CN212313298U

CN212313298U - Small-sized solar unmanned aerial vehicle

Info

Publication number: CN212313298U
Application number: CN201821070475.8U
Authority: CN
Inventors: 李可
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-07-06
Filing date: 2018-07-06
Publication date: 2021-01-08
Anticipated expiration: 2028-07-06

Abstract

A small-sized solar unmanned aerial vehicle adopts the layout form of a conventional layout, a single tail boom and an inverted T-shaped tail wing, has high reliability, and saves energy consumption by adopting a streamline design on the wings. The solar energy cruising flight-time monitoring machine is powered by the solar cell panel and the lithium battery pack, has longer flight time and longer flight distance, and can play a long-time cruising task; the conventional monocrystalline silicon battery panel is used, and the multi-layer packaging mode is adopted to be combined with the wing, so that the completeness of the wing shape is guaranteed, and the pneumatic efficiency of the whole machine is guaranteed. The solar flat plane can take off by depending on the power provided by the solar panel and the lithium battery pack and can completely take off by depending on the solar power in a flat plane state; the single-generator motor is used as driving power, and has the advantages of high force efficiency, large torsion and low rotating speed; each solar cell panel group is provided with an independent maximum power point tracking system, so that each solar cell panel works at the optimal power point, the cell panel group can work under the working condition of higher output power, and the stability of an airplane power supply system is ensured.

Description

Small-sized solar unmanned aerial vehicle

Technical Field

The utility model relates to a small-size solar energy unmanned aerial vehicle.

Background

Numerous advantages of low altitude solar powered aircraft, such as: providing a communication platform for remote mountainous areas; the close shot picture from the ground has high resolution, can detect forest fires, search for rescue and the like, and has wide application. The small low-altitude unmanned aerial vehicle which generally depends on fuel oil carried by the small low-altitude unmanned aerial vehicle as a power source has the problems of less range, short space-reserving time and great limitation on space-reserving height. In addition, in some cases, small drones are required to perform high-altitude or remote tasks, especially for search and rescue tasks, which require long-endurance day-and-night flights. Because unmanned aerial vehicle self takes off weight is less, can't carry sufficient fuel, will not satisfy the requirement of flight task.

Taking border investigation as an example, China has broad range of members and complex environment, and the reconnaissance aircraft using active service can be influenced by voyage, voyage and local environment, and can not realize all-weather 24-hour uninterrupted monitoring. If the unmanned reconnaissance plane takes off for a plurality of times, great burden is caused to ground maintenance personnel.

Military aspects: the remote early warning, ground reconnaissance and monitoring action distance and time are limited, the survival capability is low, and the progress of informatization construction of our army is severely limited.

In the civil aspect: the coverage area of the TV service, atmospheric environment monitoring and weather forecasting, disaster forecasting and emergency treatment is limited.

SUMMERY OF THE UTILITY MODEL

To the above-mentioned problem of prior art, the utility model provides a small-size solar energy unmanned aerial vehicle realizes the short distance and throws and fly, realizes when descending that the glides descend.

To for example above-mentioned border investigation etc. application, if can take off at the border depending on solar energy for the unmanned aerial vehicle of power, fly to appointed place sky, cooperate the autopilot system, provide whole journey monitoring and reconnaissance 24 hours, just can raise the efficiency and alleviate ground personnel's burden greatly, solar energy unmanned aerial vehicle can accomplish this kind of reconnaissance task of staying idle for a long time.

Therefore, the utility model aims at providing a small-size solar energy unmanned aerial vehicle.

According to the utility model discloses an aspect provides a small-size solar energy unmanned aerial vehicle, its characterized in that includes:

a body;

a wing, wherein the outer panel has a dihedral;

a motor arranged at the front end of the machine body;

a propeller mounted on said motor;

a horizontal tail and a vertical tail connected with the body.

