CN112141329A - Vertical take-off and landing solar unmanned aerial vehicle - Google Patents

Abstract

The invention proposes a vertical take-off and landing solar unmanned aerial vehicle, comprising: a fuselage, a frame, a wing group, a fixed wing and a rotor group; the wing group includes a front wing and a rear wing, and the front wing and the rear wing are connected by a connecting piece Fixed, the front wing includes the front main wing and the split aileron, the rear wing includes the rear main wing and the elevator, and the front wing is fixed on the fuselage; the rotor group includes 4 or more rotor propeller groups, and the rotor propeller group is installed on the frame ; The fuselage includes the nose, nacelle and rudder. The invention adopts a cracked aileron structure, and there is no gap on the surface of the wing, which not only satisfies the excellent aerodynamic performance of the wing, but also provides a favorable guarantee for laying solar panels on the wing; Wing drones can increase the cruising time; the rotor control scheme enables the drones to have vertical take-off and landing functions. Based on longer cruising time, it can further expand its application scenarios, provide operational efficiency and save costs.

Description

A vertical take-off and landing solar unmanned aerial vehicle

technical field

The invention belongs to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing solar unmanned aerial vehicle.

Background technique

At this stage, due to the short battery life of fixed-wing UAVs, its wide application in the market is limited. In order to improve the cruising time of fixed-wing UAVs, the use of solar panels as auxiliary power has become a new solution. For industrial-grade fixed-wing UAVs, how to design the overall aerodynamic performance with the advantages of light weight overall structure and long cruising time has become an urgent problem to be solved in the current UAV industry.

At present, in order to improve the battery life of fixed-wing UAVs, on the one hand, a lighter weight aircraft is designed, and the aerodynamic shape of the UAV is continuously optimized to further reduce the flight resistance; Human-machine flight time. However, adopting the first design scheme will reduce the payload of the UAV and limit its development in various application scenarios; for the oil-electric power design scheme, it not only increases the weight of the UAV, but also brings It comes with the cost of investment, and at the same time, compared with pure electric aircraft, it also brings hidden dangers to flight safety. Therefore, how to design a fixed-wing aircraft that is both light and can achieve long-term cruise on the premise of ensuring the effective load is the key problem to be solved by the present invention.

SUMMARY OF THE INVENTION

For conventional fixed-wing UAVs, in order to improve the cruising time, compromises must be made in the shape layout and cost. In addition, because the fixed-wing UAV adopts the rolling take-off method, its expansion in many application scenarios is limited, such as aerial survey, border inspection, forest fire prevention and other fields. In order to ensure that the cost is acceptable, the cruising time of the fixed-wing unmanned aerial vehicle can be improved, and the cruising time of the fixed-wing unmanned aerial vehicle can be improved, and a variety of application scenarios can be adapted to realize the purpose of one machine with multiple uses. The invention proposes a vertical take-off and landing solar unmanned aerial vehicle. .

The specific technical solutions are as follows:

A vertical take-off and landing solar unmanned aerial vehicle, comprising: a fuselage, a frame, a wing group, a fixed wing and a rotor group; the wing group includes a front wing and a rear wing, and the front wing and the rear wing are connected by a connecting piece Fixed, the front wing includes a front main wing and a split aileron, the rear wing includes a rear main wing and an elevator, and the front wing is fixed on the fuselage; the rotor group includes more than or equal to 4 rotor propeller groups, The rotor propeller group is installed on the frame; the fuselage includes a nose, a nacelle and a rudder.

Preferably, the rear end of the rear wing is in abutment with the rudder, and the front end is in abutment with the front wing through a connecting piece.

Preferably, the surfaces of the front and rear wings are covered with solar panels.

Preferably, the fixed wing includes a fixed wing propeller group mounted on the nose.

Preferably, the cabin includes an aircraft control system and an energy supply device, and the energy supply device includes a fuel tank and a battery pack.

Preferably, the split aileron is located below the front main wing, and the deflection angle ranges from 0 to 45°, which is a unidirectional linear deflection.

Preferably, the front wing is fixed on the fuselage by a carbon rod, and the fixing method includes bolt connection.

Preferably, the materials of the fuselage, frame, front main wing and rear main wing include one or more of aviation layer wood, composite material, carbon fiber material and aluminum alloy material.

Preferably, the material of the split aileron includes one or more of balsa wood, composite material, carbon fiber material and aluminum alloy material.

Preferably, the fixing method of the rotor propeller group includes one or more of screw fixing, pin fixing and snap fixing.

