CN214875603U

CN214875603U - Solar electric aircraft

Info

Publication number: CN214875603U
Application number: CN202121220072.9U
Authority: CN
Inventors: 王智强
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-06-02
Filing date: 2021-06-02
Publication date: 2021-11-26
Anticipated expiration: 2031-06-02

Abstract

The utility model discloses a solar energy electric aircraft, including cabin and the rotatable disc dish of setting in cabin top, the aircraft is provided with power supply, be provided with the motor between cabin and the disc dish, the motor drives disc dish clockwise or anticlockwise rotation, the cabin both sides are provided with the electronic ducted fan of lateral part respectively, the cabin afterbody is provided with the electronic ducted fan of afterbody, the disc dish upper surface is provided with solar cell, solar cell links to each other with one kind or multiple of power supply, the motor, the electronic ducted fan of lateral part, the electronic ducted fan of afterbody. The solar cell is adopted to provide sustainable clean energy for the aircraft, and the rotary disc wing has high aerodynamic effect and gyro-like stability, so that the electric aircraft can carry 3-4 people, the endurance time is 2-8 hours, and the maximum cruising speed reaches 160 kilometers per hour. The method has the characteristics of long navigation time, low cost, strong practicability, wide application range, safety, reliability, simple operation and the like.

Description

Solar electric aircraft

Technical Field

The utility model relates to a solar energy electric aircraft.

Background

In recent years, a hot tide of multi-propeller electric airplanes is raised at home and abroad, wherein small multi-propeller aircrafts develop faster, and large multi-propeller aircrafts capable of carrying people develop slower. The main reason is the power supply problem, although the lithium battery is advanced, the weight of the lithium battery is not negligible, and in the prior art, the manned multi-propeller electric aircraft capable of taking off and landing vertically can only carry 2 people generally, the speed per hour is about 70 kilometers, and the endurance time is about 30 minutes. If the endurance time is increased, the capacity of the lithium battery needs to be increased, the weight of the lithium battery is increased along with the increase of the capacity of the lithium battery, and the increased weight affects the load capacity of the airplane and shortens the endurance time of the airplane, so that the airplane falls into a technical bottleneck state.

SUMMERY OF THE UTILITY MODEL

To the problem, the utility model provides a solar energy electric aircraft improves the load capacity and the duration of a journey of aircraft.

For realizing above-mentioned technical purpose, reach above-mentioned technological effect, the utility model discloses a following technical scheme realizes:

the utility model provides an electronic aircraft of solar energy, includes the cabin and sets up at the rotatable disc dish in cabin top, the aircraft is provided with power supply, be provided with the motor between cabin and the disc dish, the motor drives disc dish clockwise or anticlockwise rotation, the cabin both sides are provided with the electronic duct fan of lateral part respectively, the cabin afterbody is provided with the electronic duct fan of afterbody, disc dish upper surface is provided with solar cell, solar cell links to each other with one kind or more of power supply, motor, the electronic duct fan of lateral part, the electronic duct fan of afterbody.

Preferably, the disc is provided with a plurality of fan openings, a top electric ducted fan is arranged in each fan opening, and the top electric ducted fan is connected with a power supply and/or a solar cell.

Preferably, the disc is provided with 16 fan ports, and each fan port is internally provided with 1 top electric ducted fan.

Preferably, a shaft sleeve is arranged at the top of the engine room, and the distance between the shaft sleeve and the output rotating shaft of the motor is set.

Preferably, the power supply is a lithium battery.

Preferably, lithium batteries are arranged on the bracket of the disc and the engine room.

Preferably, the lithium battery is a 2S lithium battery.

Preferably, 32 lithium batteries are arranged on the support of the disc, and each 2 lithium batteries are a group to supply power for the top electric ducted fan.

Preferably, 8 lithium batteries are arranged on the engine room, and each 2 lithium batteries form a group to supply power for the side electric ducted fan, the tail electric ducted fan and the motor.

Preferably, the diameter of the disc is 4-12 meters.

The utility model has the advantages that:

the utility model discloses a solar cell provides sustainable clean energy for the aircraft, and its rotary disk wing has very high pneumatic effect and has the stability as the top for electric aircraft can manned 3-4 people, and duration 2-8 hours, the highest speed of cruising reach 160 kilometers per hour. The method has the characteristics of long navigation time, low cost, strong practicability, wide application range, safety, reliability, simple operation and the like.

