Electric vertical take-off and landing manned aircraft

Abstract

The invention discloses an electric vertical take-off and landing manned aircraft which comprises an aluminum alloy rack, a second carbon fiber tube and supporting legs, one side of the aluminum alloy rack is connected with a right guardrail, the other side of the aluminum alloy rack is rotationally connected with a left guardrail through a winding shaft seat, and a vibration reduction assembly comprises a vibration reduction seat arranged on the first carbon fiber tube in a sleeving mode. The upper vibration reduction seat and the lower vibration reduction seat are fastened through bolts at the penetrating positions of the first carbon fiber pipes and the aluminum alloy rack, the rubber vibration reduction pads absorb high-frequency vibration energy through elastic deformation of the rubber vibration reduction pads, direct transmission of vibration to the rack is effectively blocked, the second carbon fiber pipes can be rotationally folded through the hinge seats, the transverse size of the whole machine is greatly reduced after folding, and the whole machine is more compact in structure. The occupied area is remarkably reduced, storage in a narrow space is facilitated, pushing can be achieved only by pressing down the tail end during transition on the flat ground, extra tools or complex operation procedures are not needed, the gravity center of the machine body is naturally transferred to the supporting wheels along with posture adjustment in the pushing process, and transition flexibility and efficiency are improved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of manned aircraft, and particularly relates to an electric vertical take-off and landing manned aircraft. BACKGROUND

[0002] In recent years, with the acceleration of urbanization and the increasing demand for air transportation, the electric vertical take-off and landing manned aircraft (eVTOL) as a new type of short-distance air transportation tool has attracted widespread attention and research. It has the advantages of vertical take-off and landing without the need for a dedicated runway, low emission, high efficiency and flexibility, and is considered an important development direction to solve urban traffic congestion and improve travel efficiency. It has great application potential in urban commuting, aerial sightseeing and emergency rescue.

[0003] The existing electric vertical take-off and landing manned aircraft is usually equipped with multiple arms in the structural design to ensure stability and lift demand during flight. The arms are usually fixedly connected, which can meet the performance requirements in the flight state, but the arms cannot be folded during storage and transportation, resulting in a large overall footprint of the aircraft, which is difficult to adapt to the storage needs of small spaces such as home garages and small airfields. At the same time, it also increases the difficulty and cost of road transportation, to some extent, restricting the process of its civilianization and popularization. SUMMARY

[0004] The purpose of the present application is to provide an electric vertical take-off and landing manned aircraft to solve the problems raised in the background.

[0005] To achieve the above purpose, the present application provides the following technical solution: an electric vertical take-off and landing manned aircraft, comprising:

[0006] An aluminum alloy frame, one side of which is connected with a right guardrail, and the other side is rotatably connected with a left guardrail through a shaft seat, so that the left guardrail can rotate around the shaft seat to form a passage for passengers to enter and exit;

[0007] A second carbon fiber pipe, which is provided in several groups and is hingedly connected to both ends of the first carbon fiber pipe through a winding seat, so as to realize the folding of the arm and reduce the footprint in the storage state.

[0008] Two groups of support legs are fixedly connected to the front side of the bottom of the aluminum alloy frame, providing stable front support when the aircraft is parked, and two groups of support wheels are rotatably connected to the rear side of the bottom of the aluminum alloy frame, facilitating easy pushing and moving during ground transfer and improving the flexibility of ground operation.

[0009] Preferably, the aluminum alloy frame is provided with a damping assembly at each of the front and rear ends, for changing the amplitude and resonance point to reduce the influence of vibration on the structural stability and ride comfort, the damping assembly comprising a damping seat sleeved on the first carbon fiber pipe, and a rubber damping pad arranged at the sleeving position of the damping seat and the first carbon fiber pipe, so that the rubber damping pad can absorb and buffer the vibration energy through elastic deformation when the aluminum alloy frame vibrates.

[0010] Preferably, the first carbon fiber pipe is arranged in the aluminum alloy frame and penetrates the aluminum alloy frame at both ends, the damping seat is arranged at the penetration position of the first carbon fiber pipe and the aluminum alloy frame, and the damping seat comprises an upper damping seat and a lower damping seat, which are sleeved on the first carbon fiber pipe and fastened and connected into an integrated body through bolts, and the rubber damping pad is clamped between the upper damping seat and the lower damping seat.

