CN104044741B - An unmanned aerial vehicle capable of solar tracking and its charging process - Google Patents

Abstract

A drone capable of solar tracking, including a drone body, a main rotating motor, a fixed seat, a photosensitive sensor, a flip-type solar panel, a panel fixing frame, a side rotating motor, a fixing frame, a lifting cylinder and There is a main rotating motor on the wing and the fuselage of the UAV, and the fixing seat is fixed on the rotating shaft of the main rotating motor. The flip solar panels are fixed in rows in the panel fixing frame, and there are side rotating motors on both sides of the panel fixing frame. , the rotating shaft of the side rotating motor is fixed on the middle part of the side end of the battery plate fixing frame, there is a lifting cylinder under the fixing frames on both sides of the battery plate fixing frame, the lifting cylinder is fixed on the fixing seat, and there are 4 photosensitive sensors on the fixing seat. The solar tracking mechanism on the top of the drone of the present invention is arranged in rows of flip-type solar panels that can be flipped at the same time, while the horizontal plane rotation is controlled by the main rotating motor, so that the solar energy can be collected to the maximum extent, and the cost is lower. Installation is more convenient.

Description

An unmanned aerial vehicle capable of solar tracking and its charging process

technical field

The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle capable of tracking solar energy and its charging process.

Background technique

UAV is an unmanned aircraft controlled by radio remote control or self-contained program control device. With the continuous advancement of science and technology, the development of UAV technology is becoming more and more mature, and its application is becoming more and more extensive. It can not only be used to complete battlefield Military tasks such as reconnaissance and surveillance, positioning and calibration, damage assessment, electronic warfare, etc., can also be used as target drones, and can also be used for civilian purposes, such as border patrol, nuclear radiation detection, aerial photography, aerial prospecting, disaster monitoring, traffic patrol, public security monitoring etc.

Due to the need for functional expansion of UAVs, it is necessary to improve the overall endurance, so the endurance has a great impact on its performance. At present, the best way to improve the endurance of UAVs is to make the wings of UAVs into solar panels. Or laying solar panels on the wings, making the wings into solar panels often requires a large area and high cost, and laying solar panels on the wings will affect the flight, so the best way at present is in A solar collector is installed on the fuselage, but due to the limitation of the fuselage, the solar panels that can be installed are limited. Therefore, in order to improve the endurance effect, a solar tracking device must be used.

At present, the domestic patent has the patent number CN201210373741.5 and the name is solar-powered unmanned aerial vehicles. As shown in Figures 1 and 2, solar-powered tracking technology is used, but it has the following problems. First, each battery panel of the application is assembled on the aircraft by tracking equipment. , so the cost is extremely high, and the installation is difficult. If the solar panels are installed too densely, it is easy to interfere with each other and affect the solar energy collection effect. And because most of the drones fly in the sky, and the solar panels are on the plane, so Solar panels in this way are particularly prone to damage when encountering strong winds or other bad weather, and there are certain requirements for the flight speed of the aircraft during take-off and landing or when performing special tasks. At this time, solar panels in this way will affect the flight.

Contents of the invention

In view of the above problems, the present invention provides an unmanned aerial vehicle capable of solar tracking and its charging process. The reversible solar panels of the solar tracking mechanism on the top of the unmanned aerial vehicle are arranged in rows, and are turned over by the side rotation motor control, while The horizontal plane rotation is controlled by the main rotating motor, so that the solar energy can be collected to the maximum extent. Compared with the design mechanism of a single flip solar panel, the cost is lower and the installation is more convenient. To achieve this purpose, the present invention provides a Solar tracking UAV, including UAV fuselage, main rotating motor, fixing base, photosensitive sensor, flip solar panel, panel fixing frame, side rotating motor, fixing frame, lifting cylinder and wings, all There are wings on both sides of the fuselage of the UAV, the main rotating motor is arranged on the fuselage of the UAV, the fixing seat is fixed on the rotating shaft of the main rotating motor, and there are at least two battery board fixing frames on the fixing seat , the flip-type solar panels are fixed in a row in the panel fixing frame, and there are side rotating motors on both sides of the panel fixing frame, and the rotating shaft of the side rotating motor is fixed in the middle of the side end of the panel fixing frame. The side rotating motor is fixed in the through hole of the fixing frame through the fixing piece. There is a lifting cylinder under the fixing frame on both sides of the battery plate fixing frame. The fixing frame is fixed at the end of the telescopic rod of the lifting cylinder. The lifting cylinder is fixed on On the fixed seat, there are four photosensitive sensors on the fixed seat, and the photosensitive sensors circle around the center of the fixed seat at equal angles.

