All-electric, manned short takeoff and landing bionic ornithopter

Abstract

A fully electrically powered and manned short takeoff and landing bionic ornithopter, characterized in that it comprises a fuselage, two main flapping wings, two auxiliary flapping wings, a tail wing, two rudder rotors, two tail rotors, a cockpit, and ground handling equipment; the cockpit is located at the top of the forward end of the fuselage; the two main flapping wings are located on both sides of the fuselage and behind the cockpit; the two auxiliary flapping wings are located on both sides of the fuselage and below the trailing ends of the main flapping wings; the tail wing is located at the rear end of the fuselage; the two rudder rotors are located on both sides of the fuselage and below the main flapping wings; the two tail rotors are located at the rear of the fuselage and on both sides of the tail wing; and the ground handling equipment is located on the underside of the fuselage in the form of wheels.

Description

Technical area

[0001] The present invention relates to the technical field of manned aircraft, in particular to a purely electrically powered and manned short takeoff and landing bionic ornithopter. State of the art

[0002] Existing fixed-wing aircraft on the market have demanding space requirements, high noise levels, high energy consumption, complex structures, and high construction costs. Existing rotary-wing aircraft exhibit very low aerodynamic efficiency, poor flight stability, and poor interference suppression performance. This has a major impact on the deployment of rotary-wing aircraft.

[0003] The ornithopter is a bionic aircraft that utilizes the principle of aerodynamic force generated by mimicking natural flying creatures. Its unique feature is that it can utilize the ideal bionic effect to achieve greater lift through lift mechanisms such as capturing wake airflow, thus saving energy. Its aerodynamic efficiency is higher than that of fixed-wing and rotary-wing aircraft despite its small size. However, ornithopters currently have difficulty taking off and still require a large amount of space for landing.

[0004] Therefore, the questions of how to achieve short-distance takeoffs and landings and stable flight under existing technical conditions and how to use electrical energy to solve the problem of high fuel energy consumption are problems that need to be urgently solved by the experts in this field. Content of the invention

[0005] The technical problem to be solved by the present invention is to overcome the deficiencies of the above-mentioned technology and to provide a purely electrically powered and manned short takeoff and landing bionic ornithopter.

[0006] A purely electrically powered and manned short takeoff and landing bionic ornithopter comprising a fuselage, two main flapping wings, two auxiliary flapping wings, a tail wing, two side rotors, two tail rotors, a cockpit and ground landing gear; The cockpit is located at the top of the front end of the fuselage; the two main flapping wings are located on either side of the fuselage and behind the cockpit; the two auxiliary flapping wings are located on either side of the fuselage and below the rear ends of the main flapping wings; the tail wing is located at the rear end of the fuselage; the two side rotors are located on either side of the fuselage and below the main flapping wings; the two tail rotors are located at the rear of the fuselage and on either side of the tail wing, and the ground driving devices are located on the lower side of the fuselage in the form of wheels.

[0007] Furthermore, the fuselage structure is made of carbon fiber and titanium alloy with high strength and low weight.

[0008] Furthermore, the main flapping wings adopt a folding and retracting mode, and the folding manner of the main flapping wings includes an upper folding or a side folding.

[0009] Furthermore, the fuselage is provided with rotor compartments on both sides, with the side rotors being connected to the fuselage by rotating brackets and the side rotors being able to be folded into the rotor compartments by the rotating brackets.

[0010] It further comprises a propulsion system, wherein the propulsion system adopts a purely electric propulsion mode, wherein the main flapping wings, the auxiliary flapping wings, the tail wing, the side rotors, the tail rotors and the ground driving devices are all electrically driven.

[0011] Furthermore, the transmission mechanism of the main flapping vanes and the auxiliary flapping vanes adopts the lever principle, gear transmission, hydraulic transmission and auxiliary drive for synchronous operation.

[0012] Furthermore, the cockpit is an independent system with modular components to facilitate installation.

[0013] Furthermore, the underside of the fuselage is provided with wheel retraction compartments for stowing the wheels of the ground travel devices, wherein the wheels of the ground travel devices are connected to the fuselage by retraction mechanisms.

[0014] Furthermore, the change in the state of the auxiliary flapping wings and the tail wing can control the flight attitude and direction of the bionic ornithopter.

[0015] The advantages of the present invention compared with existing technology are as follows: the present invention has a reasonable and compact structure, convenient operation, and easy manufacturing; it features foldable flapping wings, has a compact structure when folded, and is convenient for driving and parking on the ground; the retractable multi-rotor system enables short takeoffs and landings with comfortable mid-air transitions and free flight and stopping; pure electric power makes this product environmentally friendly, energy-saving, and silent in operation; the structure uses titanium alloy and carbon fiber, which can greatly reduce energy consumption costs during operation and use.With novel appearance and strong market influence, it can replace existing aircraft and ground vehicles and be widely used in many fields such as transportation, travel, entertainment, leisure, competition, transportation and military.; Short description of the drawings Fig. 1 is a first three-dimensional schematic representation of a purely electrically powered and manned short takeoff and landing bionic ornithopter of the present invention; Fig. 2 is a second three-dimensional schematic representation of a purely electric-powered and manned short takeoff and landing bionic ornithopter of the present invention; Fig. 3 is a schematic diagram of a folded state of main flapping wings of a purely electric-powered and manned short takeoff and landing bionic ornithopter of the present invention.

[0016] As shown in the figures: 1, fuselage; 2, main flapping wing; 3, auxiliary flapping wing; 4, tail wing; 5, vertical rotor; 6, tail rotor; 7, cockpit; 8, wheel; 9, rotating mount; 10, rotor compartment. Detailed description of the preferred embodiments

[0017] 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.

