Double-duct vertical take-off and landing electric aircraft

Abstract

The invention discloses a double-duct vertical take-off and landing electric aircraft which comprises a frame body, duct power systems, a battery and a riding control system are arranged on the frame body, the duct power systems are arranged at the left end and the right end of the frame body, and the riding control system is arranged at the front end of the frame body. The battery is arranged at the rear end of the frame body and used for providing energy power for the duct power system and the driving and riding control system. The aircraft is simple in structure and convenient to use, the whole aircraft adopts a quick disassembly and assembly mode, the whole assembly process is simple and quick, a good safety protection effect can be provided for each part during transportation, collision and other situations are avoided, energy power is provided for the duct power system and the driving and riding control system through the battery, and the safety of the aircraft is improved. A driver and passengers can control the duct power system through the riding control system, the ducts at the two side ends generate thrust downwards at the same time, the aircraft can fly upwards, the flight direction can be changed through the flow guide assembly, and therefore steering of the aircraft is completed.

Description

Technical Field

[0001] The present invention relates to the technical field of manned aircraft, and in particular to a dual-duct vertical take-off and landing electric aircraft. Background Art

[0002] As society continues to develop and progress, the level of science and technology is also constantly innovating, and people's means of transportation are also constantly innovating and changing, from bicycles, tricycles, electric vehicles and cars that run on the ground in the past, to aerospace equipment that flies in the sky, and then aircraft that can be used at high altitudes are developed, so that they can fly freely in the sky and avoid the congestion caused by driving on the ground, delaying time and progress.

[0003] Currently available aircraft have complex structures, cumbersome installation, and large sizes, which makes transportation very inconvenient. In addition, existing aircraft are expensive to manufacture, and need to be provided with sufficient safety and protection to avoid collisions during transportation, which may cause internal parts to shift or be damaged, causing the aircraft to malfunction or become unusable.

[0004] Therefore, it is necessary to study a new technical solution to solve the above problems. Summary of the invention

[0005] In view of this, the present invention aims to solve the deficiencies in the prior art, and its main purpose is to provide a dual-duct vertical take-off and landing electric aircraft.

[0006] To achieve the above purpose, the present invention adopts the following technical solutions:

[0007] A double-ducted vertical take-off and landing electric aircraft includes a frame, on which a ducted power system, a battery and a ride control system are provided. The ducted power system is arranged at the left and right ends of the frame, the ride control system is arranged at the front end of the frame, and the battery is arranged at the rear end of the frame and is used to provide energy and power to the ducted power system and the ride control system.

[0008] Preferably, the ducted power system comprises a left duct and a right duct, and the left duct and the right duct are detachably fixed to left and right ends of the frame.

[0009] Preferably, the left duct or the right duct includes a duct bracket, a duct motor, an electronic speed regulator, a servo drive, a propeller and a guide assembly, the duct motor is arranged at the upper inner end of the duct bracket, the propeller is arranged on the duct motor and is driven to rotate thereby, the electronic speed regulator is arranged on the outer surface of the duct bracket and is connected to the duct motor for controlling the rotation speed thereof, the guide assembly is arranged at the lower inner end of the duct bracket, and the servo drive is arranged between the duct bracket and the guide assembly and is used to control the swing angle of the guide assembly.

[0010] Preferably, the guide assembly includes a guide frame and a guide vane, the guide vane is arranged at the center position of the inner end of the guide frame, one end of the servo driver is connected and fixed to one end of the guide vane and controls it to swing, the other end of the servo driver passes through the guide frame and the lower end of the duct bracket and is fixed on the duct bracket, and the guide assembly is adjustably installed in the duct bracket.

[0011] As a preference, a battery rack for placing batteries is provided at the rear end of the frame, a fixed cross bar is provided at the lower end of the battery rack, and both ends of the fixed cross bar are mounted on the frame.

[0012] Preferably, the battery is a detachable battery or a rechargeable battery that can be recharged cyclically.

[0013] Preferably, the battery is a fuel cell.

[0014] As a preference, the frame is further provided with supporting feet, which are arranged at the rear end of the frame and below the battery.

[0015] Preferably, the riding control system comprises a riding position, a control handle and a safety belt, the riding position having pedals and an armrest, the control handle being arranged at the inner end of the armrest, and the safety belt being arranged at the middle and upper end of the riding position for fixing and locking the human body in the riding position.

[0016] As a preferred embodiment, the frame is also provided with a safety parachute, and the safety parachute is fixedly installed at the top center position of the frame.

[0017] Compared with the prior art, the present invention has obvious advantages and beneficial effects. Specifically, it can be seen from the above technical solution that:

[0018] The present invention has a simple structure and is easy to use. The entire aircraft adopts a quick disassembly and assembly method. The entire assembly process is simple and fast, and each component can be provided with a good safety protection effect during transportation to avoid collisions and the like. The battery provides energy and power to the ducted power system and the ride control system, so that the passengers can control the ducted power system through the ride control system, and the ducts on both sides simultaneously generate thrust downward, so that the aircraft can fly upward, and the flight direction can also be changed through the guide assembly, thereby completing the turning of the aircraft.