According to the utility model discloses an aspect provides a small-size solar unmanned aerial vehicle, its characterized in that includes:

comprises a machine body of a machine room,

the motor with the folding propeller is arranged at the front end of the airplane body and is used for providing power required by the flight for the airplane,

a wing having a four-section wing design including a first mid-section wing, a second mid-section wing, and a first outer-section wing and a second outer-section wing,

an aileron disposed at a trailing edge of the first outer wing section and the second outer wing section,

a horizontal tail wing and a vertical tail wing connected with the machine body,

a first solar cell panel group and a second solar cell panel group which are respectively arranged on the upper surfaces of a first middle section wing and a second middle section wing of the wing,

a lithium battery pack arranged in the cabin,

a sliding hook group with small wheels, which is used for realizing sliding when landing,

wherein:

the wingtips of the horizontal tail wing, the vertical tail wing, the first outer section wing and the second outer section wing are all designed by adopting streamline flow guidance, namely the wingtips and winglets are designed,

the plane shape of the wing is rectangular and has no sweepback angle.

Drawings

Fig. 1 shows an overall outline view of a small-sized solar unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 2 shows a top view of the small solar unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 3 shows a solar panel group packaging diagram of a small-sized solar unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 4 shows a foldable propeller profile of a small-sized solar unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 5 shows a sectional side view of a cabin of a small solar drone according to one embodiment of the present invention.

Fig. 6 shows a schematic view of the connection between the wing and the cabin of a small-sized solar unmanned aerial vehicle according to an embodiment of the present invention.

Detailed Description

In order to solve the problem that the range, the air-remaining time and the flying height of the existing unmanned aerial vehicle are limited, and the function of the small unmanned aerial vehicle can be expanded, so that the small unmanned aerial vehicle can depend on self power to complete the flight tasks which cannot be completed originally in high altitude and long-distance long endurance.

In order to ensure that the solar cell panel is more attached to the wing surface and the integrity of the wing section is ensured, thereby ensuring the pneumatic efficiency of the whole machine, the utility model adopts the whole-piece solar cell panel which is attached to the upper surface of the wing; and simultaneously, the utility model discloses in solar cell panel's packaging process, laminated the printing opacity membrane on its surface, improved solar cell panel's spotlight ability.

According to the utility model discloses a small-size solar energy unmanned aerial vehicle's overall arrangement

The small-sized solar unmanned aerial vehicle according to one embodiment of the utility model adopts a conventional pneumatic layout, as shown in fig. 1 and 2, and has an upper single-wing design, and a motor (2) with a folding propeller (3) is installed at the front end of a cabin (1) to provide the power required by the flight for the aircraft; the rear end is connected with the machine body (12). The aircraft cabin (1) adopts an elliptical design, so that the flight resistance is reduced while the loading capacity of airborne equipment is ensured.

The plane shape of the wing is rectangular without sweepback angles, the four-section wing design is divided into a middle section of wings (4) and (5) and an outer section of wings (6) and (7), the outer section of wings (6) and (7) have 3-degree up-down angles, the flight stability is improved, and the wings are divided into four sections of high aspect ratio design; the carbon fiber pipe frameworks in the middle section wings (4,5) are directly connected with the engine room (1), so that the strength and the rigidity of the whole machine are ensured. The trailing edge of the outer section wing is provided with an aileron (8). The horizontal tail (9) and the vertical tail (10) are connected with the body (12). The wingtips of the horizontal tail wing (9), the vertical tail wing (10), the left outer section wing (6) and the right outer section wing (7) are in streamline flow guide design, namely wingtips winglets are adopted, and the design can effectively reduce flight resistance and save energy. In one embodiment, the nacelle (1), the fuselage (12), the wings (4,5,6,7) and the empennage (9,10) are all made of carbon fiber composite. A camera (13) is arranged below the body and used for implementing tasks such as remote monitoring, reconnaissance and recording. The utility model discloses a small-size solar unmanned aerial vehicle is furnished with slip hook group (11) of taking the steamboat, can realize the rollerball when descending, reduces frictional resistance protection airborne equipment safety.

Solar cell panel group and lithium battery pack arrangement mode

According to the utility model discloses an embodiment, as shown in fig. 2, solar cell panel group (101, 102) have been arranged respectively at the upper surface of the left section of wing and right section, the utility model discloses the solar cell panel group that uses has carried out multilayer encapsulation to solar cell panel, can merge with the wing type is perfect. The lithium battery pack (103) used by the machine is arranged in the engine room (1), so that reasonable balance weight of the whole machine is realized and the stability of a circuit is guaranteed. The wingtips are designed in a streamline flow guiding mode, namely, the wingtips are designed in a winglet streamline mode (104), flying resistance can be effectively reduced, and energy is saved.

