Solar unmanned aerial vehicle

Abstract

The utility model discloses a solar unmanned aerial vehicle, and particularly relates to the technical field of unmanned aerial vehicle equipment, the solar unmanned aerial vehicle comprises a fuselage, wings, an empennage and a power system, the fuselage is internally provided with a cabin for placing a control system and an effective load, and the upper surfaces of the wings are provided with solar cell panels electrically connected with the power system. The control system is connected with the solar cell panel and stores electric energy collected by the solar cell panel, the control system is in signal connection with the power system and controls the power system to provide power, and the two sides of a middle-section horizontal wing of the wings are fixedly connected with two outer-section wings with dihedral angles of the wings respectively. The middle-section horizontal wing is fixedly connected to the top of the fuselage, a plane formed by the symmetry axis of the fuselage and the symmetry axis of the middle-section horizontal wing is perpendicular to the middle-section horizontal wing, one end of the fuselage is fixedly connected with the empennage through a connecting piece, and the power system is installed on the wing. The unmanned aerial vehicle can carry loads, has long endurance time, and can enable the flight process to be more stable and safer.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle equipment, in particular to a solar unmanned aerial vehicle. Background Art

[0002] Most solar unmanned aerial vehicles have a narrow fuselage and a low weight, and can have a long endurance time in the air. However, with the increasing application fields of unmanned aerial vehicles, more and more solar unmanned aerial vehicles need to carry pods or other mission payload equipment to complete tasks. Some solar unmanned aerial vehicles usually suspend the payload outside the fuselage, and the connection is not firm, which is likely to cause damage to the connection cables during flight and affect normal use. Chinese Patent CN115158674A discloses a support-wing new energy unmanned aerial vehicle considering the layout of a hydrogen storage device. By integrating the advantages of high energy density of solar cells and hydrogen fuel cells and high specific power of lithium batteries, it can achieve long-endurance flight of an electric unmanned aerial vehicle carrying an effective payload. However, during the flight of the unmanned aerial vehicle, it is often subject to various unpredictable disturbances, such as atmospheric disturbances, engine thrust pulsation, and unconscious control stick movements by the pilot during manual control, etc. These disturbances will change the flight state of the aircraft.

[0003] Therefore, there is an urgent need for an unmanned aerial vehicle carrying a payload that can have a long endurance time in the air and can return to the original state before being disturbed without any emergency operations after being disturbed by the unmanned aerial vehicle, that is, it has the ability to automatically restore the original trim state to ensure the flight quality of the unmanned aerial vehicle. Summary of the Utility Model

[0004] The purpose of the utility model is to provide a solar unmanned aerial vehicle to solve the problems existing in the above-mentioned prior art, which can carry a payload, has a long endurance time in the air, and can make the flight process more stable and safe.

[0005] To achieve the above purpose, the utility model provides the following scheme:

[0006] The present utility model provides a solar-powered unmanned aerial vehicle, which includes a fuselage, wings, a tail wing, and a power system. A cabin is provided inside the fuselage, and a control system and a payload can be placed inside the cabin. A solar panel is disposed on the upper surface of the wing. The control system is connected to the solar panel and can store the electric energy collected by the solar panel. The control system is in signal connection with the power system and can control the power system to provide a power output. The wing includes a middle-section horizontal wing and two outer-section wings. The two sides of the middle-section horizontal wing are respectively fixedly connected to the two outer-section wings, and both of the two outer-section wings have anhedral angles. The middle-section horizontal wing is fixedly connected to the top of the fuselage, and the plane formed by the symmetry axis of the fuselage and the symmetry axis of the middle-section horizontal wing is perpendicular to the middle-section horizontal wing. One end of the fuselage is fixedly connected to the tail wing through a connecting member, and the power system is installed on the wing to provide power.

[0007] Preferably, the range of the anhedral angle is 4° - 6°.

[0008] Preferably, the power system includes a motor and a propeller assembly, and the propeller assembly is fixedly connected to the output shaft of the motor.