[0019] The battery used in the present invention is a rechargeable or replaceable battery. The replaceable battery can be quickly replaced to improve the use efficiency; and the rechargeable battery can be used with a high-current charging gun to quickly charge the battery, so that the battery can be charged in a short time, shortening the waiting time. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0021] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0022] Figure 2 It is a structural schematic diagram from another viewing angle of the present invention.

[0023] Figure 3 It is a schematic diagram of the decomposition structure of the present invention.

[0024] Figure 4 It is a schematic diagram of the structure of the ducted power system of the present invention.

[0025] Among them, the reference numerals in the figure are:

[0026] 100, frame; 110, battery rack; 120, fixed crossbar; 130, support leg; 140, display screen; 150, sliding wheel; 200, ducted power system; 210, left duct; 220, right duct; 230, duct bracket; 240, propeller; 250, guide assembly; 251, guide frame; 252, guide vane; 260, ducted motor; 270, electronic speed regulator; 280, servo drive; 300, battery; 400, ride control system; 410, ride position; 420, control handle; 430, safety belt; 500, safety parachute. DETAILED DESCRIPTION

[0027] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0028] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0029] It should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0030] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0031] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0032] Reference Figure 1-4 As shown: a dual-ducted vertical take-off and landing electric aircraft includes a frame 100, and a ducted power system 200, a battery 300 and a ride control system 400 are arranged on the frame 100. The ducted power system 200 is arranged at the left and right ends of the frame 100, and the ride control system 400 is arranged at the front end of the frame 100, and then the battery 300 is arranged at the rear end of the frame 100, and energy is provided to the ducted power system 200 and the ride control system 400 through the battery 300, so that the operator can control the aircraft.

[0033] In this embodiment, the ducted power system 200 includes a left duct 210 and a right duct 220, and the left duct 210 and the right duct 220 are detachably fixed to the left and right ends of the frame 100, so that the left duct 210 and the right duct 220 can rotate at the same time, thereby generating lift, so that the aircraft can fly upward, and the rotation direction of the left duct 210 and the right duct 220 can rotate in the same direction, and the rotation direction of the two ducts can also be set to rotate in opposite directions.

[0034] Specifically, the left duct 210 or the right duct 220 includes a duct bracket 230, a duct motor 260, an electronic speed regulator 270, a servo drive 280, a propeller 240 and a guide assembly 250. The duct motor 260 is arranged at the upper inner end of the duct bracket 230, and then the propeller 240 is arranged on the duct motor 260 and rotated by the drive of the duct motor 260 to generate lift, and then the guide assembly 250 is arranged at the lower inner end of the duct bracket 230, so that the upper propeller 240 generates lift, and The direction of air flow is changed by the guide assembly 250 below, thereby realizing the turning of the aircraft; wherein, the electronic speed regulator 270 is arranged on the outer surface of the duct bracket 230 and connected to the duct motor 260, which can control the rotation speed of the duct motor 260, thereby changing the speed state of the aircraft, and by arranging the servo driver 280 between the duct bracket 230 and the guide assembly 250, the swing angle of the guide assembly 250 is changed through the control of the servo driver 280, thereby changing the moving direction of the aircraft.

[0035] Furthermore, the guide assembly 250 used includes a guide frame 251 and a guide vane 252. The guide vane 252 is set at the center position of the inner end of the guide frame 251, and one end of the servo driver 280 is connected and fixed to one end of the guide vane 252, so that the servo driver 280 can control the guide vane 252 to swing, and then the other end of the servo driver 280 passes through the guide frame 251 and the lower end of the duct bracket 230 and is installed and fixed on the duct bracket 230, so that the guide frame 251 is fixedly installed at the lower inner end of the duct bracket 230, and the guide assembly 250 is adjustably installed in the duct bracket 230, so that the operator can send a control signal to the servo driver 280 through the ride control system 400, so that the servo driver 280 controls the guide vane 252 of the guide assembly 250 to adjust the angle, thereby realizing the change of the flight direction of the entire aircraft.

[0036] In this embodiment, a battery rack 110 for placing the battery 300 is provided at the rear end of the frame 100, and a fixed cross bar 120 is provided at the lower end of the battery rack 110. The battery rack 110 is installed on the fixed cross bar 120, and then the two ends of the fixed cross bar 120 are respectively installed on the frame 100 to achieve a fixing effect, so that the battery can be fixed on the aircraft.

[0037] Furthermore, the battery 300 used is a rechargeable battery 300 that is cyclically charged, and a fast charging port is provided on the battery rack 110, and a high-current charging gun is used to quickly charge the battery 300, so that the battery 300 can be fully charged in a short time, saving charging time.

[0038] In this embodiment, the battery 300 used can also be a detachable and replaceable battery 300. By quickly disassembling and replacing the battery 300, another battery 300 can be quickly installed, so that the aircraft can quickly replace the battery 300.