As a further improvement of the present invention, there is a groove on the fixed seat, and the lifting cylinder is fixed in the groove on the fixed seat. Since the lifting cylinder itself will occupy a certain height, it is better to fix the lifting cylinder on the groove on the fixed seat. In this way, the flip-up solar panel can be stowed as much as possible to reduce the impact of flight.

As a further improvement of the present invention, there is a battery panel placement groove on the fixing base, and the battery panel placement groove is below the battery panel fixing frame. After the battery panel placement groove is set, the flip-type solar panel can be received in it, so that It can further prevent the solar panel from being damaged or reduce the impact on flight.

As a further improvement of the present invention, a wing-type solar panel is laid on the wing, and the collected solar energy and the solar energy collected by the solar tracking mechanism together provide power for the drone.

As a further improvement of the present invention, the fixed seat is rectangular or circular. When the fixed seat is rectangular, there are more flip-type solar panels that can be installed, and the circular fixed seat has little impact on flight. Manufacturers can Choose according to the actual situation of man-machine.

As a further improvement of the present invention, the UAV fuselage and the fixing seat are made of ultra-light and high-specific-strength magnesium-lithium Mg-Li-based composite material reinforced by boron carbide B4C particles obtained through thin-film metallurgy forming technology. The weight is extremely light, so the overall weight of the drone can be greatly reduced, and it can obtain a fine grain structure after cold rolling, the yield strength is 50% higher than that of the as-cast structure, and the specific stiffness is 22% higher than that of commercial aluminum alloys and titanium alloys , so the overall strength of the UAV can be greatly improved.

As a further improvement of the present invention, the outside of the UAV fuselage and the fixing seat are coated with nano-particle ferromagnetic material Mn-Zn, Ni-Zn ferrite and ferroelectric BaTiO3 composite nano-absorbing Composite materials, because detection and early warning is an important function of drones, so when used in these fields, the stealth capability is very high, and although the invention can put away the solar panels, it is still easy to be detected by enemy radars. In order to be invisible, the surface coating of the drone is made of self-developed nano-particle ferromagnetic material Mn-Zn, Ni-Zn ferrite and ferroelectric BaTiO3 to form a coated nano-absorbing composite material, which can be extremely Greatly improve the overall wave absorption performance of drones.

The charging process of an unmanned aerial vehicle capable of solar tracking in the present invention, the specific charging process is as follows:

1) When the aircraft is not in flight and is in a stop state, the best light direction and light angle are judged by the photosensitive sensor, the main rotating motor drives the fixed seat to rotate to the best direction, and the side rotating motor drives the flip-type solar panel to rotate to The best angle, and constantly adjust the direction of the fixed seat and the flip solar panel according to the results obtained by the photosensitive sensor, so as to achieve the best charging effect;

2) When the aircraft is in the state of take-off or landing, due to the large air flow during take-off or landing, in order to prevent the air flow from damaging the flip-type solar panel, when taking off or landing, the side-rotating motor flips the flip-type solar panel to and fixes it The end faces of the seat are parallel, and the telescopic rod of the lifting cylinder is lowered to drive the flip solar panel to the panel placement slot to prevent the rising or falling airflow from causing damage to the flip solar panel;

3) When the aircraft is in flight, the photosensitive sensor senses that its light intensity is not high, and it is in cloudy or bad weather conditions, the flip solar panel is driven by the lifting cylinder to the panel placement slot;

4) When the aircraft is in flight state, the photosensitive sensor senses that the light is in a sunny state, and the flip solar panel is raised by the telescopic rod of the lifting cylinder, and the best light direction and light angle are judged by the photosensitive sensor, and fixed by the main rotating motor The seat rotates to the best direction, and the side rotation motor drives the flip solar panel to rotate to the best angle, and constantly adjusts the direction of the fixed seat and the flip solar panel according to the results obtained by the photosensitive sensor to achieve the best charging. can effect.