Compared with the prior art, the vertical take-off and landing solar unmanned aerial vehicle of the present invention has the following advantages:

The vertical take-off and landing solar unmanned aerial vehicle proposed by the invention adopts a cracked aileron structure, and the surface of the wing has no gaps, which not only satisfies the excellent aerodynamic performance of the wing, but also provides a favorable guarantee for laying solar panels on the wing; Combined power supply with oil and electricity, compared with the traditional fixed-wing UAV, it can increase the cruising time; the control scheme of the rotor makes the UAV have the function of vertical take-off and landing. Based on the longer cruising time, it can be further extended Its application scenarios provide operational efficiency and cost savings.

Description of drawings

1 is a schematic diagram of a vertical take-off and landing solar-powered unmanned aerial vehicle proposed by the present invention;

FIG. 2 is a schematic diagram of a vertical take-off and landing solar unmanned aerial vehicle covering a solar panel proposed by the present invention;

FIG. 3 is a front view of a vertical take-off and landing solar unmanned aerial vehicle proposed by the present invention.

Description of reference numbers:

1 Fuselage 2 Frames 3 Fixed Wing Propeller Sets 4 Front Wings 5 Rear Wings

6 Rotor Propeller Sets 7 Nose 8 Cabins 9 Rudders 10 Elevators

11 Cracked ailerons 12 Carbon rods 13 Solar panels 14 Connectors

Detailed ways

The technical solutions of the present invention are further described in detail below in conjunction with specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.

In the description of the present invention, it should be understood that the terms "center", "portrait", "horizontal", "top", "bottom", "front", "rear", "left", "right", " The orientation or positional relationship indicated by vertical, horizontal, top, bottom, inner, outer, etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and The description is simplified rather than indicating or implying that the device or element referred to must have a particular square, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention.

In the description of the present invention, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense, unless otherwise expressly specified and limited, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; may be mechanical connection or electrical connection; may be direct connection or indirect connection through an intermediate medium, and may be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood through specific situations.

The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

1 is a schematic diagram of a vertical take-off and landing solar unmanned aerial vehicle proposed by the present invention, including: a fuselage 1, a frame 2, a wing group, a fixed wing and a rotor group; the wing group includes a front wing 4 and a rear wing Wing 5, the front and rear wings 4 and 5 are covered with solar panels 13. As shown in FIG. 2, the front and rear wings 4 and 5 are fixed by connecting pieces 14. connection method. As shown in FIG. 3 , in the vertical height, the rear wing 5 is higher than the front wing 4, and the connecting piece 14 is perpendicular to the plane where the rear wing 5 is located, and is also perpendicular to the plane where the front wing 4 is located. It has a whole structure and realizes the integration of the wing. The advantages of this are: on the one hand, the structural strength of the entire wing is enhanced; on the other hand, the design of the entire wing increases the area of the wing, thereby improving the efficiency of laying the solar panels 13 on the wing. The front wing 4 includes a front main wing and a split aileron 11. The split aileron 11 is located below the front main wing, and the deflection angle ranges from 0 to 45°, which is a unidirectional linear deflection. The deflection of the split aileron 11 It is driven by the driving device to realize its deflection. Since the split aileron 11 is located below the front main wing, when the deflection angle is 0°, it is integrated with the front main wing, so the thickness of the aileron 11 is not high. It is enough, preferably 2mm. At the same time, this structure will not affect the overall aerodynamic performance of the front main wing. The rear wing 5 includes a rear main wing and an elevator 10, and the front wing 4 is fixed on the fuselage 1 through a carbon rod 12, and the fixing method is bolt connection; the rotor group includes more than or equal to 4 rotor propeller groups 6, preferably 4 rotor propeller sets 6. The rotor propeller group 6 is installed on the frame 2, and the fixing method includes one or more of screw fixing, pin fixing and snap fixing; the fuselage 1 includes a nose 7, a nacelle 8 and a rudder 9, so the The fixed wing includes a fixed wing propeller group 3, which is installed on the nose 7; the nacelle 8 includes an aircraft control system and an energy supply device, the energy supply device includes a fuel tank and a battery pack, and the solar panel 13 is connected with the energy supply. The devices are connected to realize energy sharing, and the solar panel 13 can charge the battery pack to achieve the purpose of prolonging the battery life. The rear end of the rear wing 5 is in contact with the rudder 9, and the specific connection method includes bolt connection and the like. The rear wing 5 is connected to the rudder 9 by a carbon rod 12 .

The materials of the fuselage 1, the frame 2, the front main wing and the rear main wing include one or more of aviation layer wood, composite material, carbon fiber material and aluminum alloy material.

The material of the split aileron 11 includes one or more of balsa wood, composite material, carbon fiber material and aluminum alloy material.

The fixing method of the rotor propeller group 6 and the frame 2 includes one or more of screw fixing, pin fixing and snap fixing.