Drawings

Fig. 1 is a schematic structural diagram of a solar electric aircraft according to the present invention;

FIG. 2 is a side view of FIG. 1;

fig. 3 is a top view of a circular dish of the solar electric aircraft of the present invention;

the reference numerals of the drawings have the following meanings:

1: a nacelle; 2: a disc; 3: a side electric ducted fan; 4: a shaft sleeve; 5: a solar cell; 6: a tail electric ducted fan; 7: a top electric ducted fan; 8: a fan port.

Detailed Description

The technical solution of the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments, so that those skilled in the art can better understand the present invention and can implement the present invention, but the embodiments are not limited to the present invention.

As shown in fig. 1-3, a solar electric aircraft comprises a cabin 1 and a rotatable disk 2 arranged on the top of the cabin 1, wherein a motor is arranged between the cabin 1 and the disk 2, preferably, a shaft sleeve 4 is arranged on the top of the cabin 1, and a distance set by the distance between the shaft sleeve 4 and an output rotating shaft of the motor is set, in fig. 1, the motor is arranged on the top of the cabin 1, a body of the motor is fixed on the top of the cabin 1, the output rotating shaft of the motor is connected with the disk 2, and the motor drives the disk to rotate clockwise or counterclockwise to form a rotary wing of the aircraft. The top of the engine room is provided with a shaft sleeve, a certain space is reserved between the shaft sleeve and the rotating shaft, a plurality of electric brushes are convenient to install, and photoelectric control signals are transmitted in the inner space of the electric brushes to prevent external strong magnetic interference.

The aircraft is characterized in that two sides of the cabin 1 are respectively provided with a side electric ducted fan 3 for driving the aircraft to fly forwards, and the tail of the cabin 1 is provided with a tail electric ducted fan 6 for controlling the steering of the aircraft and eliminating torsion generated by the rotary disc wings.

The aircraft is provided with power supply, and among the prior art, this power supply adopts the lithium cell more, consequently, the utility model discloses also preferred adoption lithium cell is as power supply. In addition, the upper surface of the disc 2 is provided with a solar cell 5, and the solar cell 5 is used as a clean energy and is connected with one or more of a power supply, a motor, the side electric ducted fan 3 and the tail electric ducted fan 6. When the solar cell 5 is connected with the power supply, the power supply is directly supplied; when the solar battery 5 is connected with the electric fan (the side electric ducted fan 3 and the tail electric ducted fan 6), the electric fan is directly powered; when the solar cell 5 is connected to the motor, the motor is directly powered.

Preferably, the disk 2 is provided with a plurality of fan ports 8 (generally even number), a top electric ducted fan 7 is arranged in each fan port 8, and the rotating disk is provided with the top electric ducted fan 7 to drive the aircraft to vertically take off and land and hover. The top electric ducted fan 7 is connected with a power supply and/or a solar battery 5. As shown in fig. 3, the disk 2 is provided with 16 fan ports 8, and each fan port 8 is provided with 1 top electric ducted fan 7.

Preferably, lithium batteries are arranged on the support of the disc 2 and the engine room 1, and 2S lithium batteries can be selected as the lithium batteries (the 2S batteries represent that two small lithium batteries are arranged in the battery). The disk 2 is similar to an unfolded umbrella fabric structure and is provided with a support (similar to an umbrella framework of an umbrella), 32 2S lithium batteries are respectively and uniformly and symmetrically arranged in the disk and are divided into 16 groups (each 2 lithium batteries is one group) to supply power to 16 top electric ducted fans 7; 8 2S lithium batteries are installed on the engine room 1 and divided into 4 groups (every 2 lithium batteries are one group) to supply power to three electric ducted fans (2 side electric ducted

fans

3 and 1 tail electric ducted fan 6) and one motor and a control circuit thereof.

The solar cells are arranged on the upper surface of the circular disk 2 except for the electric ducted fan opening 8, the diameter range of the circular disk 2 can be 4-12 meters, and the power generation power of the solar cells arranged on the surface of the circular disk 2 with the diameter of 8 meters can reach more than 6 KW. The solar battery can respectively charge each lithium battery, and can also directly supply power to each electric ducted fan and the motor. The aircraft can continue for more than 2 hours in rainy days and 8 hours in sunny days.

Compared with the prior art, the utility model has the advantages of:

first, compare with current many screw electric aircraft, the utility model discloses a plurality of electronic duct fan dress have improved acting area and effective power on rotatory disc 2 by a wide margin, have enlarged electronic duct fan power effect, have increased the load capacity of aircraft. The air density and the pressure intensity below the rotary disk 2 are increased under the action of the electric ducted fan, the air density and the pressure intensity above the rotary disk 2 are reduced, and the pressure intensity below the rotary disk is greater than that above the rotary disk to enable the aircraft to generate lift force. In contrast, the larger the area of the disk 2, the greater the lift force that is obtained and the greater the load capacity of the aircraft.