As a further improvement of the present invention, when the aircraft is in flight, the photosensitive sensor senses that the light is in a sunny state, the aircraft flies at a speed beyond normal speed, or the aircraft performs special tasks, the flip solar panel is driven by the lifting cylinder into the panel placement slot , because the flip-up solar panel can greatly improve solar energy collection after rising, but it will affect the flight speed. Best to put it away.

The invention provides an unmanned aerial vehicle capable of solar tracking and its charging process. The top of the unmanned aerial vehicle is provided with a solar tracking mechanism, and the rotation is controlled by the main rotating motor, and then each row of flipped solar panels is controlled by the side rotating motor. Turning over, compared with the overall turning over, the effect of collecting solar energy is better, the cost is lower than that of a single turning over, and the installation is more convenient. In addition, there are battery board placement slots on the fixing seat of the present invention, and the motor fixing frames on both sides of the turning solar panel in rows There is a lifting cylinder at the bottom, and in cloudy days or special circumstances, the flip-type solar panel can be received into the panel placement groove through the lifting cylinder, so that the solar panel is not easy to be damaged in bad weather. In addition, the invention has no There are wing-type solar panels on the wings of the man-machine, and since it is mainly powered by solar tracking panels, the wings are only auxiliary power supply, so the design requirements for the wing area are not high, which can greatly reduce the design of the wing. In addition, the present invention designs a corresponding charging process according to the sun's altitude angle and azimuth angle and the operating rules of the UAV, so as to maximize the solar energy collection efficiency of the UAV and the endurance of the UAV.

Description of drawings

Fig. 1 is prior art schematic diagram;

Fig. 2 is a partial schematic view of the prior art;

Fig. 3 is a structural diagram of the present invention;

Fig. 4 is a side view of the present invention;

Fig. 5 is a partial structural diagram of the present invention;

The components in the figure are:

1. UAV fuselage; 2. Main rotating motor; 3. Fixing seat;

4. Photosensitive sensor; 5. Flip solar panel; 6. Panel fixing frame;

7. Battery board placement slot; 8. Side rotation motor; 9. Fixing frame;

10. Lifting cylinder; 11. Fixing parts; 12. Wing;

13. Winged solar panels.

Detailed ways

The present invention is described in detail below in conjunction with accompanying drawing and example:

The invention provides an unmanned aerial vehicle capable of solar tracking and its charging process. The overturned solar panels of the solar tracking mechanism on the top of the unmanned aerial vehicle are arranged in a row, and the overturning is controlled by a side rotation motor, while the horizontal plane rotation is controlled by The main rotating motor is controlled, so that the solar energy can be collected to the maximum extent. Compared with a single flip solar panel, the cost of this mechanism is lower and the installation is more convenient.