[0011] Preferably, the first carbon fiber pipe is sleeved with a sleeve, and the sleeve and the first carbon fiber pipe are connected through a hollow fixing pin penetrating the corresponding assembly holes of the sleeve and the first carbon fiber pipe, so as to form an axial limiting structure to prevent the sleeve from moving left / right on the first carbon fiber pipe.

[0012] Preferably, the top of the sleeve is connected with an axial anti-rolling support through a rubber clip, and the axial anti-rolling support is welded with the aluminum alloy frame.

[0013] Preferably, the right guardrail and the left guardrail are respectively connected with a right handrail guard plate and a left handrail guard plate, and the right handrail guard plate and the left handrail guard plate are both made of carbon fiber composite material or engineering plastic.

[0014] Preferably, the right handrail guard plate is provided with an on-board direction proportional rocker, and the left handrail guard plate is provided with an on-board lifting proportional throttle rocker, and the aluminum alloy frame is provided with a seat.

[0015] Preferably, one side of the aluminum alloy frame is connected with a limiting rod, the left guardrail is opened by rotating around the shaft seat, and stops when opened to the limiting rod, and the limiting rod can limit the maximum opening angle of the left guardrail.

[0016] Preferably, one end of the second carbon fiber pipe is connected with a double-shaft motor, and the output shafts of the double-shaft motor are both connected with propellers.

[0017] Preferably, the bottom of the aluminum alloy frame is provided with a bottom compartment, and the bottom compartment is provided with a battery, and the battery is electrically connected with the double-shaft motor.

[0018] Compared with the prior art, the present application has the following advantages:

[0019] (1) The double-layer buffer design of the vibration damping assembly forms an efficient vibration filtering system. The upper vibration damping seat and the lower vibration damping seat are fastened by bolts through the penetration of the first carbon fiber pipe and the aluminum alloy frame, and the rubber damping pad is clamped therein. When vibration is transmitted to the rubber damping pad, the rubber damping pad absorbs high-frequency vibration energy through its elastic deformation, effectively blocking the direct transmission of vibration to the frame. At the same time, the sleeve and the first carbon fiber pipe are rigidly connected by means of the hollow fixing pin, and the axial anti-rolling support is elastically clamped to the sleeve by the rubber clip. The clamping force can be flexibly adjusted by the hardness of the rubber clip, which can further filter low-frequency vibration and significantly reduce the vibration sensation in the cabin area. The first carbon fiber pipe and the second carbon fiber pipe are made of carbon fiber composite material, which has weak reflection ability to sound waves and can reduce the transmission efficiency of propeller aerodynamic noise.

[0020] (2) The aluminum alloy frame is made of aviation-grade aluminum alloy by argon arc welding, and the welded joints are subjected to special stress relief treatment. The overall structural strength is high, and it can withstand the instantaneous impact force generated during the accidental failure of the propeller. The "scissors door" formed by the opening of the left guardrail around the shaft seat can rotate along the shaft seat when opened, and the limiting rod controls the opening angle, ensuring sufficient access for passengers and preventing excessive opening from causing structural deformation.

[0021] (3) The second carbon fiber pipe can be rotated and folded through the twist seat, greatly reducing the overall horizontal size and significantly reducing the floor space, making it easy to store in a small space.

[0022] (4) When transferring on flat ground, it only needs to lower the tail end to realize pushing, without the need for additional tools or complex operation procedures. During the pushing process, the center of gravity of the fuselage naturally shifts to the support wheel with the adjustment of the attitude, making the pushing process more labor-saving and improving the flexibility and efficiency of the transfer. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 is the structural schematic diagram of the first perspective of the present application;

[0024] Figure 2 is the structural schematic diagram of the second perspective of the present application;

[0025] Figure 3 is the top view of the present application;

[0026] Figure 4 is the structural schematic diagram of the first carbon fiber pipe and the second carbon fiber pipe connected by the twist seat of the present application.