[0039] In this embodiment, the battery 300 used can also be a fuel cell, which has the characteristics of high power generation efficiency, low pollution, a wide range of optional fuels and high reliability. When in use, by adding material fuel that can be used for chemical reactions to generate electrical energy into the battery 300, the fuel cell can provide energy power to the aircraft, allowing the aircraft to operate and take off.

[0040] In this embodiment, a support leg 130 is further provided on the frame 100 . The support leg 130 is disposed at the rear end of the frame 100 and below the battery 300 , so that the aircraft can be stably placed on the ground.

[0041] In this embodiment, the riding control system 400 includes a riding position 410, a control handle 420 and a safety belt 430. The riding position 410 is provided with a pedal and an armrest, so that the user can stand on the pedal and hold on to the armrest to keep himself stable. The control handle 420 is arranged at the inner end of the armrest to facilitate the operator to hold and control it. The safety belt 430 is also arranged at the middle and upper ends of the riding position 410 to fix and lock the human body in the riding position 410, thereby playing a good protective role.

[0042] Specifically, a display screen 140 is also included. By arranging the display screen 140 on the handrails on both sides, the operator can observe the flight altitude, speed and status of the aircraft through the display screen 140 when controlling the aircraft.

[0043] In this embodiment, a safety parachute 500 is further provided on the frame 100. When encountering special circumstances, the safety parachute can provide cushioning for the aircraft to land safely and smoothly on the ground.

[0044] In this embodiment, a signal indicator light is provided on the frame 100 and fixedly mounted on the top of the frame 100 so that the signal indicator light can be emitted for others to observe.

[0045] In this embodiment, sliding wheels 150 are further provided on the frame 100 , and by arranging them on both sides of the driving position 410 , the aircraft can glide and move on the ground.

[0046] The above are only preferred embodiments of the present invention, and only specifically describe the technical principles of the present invention. These descriptions are only for explaining the principles of the present invention and cannot be interpreted as limiting the scope of protection of the present invention in any way. Based on the explanations here, any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention, and other specific implementations of the present invention that can be associated with by technicians in this field without creative labor, should be included in the scope of protection of the present invention.

Claims

1. A dual-duct vertical take-off and landing electric aircraft, comprising a frame, characterized in that: The frame is provided with a ducted power system, a battery and a ride control system. The ducted power system is arranged at the left and right ends of the frame, the ride control system is arranged at the front end of the frame, and the battery is arranged at the rear end of the frame and is used to provide energy and power to the ducted power system and the ride control system.

2. The dual-duct vertical take-off and landing electric aircraft according to claim 1, characterized in that: The ducted power system includes a left duct and a right duct, and the left duct and the right duct are detachably fixed to the left and right ends of the frame.

3. The dual-duct vertical take-off and landing electric aircraft according to claim 2, characterized in that: The left duct or the right duct includes a duct bracket, a duct motor, an electronic speed regulator, a servo drive, a propeller and a guide assembly. The duct motor is arranged at the upper inner end of the duct bracket, the propeller is arranged on the duct motor and is driven to rotate thereby, the electronic speed regulator is arranged on the outer surface of the duct bracket and is connected to the duct motor for controlling the rotation speed thereof, the guide assembly is arranged at the lower inner end of the duct bracket, and the servo drive is arranged between the duct bracket and the guide assembly and is used to control the swing angle of the guide assembly.

4. The dual-duct vertical take-off and landing electric aircraft according to claim 3, characterized in that: The guide assembly includes a guide frame and a guide vane. The guide vane is arranged at the center position of the inner end of the guide frame. One end of the servo driver is connected and fixed to one end of the guide vane to control the swinging thereof. The other end of the servo driver passes through the guide frame and the lower end of the duct bracket and is fixed on the duct bracket. The guide assembly is adjustably installed in the duct bracket.

5. The dual-duct vertical take-off and landing electric aircraft according to claim 1, characterized in that: A battery rack for placing batteries is arranged at the rear end of the frame body, and a fixed cross bar is arranged at the lower end of the battery rack. Both ends of the fixed cross bar are installed on the frame body.

6. The dual-duct vertical take-off and landing electric aircraft according to claim 5, characterized in that: The battery is a detachable battery or a rechargeable battery that can be recharged cyclically.

7. The dual-duct vertical take-off and landing electric aircraft according to claim 5, characterized in that: The battery is a fuel cell.

8. The dual-duct vertical take-off and landing electric aircraft according to claim 1, characterized in that: The frame is also provided with supporting feet, which are arranged at the rear end of the frame and below the battery.

9. The dual-duct vertical take-off and landing electric aircraft according to claim 1, characterized in that: The driving control system includes a driving position, a control handle and a safety belt. The driving position has a pedal and an armrest. The control handle is arranged at the inner end of the armrest. The safety belt is respectively arranged at the middle and upper ends of the driving position to fix and lock the human body in the driving position.

10. The dual-duct vertical take-off and landing electric aircraft according to claim 1, characterized in that: The frame is also provided with a safety parachute, which is fixedly installed at the top center of the frame.

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