As an example of the present invention, the present invention provides an unmanned aerial vehicle capable of solar tracking, including an unmanned aerial vehicle body 1, a main rotating motor 2, a fixed seat 3, a photosensitive sensor 4, a flip-type solar panel 5, Battery plate fixing frame 6, side rotating motor 8, fixing frame 9, lifting cylinder 10 and wing 12, there are wings 12 on both sides of the drone fuselage 1, and the main rotating motor is arranged on the drone fuselage 1 2. The fixing base 3 is fixed on the rotating shaft of the main rotating motor 2, and there are at least two battery panel fixing frames 6 on the fixing base 3, and the flipped solar panels 5 are fixed on the battery panel fixing frames 6 in a row Inside, there are side rotating motors 8 on both sides of the battery panel fixing frame 6, the rotating shaft of the side rotating motor 8 is fixed in the middle of the side end of the battery panel fixing frame 6, and the side rotating motor 8 is fixed on the fixing frame through a fixing piece 11 9, there is a lifting cylinder 10 under the fixing frame 9 on both sides of the battery plate fixing frame 6, the fixing frame 9 is fixed on the end of the telescopic rod of the lifting cylinder 10, and the lifting cylinder 10 is fixed on the fixing seat 3 Above, there are four photosensitive sensors 4 on the fixed seat 3, and the photosensitive sensors 4 circle around the center of the fixed seat 3 at equal angles.

As a kind of best specific example of the present invention, the present invention provides a kind of unmanned aerial vehicle that can carry out solar tracking as shown in Fig. 3, Fig. 4 and Fig. 5 of structural diagram, comprise unmanned aerial vehicle fuselage 1, main rotating motor 2 , fixed seat 3, photosensitive sensor 4, flip solar panel 5, panel fixed frame 6, side rotating motor 8, fixed frame 9, lifting cylinder 10 and wing 12, the two sides of described UAV fuselage 1 Wings 12 are arranged, and wing-type solar panels 13 are laid on the wings 12. In order to further improve the endurance effect, wing-type solar panels can be laid on the wings to collect solar energy, and the collected solar energy and solar tracking mechanism The collected solar energy supplies power for the UAV together. There is a main rotating motor 2 on the body 1 of the UAV, and the fixed seat 3 is fixed on the rotating shaft of the main rotating motor 2. The fixed seat 3 is circular, When the fixed seat is rectangular, there are many flip-type solar panels that can be installed, and the circular fixed seat has little impact on flight. The manufacturer can choose according to the actual use of the drone. The fixed seat 3 is shown in Figure 2. Shown are at least two battery panel fixing frames 6, the flip solar panels 5 are fixed in a row in the panel fixing frame 6, and there are side rotating motors 8 on both sides of the battery panel fixing frame 6, and the side rotating motors The rotating shaft of 8 is fixed in the middle part of the side end of the battery plate fixing frame 6, and the side rotating motor 8 is fixed in the through hole of the fixing frame 9 through the fixing piece 11. Cylinder 10, the fixed frame 9 is fixed on the end of the telescopic rod of the lifting cylinder 10, the fixed seat 3 has a groove, and the lifting cylinder 10 is fixed in the groove on the fixed seat 3, because the lifting cylinder itself will occupy a certain height , so it is best to fix the lifting cylinder in the groove on the fixed seat, so that the flip-type solar panel can be packed up as much as possible to reduce the impact of flight. There is a battery panel placement groove 7 on the fixed seat 3, and the battery The board placement groove 7 is below the battery board fixing frame 6. After the battery board placement groove is set, the flip-type solar panel can be received in it, which can further prevent the solar panel from being damaged or reduce the impact on flight. There are four photosensitive sensors 4 on the seat 3, and the photosensitive sensors 4 circle around the center of the fixed seat 3 at equal angles.

The fuselage and the fixing seat of the UAV described in the present invention are all made of ultra-light, high-specific-strength magnesium-lithium-lithium Mg-Li-based composite materials reinforced by boron carbide B4C particles obtained through thin-film metallurgy forming technology. The material is extremely light in weight, so It can greatly reduce the overall weight of the drone, and it can obtain a fine grain structure after cold rolling, the yield strength is 50% higher than that of the cast structure, and the specific stiffness is 22% higher than that of commercial aluminum alloys and titanium alloys, so it can be greatly improved. The overall strength of the UAV, the UAV fuselage and the outside of the fixed seat are all coated with nanoparticles of ferromagnetic material Mn-Zn, Ni-Zn ferrite and ferroelectric BaTiO3 composite materials, due to Reconnaissance and early warning is an important function of unmanned aerial vehicles, so it requires high stealth ability when used in these fields, and although the present invention can put away the solar panels, it is still easy to be detected by enemy radar, so the present invention has no In order to be invisible, the surface coating of the man-machine uses self-developed nano-particle ferromagnetic material Mn-Zn, Ni-Zn ferrite and ferroelectric BaTiO3 to form a coated nano-absorbing composite material, which can greatly Improve the overall wave absorption performance of drones.