[0027] In the figure: 1, aluminum alloy frame; 2, right guardrail; 3, shaft seat; 4, left guardrail; 5, first carbon fiber pipe; 6, rubber damping pad; 7, second carbon fiber pipe; 8, upper damping seat; 9, lower damping seat; 10, sleeve; 11, hollow fixing pin; 12, axial anti-rolling support; 13, right handrail guard plate; 14, left handrail guard plate; 15, airborne directional proportional rocker; 16, airborne lifting proportional throttle rocker; 17, seat; 18, limiting rod; 19, double-shaft motor; 20, propeller; 21, bottom compartment; 22, battery; 23, support leg; 24, support wheel; 25, winding seat; 26, rubber clip; 27, fixing lug. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0029] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "provided with", "sleeved", "sleeved", "connected" and the like should be understood broadly, for example, "connected" can be fixedly connected, or detachably connected, or integrally connected; can be mechanically connected, or electrically connected; can be directly connected, or indirectly connected through an intermediate medium; can be the communication inside two elements, and those skilled in the art can understand the specific meaning of the above terms in the present application according to the specific circumstances.

[0030] The present application provides an electric vertical take-off and landing manned aircraft as shown in Figures 1-4 The present application provides an electric vertical take-off and landing manned aircraft as shown in

[0031] The aluminum alloy frame 1 is fixedly connected with the right guardrail 2 on one side to form a lateral protection, and is rotatably connected with the left guardrail 4 through the shaft seat 3 on the other side. The left guardrail 4 can be rotated around the shaft seat 3 to a preset angle to form a passage for passengers to get on and off the aircraft. The guardrail structure realizes lateral safety protection of passengers and convenient getting on and off the aircraft function.

[0032] The damping assembly is provided with two groups and is assembled at the front and rear ends of the aluminum alloy frame 1, which is used to change the vibration transmission path and resonance frequency through a multi-stage buffer structure to weaken the influence of vibration on the stability of the fuselage structure and the comfort of the cabin.

[0033] The second carbon fiber pipe 7 is provided with several groups and is hinged at the ends of the first carbon fiber pipe 5 through the hinge seat 25, and the folding action of the arm is realized through the rotation characteristics of the hinge seat 25, so as to reduce the lateral size of the whole machine in the non-use state to reduce the storage area.

[0034] The support leg 23 is provided with two groups and is fixedly connected to the front side of the bottom of the aluminum alloy frame 1, and the front end is stably supported when parking through the support leg 23, and the rear side of the bottom of the aluminum alloy frame 1 is rotatably connected with two groups of support wheels 24 which can be flexibly turned, and the rolling characteristics of the support wheels 24 facilitate the transfer movement of the whole machine on the ground, and the ground operation convenience is improved,

[0035] The first carbon fiber pipe 5 is arranged inside the aluminum alloy frame 1 and extends out of the frame at both ends, the damping seat is assembled at the penetration position of the first carbon fiber pipe 5 and the aluminum alloy frame 1, the damping seat is composed of an upper damping seat 8 and a lower damping seat 9, both of which are sleeved on the first carbon fiber pipe 5 and are fastened by bolts to form an integral structure, and the rubber damping pad 6 is clamped between the two, and the rigid fastening structure ensures the close contact of the rubber damping pad 6 with the vibration source to maximize the absorption of vibration energy.

[0036] The first carbon fiber pipe 5 is sleeved with a sleeve 10, and the sleeve 10 and the first carbon fiber pipe 5 are connected through a hollow fixing pin 11, and the hollow fixing pin 11 is embedded in the corresponding assembly hole of the two to form an axial limiting mechanism, which can limit the relative displacement of the first carbon fiber pipe 5 and the sleeve 10 along the axis direction, and ensure the stability of the structure connection.

[0037] The sleeve 10 is connected with an axial anti-rolling support 12 through a rubber clip 26, and the axial anti-rolling support 12 is welded and fixed with the aluminum alloy frame 1, and the elastic connection characteristics of the rubber clip 26 form a two-stage damping structure, and the rigid support of the axial anti-rolling support 12 enhances the anti-rollover ability of the fuselage.

[0038] The right guardrail 2 and the left guardrail 4 are respectively connected with the right handrail guard plate 13 and the left handrail guard plate 14, both of which are made of carbon fiber composite material or engineering plastic, so as to reduce the weight of the fuselage and improve the protection performance through the characteristics of light weight and high strength, and provide an operating support surface for the driver and passenger.

[0039] The right handrail guard plate 13 is equipped with an on-board directional proportional rocker 15, and the left handrail guard plate 14 is equipped with an on-board lifting proportional throttle rocker 16, so as to realize precise control of the flight attitude through the ergonomic layout. The aluminum alloy frame 1 is provided with a seat 17 to provide a passenger seating support.