[0018] Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be understood as indicating a relative importance or implicitly determining 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.

[0019] 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.

[0020] 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.

[0021] The present invention is described in more detail below in conjunction with the accompanying drawings.

[0022] With reference to the Fig. 1 to 3, a purely electrically powered and manned short takeoff and landing bionic ornithopter comprises a fuselage 1, two main flapping wings 2, two auxiliary flapping wings 3, a tail wing 4, two side rotors 5, two tail rotors 6, a cockpit 7 and ground landing devices; the cockpit 7 is located at the top of the forward end of the fuselage 1; the two main flapping wings 2 are located on both sides of the fuselage 1 and behind the cockpit 7; the two auxiliary flapping wings 3 are located on both sides of the fuselage 1 and below the rear ends of the main flapping wings 2; the tail wing 4 is located at the rear end of the fuselage 1; the two side rotors 5 are located on both sides of the fuselage 1 and below the main flapping wings 2; the two tail rotors 6 are located at the rear of the fuselage 1 and on both sides of the tail wing 4, and the ground driving devices are located on the lower side of the fuselage 1 in the form of wheels 8.

[0023] The fuselage 1 has a high-strength and light-weight carbon fiber and titanium alloy fuselage structure, which makes it high-strength and light-weight.

[0024] The main flapping wings 2 adopt a folding and retracting mode, and the folding manner of the main flapping wings 2 includes an upper folding or a side folding. Fig. 3 shows a folding method of the main flapping wings 2 which is suitable for reducing the space required while driving or when parking on the ground.

[0025] The fuselage 1 is provided with rotor compartments 10 on both sides, wherein the side rotors 5 are connected to the fuselage 1 by rotatable brackets 9 and the side rotors 5 can be folded into the rotor compartments 10 by the rotatable brackets 9.

[0026] It further comprises a propulsion system, wherein the propulsion system adopts a purely electric propulsion mode, wherein the main flapping wings 2, the auxiliary flapping wings 3, the tail wing 4, the side rotors 5, the tail rotors 6 and the ground driving devices are all electrically driven.

[0027] The transmission mechanism of the main flapping vanes 2 and the auxiliary flapping vanes 3 adopts the lever principle, the gear transmission, the hydraulic transmission and the auxiliary drive for synchronous operation.

[0028] The Cockpit 7 is a standalone system with modular components to facilitate installation.

[0029] The underside of the fuselage 1 is provided with wheel retraction compartments for stowing the wheels 8 of the ground travel devices, wherein the wheels 8 of the ground travel devices are connected to the fuselage 1 by retraction mechanisms.

[0030] The change in state of the auxiliary flapping wings 3 and the rear wing 4 can control the flight attitude and direction of the bionic ornithopter.

[0031] The multi-rotor system of the present invention, i.e., the combination of side rotors 5 and tail rotors 6, supports the takeoff and landing operation. In particular, in the short takeoff state, the folded main flapping wings 2 are unfolded, the side rotors 5 are rotated and released from the rotor compartments 10, which are activated to cause an upward movement of the entire aircraft. At the same time, the tail rotors 6 are rotated and extended and activated to cause a forward movement of the entire aircraft, so that the short takeoff can be realized and the flight mode can be activated. During landing, the side rotors 5 are rotated and released to achieve a short landing.During normal flight, the side rotors 5 are retracted, and the tail rotors 6 can also be closed (retracted) to enter a flapping flight state, and the tail rotors 6 can also be rotated and extended to assist in amplifying and improving kinetic energy during normal flight.;

[0032] In the implementation of the invention, the appearance can be sprayed with colors, and when it flies in the air, it is as colorful as the appearance of a bird.

[0033] 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 electrically powered and manned short take-off and landing bionic ornithopter, characterized by that it comprises a fuselage, two main flapping wings, two auxiliary flapping wings, a tail wing, two horizontal rotors, two tail rotors, a cockpit and ground landing gear; the cockpit is located at the top of the forward end of the fuselage; the two main flapping wings are located on either side of the fuselage and behind the cockpit; the two auxiliary flapping wings are located on either side of the fuselage and below the rear ends of the main flapping wings; the tail wing is located at the rear end of the fuselage; the two horizontal rotors are located on either side of the fuselage and below the main flapping wings; the two tail rotors are located at the rear of the fuselage and on either side of the tail wing, and the ground landing gear is located on the lower side of the fuselage in the form of wheels. [2] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the hull has a carbon fiber and titanium alloy hull structure with high strength and low weight. [3] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the main flapping wings adopt a folding and retracting mode, and the folding mode of the main flapping wings includes an upper folding or a side folding. [4] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the fuselage is provided with rotor compartments on both sides, whereby the side rotors are connected to the fuselage by rotating brackets and the side rotors can be folded into the rotor compartments by the rotating brackets. [5] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that it further comprises a propulsion system, the propulsion system adopting a purely electric propulsion mode, the main flapping wings, the auxiliary flapping wings, the tail wing, the side rotors, the tail rotors and the ground driving devices all being electrically driven. [6] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the transmission mechanism of the main flapping vanes and the auxiliary flapping vanes adopts the lever principle, gear transmission, hydraulic transmission and auxiliary drive for synchronous operation. [7] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the cockpit is an independent system with modular components to facilitate installation. [8] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the underside of the fuselage is provided with wheel retraction compartments for stowing the wheels of the ground travel devices, the wheels of the ground travel devices being connected to the fuselage by retraction mechanisms. [9] Purely electrically operated and manned short take-off and landing bionic ornithopter according to claim 1, characterized by that the change in state of the auxiliary flapping wings and the tail wing can control the flight attitude and direction of the bionic ornithopter.

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