The charging process of an unmanned aerial vehicle capable of solar tracking in the present invention, the specific charging process is as follows:

1) When the aircraft is not in the flying state and is in the parking state, the best light direction and light angle are judged by the photosensitive sensor 4, the main rotating motor 2 drives the fixed seat 3 to rotate to the best direction, and the side rotating motor 8 drives the flip solar energy The battery panel 5 is rotated to an optimal angle, and the direction of the fixing seat 3 and the flipped solar panel 5 are constantly adjusted according to the results obtained by the photosensitive sensor 4, so as to achieve the best charging effect;

2) When the aircraft is in the take-off or landing state, due to the large air flow during take-off or landing, in order to prevent the airflow from damaging the flip-type solar panel 5, the side rotation motor 8 flips the flip-type solar panel 5 during take-off or landing To be parallel to the end surface of the fixed seat 3, the telescopic rod of the lifting cylinder 10 descends to drive the flip solar panel 5 into the panel placement groove 7, so as to prevent the upward or downward airflow from causing damage to the flip solar panel 5;

3) When the aircraft is in flight, the photosensitive sensor 4 senses that its light intensity is not high, and it is in cloudy or bad weather conditions, the flip solar panel 5 is driven by the lifting cylinder 10 to the panel placement slot 7;

4) When the aircraft is in flight, the light sensor 4 senses that the light is in a sunny state, and the flip solar panel 5 is raised by the telescopic rod of the lifting cylinder 10, and the best light direction and light angle are judged by the light sensor 4. The rotating motor 2 drives the fixed seat 3 to rotate to the optimal direction, and the side rotating motor 8 drives the flip-type solar panel 5 to rotate to the optimal angle, and continuously adjusts the direction of the fixed seat 3 and the flip-type solar panel 5 according to the results obtained by the photosensitive sensor 4. The solar panel 5 is adjusted to achieve the best charging effect.

Wherein when the aircraft is in the flying state, the photosensitive sensor 4 senses that the light is in a sunny state, and if the aircraft flies beyond the normal speed or the aircraft performs special tasks, the flip solar panel 5 is driven by the lifting cylinder 10 to the panel placement groove 7, Although the flip-up solar panel can greatly increase solar energy collection after it is raised, it will affect the flight speed. Better put it away.

The above description is only a preferred example of the present invention, and is not intended to limit the present invention in any other form, and any modification or equivalent change made according to the technical essence of the present invention still belongs to the scope of protection claimed by the present invention.

Claims (9)