In the present invention, the rotor propeller group 6 and the fixed-wing propeller group 3 include propellers, motors, etc., and the motors are connected to the energy supply device. This part of the content is the common knowledge of those skilled in the art, so it will not be described in detail.

The solar cell panel 13 can be fixed on the front wing 4 and the rear wing 5 by means of bonding, glass fiber reinforced plastic packaging, welding or the like.

The present invention is based on a new type of fixed-wing unmanned aerial vehicle, which is based on a cracked aileron 11, uses solar energy as auxiliary power (the specific form is solar panel 13), and replaces the traditional The design of the landing gear roll is a low-cost and easy-to-implement solution in engineering applications.

The purpose of the present invention is to provide a new fixed-wing unmanned aerial vehicle shape layout form, so as to greatly improve the cruising time of the fixed-wing unmanned aerial vehicle, which is used to solve the existing fixed-wing unmanned aerial vehicle's short cruising time, slippery The disadvantages of running and take-off, the heavy weight of the oil-electric power structure, etc. At the same time, in order to increase the laying area of the solar cell panels 13 on the upper surface of the front wing 4, the present invention adopts the cracked aileron 11 to replace the traditional aileron design form, and realizes the basis of increasing the number of solar cell panels by 6%-8%. , without destroying the aerodynamic profile of the wing surface. In addition, the front wing 4 and the rear wing 5 are connected by the connecting member 14 by means of screws, snaps, magnets, etc., to form a closed overall structure, which obviously enhances the structural strength of the whole machine. The more prominent feature is that this design scheme, which uses solar energy as auxiliary power, greatly prolongs the battery life of the drone.

The working principle of the new configuration of the vertical take-off and landing solar unmanned aerial vehicle of the present invention includes: firstly, the flight control of the aircraft adopts the layout form of the split aileron 11 instead of the traditional aileron, which is used to control the flight of the aircraft in flight. Rolling motion; the elevator 10 is used to control the pitching motion of the aircraft, and the rudder 9 is used to control the heading motion of the aircraft. Second, the design scheme of the split aileron 11 is adopted, which ensures that the upper surface of the front wing 4 is smooth, and also facilitates the laying of solar panels to a greater extent. The hybrid solution based on the solar panel 13 and the energy supply device can realize that when the light intensity reaches 150,000 LUX, the power supply of the solar energy can meet the power consumption of the whole machine. When the light intensity is greater than this critical value, the excess electricity can be supplied by the energy device to charge the battery. Third, the vertical take-off and landing solar aircraft of the present invention is a five-rotor design, and the four-rotor propeller group 6 is fixed by the frame 2 and is used to provide operations such as vertical take-off and landing, hovering, etc. The fixed-wing propeller group 3 on the nose 7 It is used to provide power for the advancement of the whole machine. For low-altitude solar UAVs (less than 500m), this layout design can facilitate engineering applications on the basis of maximizing cost savings.

The structural layout of the new layout of the vertical take-off and landing solar unmanned aerial vehicle is now described in detail. In the vertical take-off and landing solar unmanned aerial vehicle type of the present invention, the front wing 4 is connected with the fuselage 1 through the carbon rod 12, and the position of the front wing 4 is fixed with bolts and screws; the rear wing 5 is connected with the fuselage 1 through the carbon rod 12, and bolts are also used. The screws fix the position of the rear wing 5. The fixing method of the front wing 4 and the rear wing 5 of the present invention is connected by bolts and screws to form an integral structure. On the one hand, the structural strength of the entire wing is enhanced; on the other hand, the design of the overall wing increases the area of the wing, thereby improving the efficiency of laying solar panels on the wing. However, the design scheme of the split aileron 11 is adopted, so that there is no assembly gap on the upper surface of the front wing 4 , which not only obtains an excellent aerodynamic shape, but also further increases the number of solar panels 13 laid on the front wing 4 . In addition, for this design scheme, the hybrid scheme of fixed-wing propeller group 3 and rotary-wing propeller group 6 can be used to realize the vertical take-off and landing of the UAV, which reduces the UAV's demand for flight sites and is more conducive to the development of the industry market. application. The most important thing is that the fuselage 1 is designed with a cabin cover for loading 18650 batteries, and at the same time, combined with solar energy for power supply, and through the optimization of the energy supply device, the UAV of the present invention can achieve longer cruise time.