And secondly, compared with the tilting multi-propeller electric airplane, the disk wing can obtain larger wingspan area than the fixed airplane wing at the same wing length, and more solar cells can be installed to obtain larger power generation capacity, so that the load capacity is improved. And the rotary disk 2 has horizontal stability, so that the cabin can not be greatly inclined and can not follow the head no matter the plane rises, falls or turns, and drivers and passengers have strong safety and high comfort level.

And thirdly, the electric ducted fan is embedded in the rotating disk to form the wing with high flying efficiency, and the flying efficiency is improved by about 4 to 5 times compared with that of the multi-propeller electric aircraft during horizontal flight.

The fourth, compare with many screw electric aircraft of tilting, the utility model discloses do not have complicated mechanical control transmission structure, be telex control completely, simple structure is light, the fault rate is low, safe and reliable.

Fifth, rotatory disc is just like a high-quality parachute of performance, even makes a plurality of electronic ducted fans break down also can slowly steadily descend, can open cabin bottom inflatable packer shock attenuation and can float on the surface of water during burst state, and the security is higher.

Sixth, install solar cell on the disc not only can give lithium cell charging, for the power supply of electronic duct fan, can also provide power such as domestic power consumption, illumination, heating, water boiling, cook, stir-fry dish for the crew member, be suitable for very much field exploration, grassland grazing, ecological tourism, border patrol, be a extensive applicability and very practical electric aircraft.

And seventhly, the solar electric rotary disc wing aircraft is driven by the electric ducted fan to ascend, descend, hover, turn left, turn right, fly forwards and turn in a zero radius direction, a plurality of actions can be combined and fly out of erratic wonderful tracks which cannot be realized by the fixed wing aircraft, so that the tracking and attack of the other party can be effectively avoided in military use, and the solar electric rotary disc wing aircraft can be configured on ships and warships for anti-diving patrol and beach landing.

And eighth, when the solar generating capacity is insufficient, an external power supply can be used for charging and a range extender can be additionally arranged.

The above is only the preferred embodiment of the present invention, and not the scope of the present invention, all the equivalent structures or equivalent flow changes made by the contents of the specification and the drawings are utilized, or directly or indirectly applied to other related technical fields, and all the same principles are included in the protection scope of the present invention.

Claims

1. The utility model provides a solar energy electric aircraft, includes cabin (1) and sets up at rotatable disc (2) in cabin (1) top, the aircraft is provided with power supply, be provided with the motor between cabin (1) and disc (2), the motor drives disc (2) clockwise or anticlockwise rotation, its characterized in that, cabin (1) both sides are provided with the electronic ducted fan of lateral part (3) respectively, cabin (1) afterbody is provided with the electronic ducted fan of afterbody (6), disc (2) upper surface is provided with solar cell (5), solar cell (5) link to each other with one kind or more of power supply, motor, the electronic ducted fan of lateral part (3), the electronic ducted fan of afterbody (6).

2. The solar electric aircraft as claimed in claim 1, wherein a plurality of fan ports (8) are arranged on the circular disc (2), a top electric ducted fan (7) is arranged in each fan port (8), and the top electric ducted fan (7) is connected with a power supply and/or a solar battery (5).

3. The solar electric aircraft as claimed in claim 2, wherein the disc (2) is provided with 16 fan ports (8), and each fan port (8) is provided with 1 top electric ducted fan (7).

4. The solar electric aircraft according to claim 1, characterized in that a bushing (4) is arranged on top of the nacelle (1), said bushing (4) being spaced from the output shaft of the electric motor by a set distance.

5. The solar powered electric aircraft as defined in claim 1 wherein the power supply is a lithium battery.

6. The solar electric aircraft as claimed in claim 5, characterized in that the disc (2) is provided with lithium batteries on both the support and the nacelle (1).

7. The solar electric aircraft as claimed in claim 6, wherein the lithium battery is a 2S lithium battery.

8. The solar electric aircraft as claimed in claim 6, characterized in that 32 lithium batteries are arranged on the support of the disc (2), each 2 lithium batteries forming a group for supplying power to the top electric ducted fan (7).

9. The solar electric aircraft according to claim 6, characterized in that the cabin (1) is provided with 8 lithium batteries, each 2 of which is a group supplying the lateral electric ducted fans (3), the aft electric ducted fans (6) and the electric motor.

10. A solar electric vehicle according to claim 1, characterized in that the diameter of the disc (2) is 4-12 meters.