[0040] One side of the aluminum alloy frame 1 is connected with a limiting rod 18. When the left guardrail 4 rotates to open around the shaft seat 3, it stops rotating after contacting the limiting rod 18. The maximum opening angle of the left guardrail 4 is limited by the mechanical blocking action of the limiting rod 18 to prevent structural damage caused by excessive rotation.

[0041] One end of the second carbon fiber pipe 7 is connected with a double-shaft motor 19, and the two output shafts of the double-shaft motor 19 are respectively connected with propellers 20. The double-shaft driving structure improves the power output efficiency, and the rotation of the propellers 20 generates lift and propulsion.

[0042] The bottom of the aluminum alloy frame 1 is provided with a bottom compartment 21, and the bottom compartment 21 is equipped with a battery 22. The battery 22 is electrically connected with the double-shaft motor 19, and the double-shaft motor 19 is driven to operate by the electric energy provided by the battery 22 to realize the power supply of the aircraft.

[0043] This electric vertical takeoff and landing (eVTOL) manned aircraft has lithium-ion batteries 22 in its base compartment 21 that continuously supply power to dual-axis motors 19 via waterproof cables. The power of the dual-axis motors 19 is bolted to propellers 20. The propellers 20 employ a variable cross-section airfoil design, which more efficiently cuts through the air to generate lift during rotation. The flight control system within the manned aircraft precisely regulates the rotational speeds of the left and right motors, utilizing the thrust difference generated by the two propellers 20 to drive the aircraft's steering. By changing the thrust ratio of the front and rear motors, the pitch angle of the fuselage is adjusted, thereby achieving flexible movement in the vertical, horizontal, and forward / backward directions, and completing various flight attitude controls. When the pilot operates the aircraft... When the lift-proportional throttle stick is at position 16, the stick's displacement is converted into an electrical signal by an internal sensor. This signal is processed and transmitted to the flight control mainboard. Based on preset control logic and parameters, the flight control mainboard calculates the target speed required for each motor and then sends control commands to the corresponding motor controllers via the bus. After receiving the commands, the motor controllers drive the motors to adjust their speeds. The encoders on the motors monitor the actual rotational speed in real time and continuously transmit the monitored information back to the flight control system. The flight control system compares the difference between the actual speed and the target speed and adjusts the output commands in a timely manner, forming a complete closed-loop control to ensure that the motor speeds are strictly executed according to the commands, thereby ensuring the stability of the aircraft's flight attitude.

[0044] When the propeller 20 rotates, the aerodynamic vibration generated is transmitted to the first carbon fiber tube 5 through the second carbon fiber tube 7. The vibration wave rebounds at the gap between the sleeve 10 and the first carbon fiber tube 5, and some of the vibration energy is consumed. At the same time, after the rubber damping pad 6 is squeezed by vibration, its internal molecular chains rub against each other, further absorbing high-frequency vibration energy and greatly weakening the transmission of high-frequency vibration to the frame. The axial anti-roll bracket 12 is connected to the sleeve 10 through the rubber clip 26, which can form a wrap-around clamp for the sleeve 10. When low-frequency vibration is transmitted to this point, the rubber clip 26 will undergo elastic deformation, using its own elastic properties to buffer the vibration and suppress the generation of low-frequency resonance. After these two stages of vibration reduction, the vibration energy transmitted to the aluminum alloy frame 1 is greatly weakened, and the vibration in the cockpit area is significantly reduced.

[0045] When the manned aircraft is grounded and the arm needs to be folded, the fastening bolts on the fixing lug 27 at the hinge joint of the first carbon fiber tube 5 and the second carbon fiber tube 7 can be manually loosened to release the constraint on the arm, allowing the second carbon fiber tube 7 to rotate freely around the hinge seat 25, thereby folding the arm of the manned aircraft and reducing the footprint.

[0046] When parking a manned aircraft, the tail is manually lowered so that the support wheel 24 contacts the ground. The center of gravity of the aircraft then shifts to the support wheel 24, allowing the aircraft to move flexibly on the ground.