The main reasons for innovating and inventing new configurations of vertical take-off and landing solar drones are: First, the current research and development and engineering applications of solar drones are mainly concentrated in the research of high altitude and long flight time. For low altitude application scenarios, it is limited by Considering cost and technology, the development of vertical take-off and landing solar energy is still immature. In order to further improve the flight time of fixed-wing UAVs, it will become a new research and development direction for UAVs; There is no gap on the surface of the wing, which not only satisfies the excellent aerodynamic performance of the wing, but also provides a favorable guarantee for the installation of solar panels on the wing; third, the use of solar and battery hybrid power supply, compared with traditional fixed-wing drones, can average The cruising time is increased by 40%-60%; fourthly, the control scheme of the rotor is adopted, so that the UAV has the function of vertical take-off and landing. Based on the longer cruising time, it can further expand its application scenarios and improve the operation efficiency. cut costs;

The fuselage 1, frame 2, front main wing and rear main wing are made of aviation layer wood, composite materials, carbon fiber materials, aluminum alloy materials, etc.;

The material of the split aileron 11 is balsa wood, composite material, carbon fiber material, aluminum alloy material, etc.;

The connection between the front main wing and the split aileron 11 can be connected by connecting rods, bearings, screws, etc.;

The fixing method of the rotor propeller group 6 can be fixed by screws, pins, bayonet, etc.;

The fixing method of the solar cell panel 13 may be through bonding, glass fiber reinforced plastic packaging, welding or the like.

To sum up, the vertical take-off and landing solar unmanned aerial vehicle proposed by the present invention adopts a cracked aileron structure, and there is no gap on the surface of the wing, which not only satisfies the excellent aerodynamic performance of the wing, but also provides solar panels for the wing. Favorable guarantee; the use of solar and oil-electric hybrid power supply can increase the cruising time compared to the traditional fixed-wing UAV; the use of the rotor control scheme enables the UAV to have the function of vertical take-off and landing, based on longer cruising time , it can further expand its application scenarios, provide operational efficiency and save costs.

The above embodiments are all preferred embodiments of the present invention, which do not limit the scope of the patent protection of the present invention. Any person skilled in the technical field to which the present invention belongs, without departing from the spirit and scope disclosed by the present invention, the equivalent structure and equivalent step transformation made by the content of the present invention all fall into the protection of the present invention. within the scope of the patent.

Claims (10)

1. a vertical take-off and landing solar-powered unmanned aerial vehicle, characterized in that, comprising: a fuselage (1), a frame (2), a wing group, a fixed wing and a rotor group; The wing group includes a front wing (4) and a rear wing (5), the front wing (4) and the rear wing (5) are fixed by connecting pieces, and the front wing (4) includes a front main wing and a split type. Ailerons (11), the rear wing (5) includes a rear main wing and an elevator (10), and the front wing (4) is fixed on the fuselage (1); The rotor group includes four or more rotor propeller groups (6), and the rotor propeller group (6) is installed on the frame (2); The fuselage (1) includes a nose (7), a nacelle (8) and a rudder (9). 2. A kind of vertical take-off and landing solar-powered unmanned aerial vehicle according to claim 1, wherein the rear end of the rear wing (5) is in contact with the rudder (9), and the front end is connected to the front end through a connector (14) The wings (4) abut. 3 . The vertical take-off and landing solar unmanned aerial vehicle according to claim 1 , wherein the surfaces of the front wings ( 4 ) and the rear wings ( 5 ) are covered with solar cell panels ( 13 ). 4 . 4. A vertical take-off and landing solar-powered unmanned aerial vehicle according to claim 1, wherein the fixed wing comprises a fixed-wing propeller group (3), which is installed on the nose (7). 5 . The vertical take-off and landing solar-powered UAV according to claim 1 , wherein the nacelle ( 8 ) includes an aircraft control system and an energy supply device, and the energy supply device includes a fuel tank and a battery pack. 6 . 6. A vertical take-off and landing solar-powered unmanned aerial vehicle according to claim 1, characterized in that the split aileron (11) is located below the front main wing, and the deflection angle ranges from 0 to 45°. Deflection towards linearity. 7. A VTOL solar unmanned aerial vehicle according to claim 1, wherein the front wing (4) is fixed on the fuselage (1) through a carbon rod (12), and the fixing method comprises bolt connection . 8. A VTOL solar unmanned aerial vehicle according to claim 1, wherein the material of the fuselage (1), the frame (2), the front main wing and the rear main wing comprises aviation layer wood , one or more of composite materials, carbon fiber materials and aluminum alloy materials. 9. A kind of VTOL solar unmanned aerial vehicle according to claim 1, is characterized in that, the material of described cracked aileron (11) comprises balsa wood, composite material, carbon fiber material and aluminum alloy material. one or more. 10. A vertical take-off and landing solar-powered unmanned aerial vehicle according to claim 1, wherein the fixing method of the rotor propeller group (6) comprises one or more of screw fixing, pin fixing and snap fixing kind.

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