1. An unmanned aerial vehicle capable of tracking solar energy, including an unmanned aerial vehicle body (1), a main rotating motor (2), a fixed seat (3), a photosensitive sensor (4), and a flip solar panel (5 ), battery plate fixing frame (6), side rotating motor (8), fixing frame (9), lifting cylinder (10) and wing (12), and there are wings on both sides of the UAV body (1) ( 12), characterized in that: there is a main rotating motor (2) on the drone body (1), the fixing seat (3) is fixed on the rotating shaft of the main rotating motor (2), and the fixing seat ( 3) There are at least two battery panel fixing frames (6) on it, and the flip-type solar panels (5) are fixed in a row in the battery panel fixing frame (6), and the battery panel fixing frame (6) has two sides The side rotating motor (8), the rotating shaft of the side rotating motor (8) is fixed in the middle of the side end of the battery plate fixing frame (6), and the side rotating motor (8) is fixed on the fixing frame (9) through the fixing piece (11) ), there is a lifting cylinder (10) under the fixing frame (9) on both sides of the battery panel fixing frame (6), and the fixing frame (9) is fixed at the end of the telescopic rod of the lifting cylinder (10), The lift cylinder (10) is fixed on the fixed seat (3), and there are four photosensitive sensors (4) on the fixed seat (3), and the photosensitive sensors (4) are equiangular around the fixed seat (3) Center for a week. 2. An unmanned aerial vehicle capable of solar tracking according to claim 1, characterized in that: there is a groove on the fixed seat (3), and the lifting cylinder (10) is fixed on the fixed seat (3) in the slot. 3. An unmanned aerial vehicle capable of solar tracking according to claim 1, characterized in that: there is a battery board placement slot (7) on the fixed seat (3), and the battery board placement slot (7) Under the panel fixing frame (6). 4. The UAV capable of solar tracking according to claim 1, characterized in that: a wing-type solar panel (13) is laid on the upper part of the wing (12). 5. An unmanned aerial vehicle capable of solar tracking according to claim 1, characterized in that: the fixing seat (3) is rectangular or circular. 6. An unmanned aerial vehicle capable of solar tracking according to claim 1, characterized in that: the unmanned aerial vehicle fuselage (1) and the fixing seat (3) both adopt carbonization obtained by thin film metallurgy forming technology It is made of ultra-light and high specific strength magnesium-lithium Mg-Li matrix composite material reinforced by boron B4C particles. 7. A UAV capable of solar tracking according to claim 6, characterized in that: the exterior of the UAV body (1) and the fixing seat (3) are coated with nano-particle ferromagnetic substances Nano-absorbing composite material composed of Mn-Zn, Ni-Zn ferrite and ferroelectric BaTiO3. 8. According to the charging process of a kind of unmanned aerial vehicle capable of solar tracking according to any one of claims 1-7, the specific charging process is as follows, characterized in that: 1) When the aircraft is not in the flight state and is in the parking state, the best light direction and light angle are judged by the photosensitive sensor (4), and the main rotating motor (2) drives the fixed seat (3) to rotate to the best direction, and rotates from the side The motor (8) drives the flip solar panel (5) to rotate to an optimal angle, and constantly adjusts the direction of the fixing seat (3) and the flip solar panel (5) according to the results obtained by the photosensitive sensor (4). In order to achieve the best charging effect; 2) When the aircraft is in the take-off or landing state, due to the large air flow during take-off or landing, in order to prevent the air flow from damaging the flip-type solar panel (5), when taking off or landing, the side rotation motor (8) will turn the flip-type solar panel The battery panel (5) is turned over to be parallel to the end surface of the fixed seat (3), and the telescopic rod of the lifting cylinder (10) descends to drive the flipped solar panel (5) into the battery panel placement slot (7) to prevent the rising or falling airflow from affecting the solar panel (5). Flip-up solar panel (5) causing damage; 3) When the aircraft is in flight, the photosensitive sensor (4) senses that the light intensity is not high, and it is in cloudy or bad weather conditions, the flip solar panel (5) is driven by the lifting cylinder (10) to place the panel In the groove (7); 4) When the aircraft is in flight state, the photosensitive sensor (4) senses that the light is in a sunny state, and the flip solar panel (5) is lifted by the telescopic rod of the lifting cylinder (10), and the photosensitive sensor (4) judges the best For the direction and angle of light, the main rotating motor (2) drives the fixed seat (3) to rotate to the best direction, and the side rotating motor (8) drives the flip solar panel (5) to rotate to the best angle, and continuously according to The result obtained by the photosensitive sensor (4) adjusts the direction of the fixing seat (3) and the reversible solar panel (5) to achieve the best charging effect. 9. The charging process of an unmanned aerial vehicle capable of solar tracking according to claim 8, characterized in that: when the aircraft is in the flight state, the photosensitive sensor (4) senses that the light is in a sunny state, and the aircraft exceeds normal When flying at high speed or when the aircraft is performing special tasks, the flip solar panel (5) is driven by the lifting cylinder (10) into the panel placement slot (7).