Solar cell panel packaging mode

According to one embodiment of the present invention, as shown in fig. 3, a plurality of single crystal silicon solar cells are packaged on a solar cell panel group (101, 102) in a multi-layer packaging manner. The solar cell panel group takes a soft plastic film as a bottom film (201); according to a specific embodiment, the packaging mode is that a layer of EVA (ethylene vinyl acetate) hot melt adhesive film (202) is arranged between the solar cell panel (203) and the bottom film (201); the upper surface of the solar panel (203) is also covered with a layer of EVA hot melt adhesive film (204); a light-transmitting film (205) is packaged on the upper surface of the upper EVA hot-melt adhesive film (204), and the light-transmitting film can improve the light-gathering capacity of the solar cell panel set; the EVA hot melt adhesive films (202 and 204) have the function of bonding the bottom film (201), the solar cell panel (203) and the light transmission film (205), and the stability of the solar cell panel packaging structure is ensured.

Folding propeller design

The folding propeller (9) of the solar airplane according to one embodiment of the invention is shown in figure 4. Wherein, the two paddles (401, 402) are respectively connected to the paddle clamp (405) through two rotating shafts (403, 404); the paddle holder (405) is connected to the motor (2) through the shaft hole (406). Wherein, paddle (401, 402) can rotate around pivot (403, 404), realizes the folding of paddle, and when motor (2) drove the screw and rotate, paddle (401, 402) can be opened under the centrifugal force effect, provides thrust for unmanned aerial vehicle. The beneficial effect of this design lies in, when unmanned aerial vehicle descends, motor (2) stall, and paddle (401, 402) can be packed up automatically, can prevent effectively like this that the paddle from colliding with ground, avoids the motor to damage.

Airborne electronic arrangement and sliding hook group design with small wheels

A sectional side view of a nacelle (1) of a solar aircraft according to one embodiment of the invention is shown in fig. 5. Wherein the lithium battery pack (502) is arranged in the nacelle (1). Furthermore, a solar powered aircraft according to an embodiment of the invention comprises a set of hooks with small wheels (11); the sliding hook group (11) comprises a sliding hook (506) and a small wheel (507), and when the unmanned aerial vehicle descends, the small wheel can be used for sliding and running, so that the stability during descending is ensured.

Connection mode of wing and cabin

The schematic view of the connection between the wings (4,5) and the nacelle (1) of the solar aircraft according to an embodiment of the present invention is shown in fig. 6, and fig. 6 is a cross-sectional view of the wings (4,5) and the nacelle (1). The wing comprises a carbon fiber pipe wing beam (601) which is inserted into a plurality of perforated wing ribs (602), so that the wing beam (601) and the wing (4,5) are fixed, and the structural strength of the airplane wing is guaranteed. Meanwhile, the carbon fiber pipe wing beam (601) is inserted between the cabin (1) and the wings (4 and 5) in a penetrating manner, and the function of connecting the wings (4 and 5) and the cabin (1) is achieved. The connecting mode ensures the easy disassembly and easy maintenance performance of the whole machine and simultaneously improves the structural strength of the whole machine.

The utility model discloses an advantage and beneficial effect include:

1) this small-size solar unmanned aerial vehicle adopts the overall arrangement form of conventional overall arrangement, single tail boom, type of falling T fin, has very high reliability to the wing has adopted streamlined design to save energy consumption.

2) Compared with the conventional power small unmanned aerial vehicle, the power supply of the small unmanned aerial vehicle through the solar cell panel and the lithium battery pack has longer flight time and longer flight distance, and can play a long-time cruising task.

3) The conventional monocrystalline silicon battery panel is used, and the multi-layer packaging mode is adopted to be combined with the wing, so that the completeness of the wing shape is guaranteed, and the pneumatic efficiency of the whole machine is guaranteed.

4) The solar flat plane aircraft takes off by means of power provided by the solar cell panel and the lithium battery pack, and can completely take off by means of solar power in a flat plane flight state.

5) The single-generator motor is used as driving power, and has the advantages of high force efficiency, large torque force and low rotating speed.

6) Each solar cell panel group is provided with an independent maximum power point tracking system, so that each solar cell panel can work at the optimal power point, the solar cell panel groups can work under the working condition of higher output power, and the stability of an airplane power supply system is ensured.

7) The lithium battery pack is provided with an overcharge protection system, so that the overcharge of the battery can be prevented, and the service life of the battery is prolonged.

