mounted directly on the other feature or indirectly on the other feature.

[0016] In the description of the embodiments of the present invention, "some" means more than one, "several" means more than two; when "greater than," "less than," or "exceeding" are involved, they are to be understood as excluding that number; when "over," "under," or "within" are involved, they are to be understood as including that number. When "first" and "second" are used, they are to be understood as being used to distinguish technical features and are not to be understood as meaning or implying a relative importance or an implicit indication of the number of technical features specified, or an implicit indication of the order of the technical features specified.

[0017] The present invention is described in more detail below in conjunction with the accompanying drawings.

[0018] A purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings, as in Fig. 1, comprises a fuselage 1; the fuselage 1 is provided with a cockpit 2 at the top of the front end; the fuselage 1 is provided with double rows of flapping wings 3, each arranged one behind the other on both sides of the top of the fuselage 1; the fuselage 1 is provided with a plurality of side rotors 4 on both sides, which are located below the flapping wings 3; the fuselage 1 is provided with a plurality of tail rotors 5 at the rear end of the fuselage 1; and the fuselage 1 is provided with landing gear below the fuselage 1.

[0019] The hull 1 has a high capacity and a large space and is made of titanium alloy and carbon fiber hull materials to achieve a hull structure with high capacity and large carrying capacity, strengthen the hull 1 and the propulsion auxiliary devices, and significantly increase the loading weight. The middle section of the hull 1 has, as shown in Fig. 3, continuous rotor space airflow guide devices 9 to ensure vertical lifting and lowering performance and aerodynamic balance.

[0020] The side rotors 4 and the tail rotors 5 can be rotated and folded, with the side rotors 4 being able to provide lift and lower assistance, while the tail rotors 5 can be steered and retracted to adjust the balance during the takeoff and landing phases and to increase and boost the speed during the flight phase.

[0021] The driving devices are wheel devices 6, which are arranged at the front and rear of the lower part of the fuselage 1, which is practical for ground travel.

[0022] The propulsion devices of the entire aircraft include rotor devices, gear drive devices, hydraulic drive devices and auxiliary drive devices for propelling the aircraft.

[0023] The entire aircraft is also equipped with a control and operation module that facilitates the operation and control of the entire aircraft.

[0024] On both sides of the accommodation space of the fuselage 1 there are access doors 7 and observation windows 8.

[0025] The application of the double-row folding and retractable flapping wings of the present invention improves the main function of the ornithopter, which combines various advantages, and can fill the gap of the ornithopter in many fields.

[0026] The present invention and its embodiments are described above. Such description is not limiting, and what is shown in the accompanying drawings is only one embodiment of the present invention, and the actual structure is not limited thereto. In short, if a person skilled in the art, inspired by this, and without departing from the purpose of the present invention and without resorting to creative activity, devises structural methods and embodiments similar to the technical solution, they all fall within the scope of the present invention.

Claims

[1] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings, characterized by that it comprises a fuselage; the fuselage is provided with a cockpit on the upper side of the forward end; the fuselage is provided with double rows of flapping wings, one behind the other on either side of the upper side of the fuselage; the fuselage is provided with a plurality of side rotors on either side located below the flapping wings; the fuselage is provided with a plurality of tail rotors at the rear end of the fuselage; and the fuselage is provided with landing gear below the fuselage. [2] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that the hull has high capacity and large space and is made of titanium alloy and carbon fiber hull materials. [3] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that the center section of the fuselage has continuous rotor compartment airflow control devices to ensure vertical lift and descent performance and aerodynamic balance. [4] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that the side rotors and tail rotors can be rotated and folded. [5] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that the driving devices are wheel devices located at the front and rear of the lower part of the hull. [6] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that the propulsion devices of the entire aircraft include rotor devices, gear drive devices, hydraulic drive devices and auxiliary drive devices for propelling the aircraft. [7] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that the entire aircraft is also equipped with a control and operating module. [8] Purely electric vertical take-off and landing high-capacity aircraft with folding double flapping wings according to claim 1, characterized by that there are access doors and observation windows on both sides of the hull accommodation space.

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