[0047] It should be pointed out finally that the above only describes the preferred embodiments of the present application and is not intended to limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent replacements to some of the technical features, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An electric vertical take-off and landing passenger aircraft, characterized in that, include: An aluminum alloy frame (1) is connected to a right guardrail (2) on one side and to a left guardrail (4) on the other side by rotating around a pivot seat (3) so that the left guardrail (4) can rotate around the pivot seat (3) to form a passage for passengers to enter and exit. The second carbon fiber tube (7) is provided in several groups and one end of the second carbon fiber tube (7) is hinged to both ends of the first carbon fiber tube (5) through a hinge (25) to realize the folding of the arm, thereby reducing the floor space occupied in the storage state. Support legs (23) are provided in two sets and are fixedly connected to the front bottom of the aluminum alloy frame (1) to provide stable front support when the aircraft is parked. The rear bottom of the aluminum alloy frame (1) is rotatably connected to two sets of flexible steering support wheels (24) to facilitate easy pushing and moving during ground transfer and improve the flexibility of ground operation.

2. An electric vertical take-off and landing passenger aircraft according to claim 1, characterized in that: The aluminum alloy frame (1) is equipped with vibration damping components at both the front and rear ends to change the amplitude and resonance point, so as to reduce the impact of vibration on structural stability and ride comfort. The vibration damping components include a vibration damping seat fitted on the first carbon fiber tube (5). A rubber vibration damping pad (6) is provided at the fitting point between the vibration damping seat and the first carbon fiber tube (5). When the aluminum alloy frame (1) vibrates, the rubber vibration damping pad (6) can absorb and buffer the vibration energy through elastic deformation.

3. An electric vertical take-off and landing passenger aircraft according to claim 2, characterized in that: The first carbon fiber tube (5) is located inside the aluminum alloy frame (1) and both ends of the first carbon fiber tube (5) penetrate the aluminum alloy frame (1). The vibration damping seat is located at the penetration point between the first carbon fiber tube (5) and the aluminum alloy frame (1). The vibration damping seat includes an upper vibration damping seat (8) and a lower vibration damping seat (9). After the upper vibration damping seat (8) and the lower vibration damping seat (9) are fitted onto the first carbon fiber tube (5), they are fastened together by bolts and a rubber vibration damping pad (6) is clamped between the upper vibration damping seat (8) and the lower vibration damping seat (9).

4. An electric vertical take-off and landing passenger aircraft according to claim 1, characterized in that: The first carbon fiber tube (5) is fitted with a sleeve (10), and the sleeve (10) and the first carbon fiber tube (5) are connected through a hollow fixing pin (11). The hollow fixing pin (11) is embedded in the corresponding assembly hole of the sleeve (10) and the first carbon fiber tube (5) to form an axial limiting structure, thereby preventing the sleeve (10) from moving left or right on the first carbon fiber tube (5).

5. An electric vertical take-off and landing passenger aircraft as claimed in claim 4 wherein: The top of the sleeve (10) is connected to an axial anti-roll bracket (12) by a rubber clamp (26), and the axial anti-roll bracket (12) is welded to the aluminum alloy frame (1).

6. An electric vertical take-off and landing passenger aircraft according to claim 1, characterized in that: The right guardrail (2) and the left guardrail (4) are respectively connected to a right handrail guard plate (13) and a left handrail guard plate (14), and both the right handrail guard plate (13) and the left handrail guard plate (14) are made of carbon fiber composite material or engineering plastic.

7. An electric vertical take-off and landing passenger aircraft as claimed in claim 6, characterized in that: The right armrest guard plate (13) is equipped with a load direction proportional rocker arm (15), the left armrest guard plate (14) is equipped with a load lifting proportional throttle rocker arm (16), and the aluminum alloy frame (1) is equipped with a seat (17).

8. An electric vertical take-off and landing passenger aircraft according to claim 1, characterized in that: The aluminum alloy frame (1) is connected with a limiting rod (18) on one side, the left guardrail (4) is opened by rotating around the shaft seat (3), and stops when being opened to the limiting rod (18), and the maximum opening angle of the left guardrail (4) can be limited through the limiting rod (18).

9. An electric vertical take-off and landing passenger aircraft according to claim 2, characterized in that: One end of the second carbon fiber pipe (7) is connected with a double-shaft motor (19), and the output shafts of the double-shaft motor (19) are both connected with propellers (20).

10. An electric vertical take-off and landing passenger aircraft as claimed in claim 9, characterized in that: The bottom of the aluminum alloy frame (1) is provided with a bottom bin (21), and the bottom bin (21) is provided with a battery (22), and the battery (22) is electrically connected with the double-shaft motor (19).

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