8) Adopt foldable screw design, and the utility model discloses do not have the undercarriage, can realize the short distance when taking off and throw and fly no runway requirement, realize the glide when descending and descend.

9) The bottom of the cabin is provided with a sliding hook group with small wheels, so that sliding can be realized during landing, and the stability during landing is ensured.

10) The carbon fiber pipe framework inside the wing is directly connected with the engine room, so that the strength and the rigidity of the whole machine are ensured.

Claims

1. A small-size solar unmanned aerial vehicle, its characterized in that includes:

comprises a fuselage (12) of the nacelle (1),

a motor (2) which is arranged at the front end of the machine body (12) and is provided with a folding propeller (3),

the wing comprises a first middle section wing (4), a second middle section wing (5), a first outer section wing (6) and a second outer section wing (7),

an aileron (8) arranged at the trailing edge of the first outer wing section (6) and the second outer wing section (7),

a horizontal tail (9) and a vertical tail (10) connected with the body (12),

a first solar cell panel group (101, 301) and a second solar cell panel group (102, 302) which are respectively arranged on the upper surfaces of a first middle wing (4) and a second middle wing (5) of the wing,

a lithium battery pack (306) arranged within the nacelle (1),

a sliding hook group (11) with small wheels for realizing sliding when landing,

wherein:

the wingtips of the horizontal tail wing (9), the vertical tail wing (10), the first outer section wing (6) and the second outer section wing (7) are all designed by adopting streamline flow guidance, namely the wingtips are designed by adopting wingtips winglets,

the plane shape of the wing is rectangular without sweepback angle

Wherein:

a plurality of solar panels (203) are encapsulated in the first solar panel group (101, 301) in a multi-layer encapsulation manner,

a plurality of solar panels (203) are encapsulated in the second solar panel group (102, 302) in a multi-layer encapsulation,

the first solar cell panel group (101, 301) and the second solar cell panel group (102, 302) each comprise a carrier film (201),

the bottom film (201) is a soft plastic film,

a first ethylene-vinyl acetate copolymer hot melt adhesive film (202) is arranged between the solar panel (203) and the bottom film (201),

the upper surface of the solar panel (203) is covered with a second ethylene-vinyl acetate copolymer hot melt adhesive film (204),

a light-transmitting film (205) is packaged on the upper surface of the second ethylene-vinyl acetate copolymer hot-melt adhesive film (204),

the first ethylene-vinyl acetate copolymer hot melt adhesive film (202) and the second ethylene-vinyl acetate copolymer hot melt adhesive film (204) have the function of bonding the bottom film (201), the solar panel (203) and the light transmission film (205).

2. The small solar drone according to claim 1, characterized in that:

the folding propeller (3) comprises two blades (401, 402) which are respectively connected to a blade clamp (405) through two rotating shafts (403, 404);

the paddle clamp (405) is connected to the motor (2) through the shaft hole (406),

wherein the content of the first and second substances,

the paddle (401, 402) can rotate around the rotating shaft (403, 404) to realize the folding of the paddle,

when the motor (2) drives the propeller to rotate, the blades (401, 402) are opened under the action of centrifugal force to provide thrust for the small-sized solar unmanned aerial vehicle,

when the small-sized solar unmanned aerial vehicle lands and the motor (2) stops rotating, the blades (401 and 402) are automatically retracted.

3. The small solar drone according to claim 1, characterized in that:

the sliding hook group (11) comprises a sliding hook (506) and a small wheel (507).

4. The small solar drone according to claim 1, characterized in that:

the first middle section wing (4) and the second middle section wing (5) comprise carbon fiber pipe wing beams (601) which are inserted into a plurality of perforated wing ribs (602), so that the carbon fiber pipe wing beams (601) are fixed with the first middle section wing (4) and the second middle section wing (5),

the carbon fiber pipe wing beam (601) is inserted into the cabin (1) and the first middle section wing (4) and the second middle section wing (5) in a penetrating mode, and therefore the effect of connecting the first middle section wing (4) and the second middle section wing (5) with the cabin (1) is achieved.

5. The small solar drone of claim 1, further comprising:

a camera (13) arranged below the body.

6. The small solar drone according to claim 1, characterized in that:

the solar panel (203) comprises a single crystalline silicon solar cell.