[0009] Preferably, the propeller assembly includes a hub and at least two blades. The blades are fixedly connected to one end of the hub, and the other end of the hub is fixedly connected to the output shaft of the motor.

[0010] Preferably, there are two sets of the power systems, and the two sets of power systems are respectively symmetrically fixed at the front ends of the left and right sides of the middle-section horizontal wing.

[0011] Preferably, the tail wing is a T-shaped tail wing. The T-shaped tail wing includes a horizontal stabilizer and a vertical stabilizer. The vertical stabilizer is perpendicularly and fixedly connected to the bottom surface of the horizontal stabilizer, and the vertical stabilizer is fixed on the symmetry axis of the horizontal stabilizer.

[0012] Preferably, the connecting member is a tail pipe. One end of the tail pipe is fixedly connected to the fuselage, and the other end of the tail pipe is fixedly connected to the end of the vertical stabilizer away from the horizontal stabilizer.

[0013] Preferably, equipment hatch covers are provided on both sides of the fuselage perpendicular to the middle-section horizontal wing.

[0014] The present utility model has achieved the following technical effects compared with the prior art:

[0015] The present utility model provides a solar unmanned aerial vehicle. A cabin capable of placing a control system and payload is arranged inside the fuselage, which facilitates the installation of various airborne devices, ensures the normal operation after carrying the payload of the installed devices, and increases the application range of the solar unmanned aerial vehicle. The control system can control the solar panels arranged on the upper surface of the wings to supply electric energy to the power system, ensuring that the solar unmanned aerial vehicle has a long endurance time in the air. The outer wings connected to both sides of the middle-section horizontal wings both have anhedral angles. When the solar unmanned aerial vehicle is disturbed during flight, the anhedral angles have a self-correcting function, which can make the unmanned aerial vehicle return to the original state before being disturbed within a short time, ensuring the stability of the unmanned aerial vehicle during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0017] Figure 1 It is a schematic structural diagram of the solar unmanned aerial vehicle of the present utility model.

[0018] In the figure: 1 - fuselage; 2 - wing; 21 - middle-section horizontal wing; 22 - outer wing; 3 - tail; 31 - horizontal tail; 32 - vertical tail; 4 - power system; 5 - tail pipe. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model with reference to the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, rather than all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the protection scope of the present utility model.

[0020] The purpose of the present utility model is to provide a solar unmanned aerial vehicle to solve the problems existing in the above-mentioned prior art, which can carry a payload, has a long endurance time in the air, and can make the flight process more stable and safe.

[0021] To make the above-mentioned objects, features, and advantages of the present utility model more obvious and understandable, the present utility model will be further described in detail below with reference to the drawings and specific embodiments.

[0022] The present utility model provides a solar unmanned aerial vehicle, such as Figure 1As shown in the figure, it includes a fuselage 1, wings 2, a tail 3 and a power system 4. A cabin is provided inside the fuselage 1, and a control system and payload can be placed inside the cabin. Solar panels are provided on the upper surface of the wings 2. The control system is connected to the solar panels and can store the electric energy collected by the solar panels. The control system is signal-connected to the power system and can control the power system to provide a power output. The wings 2 include a middle-section horizontal wing 21 and two outer-section wings 22. The two sides of the middle-section horizontal wing 21 are respectively fixedly connected to the two outer-section wings 22, and both of the two outer-section wings 22 have anhedral angles. The middle-section horizontal wing 21 is fixedly connected to the top of the fuselage 1. The plane formed by the symmetry axis of the fuselage 1 and the symmetry axis of the middle-section horizontal wing 21 is perpendicular to the middle-section horizontal wing 21. One end of the fuselage 1 is fixedly connected to the tail 3 through a connecting member. The power system 4 is installed on the wings 2 to provide power. A cabin capable of placing a control system and payload is provided inside the fuselage 1. The payload equipment and the control system are both located inside the cabin, with safer connection, higher protection for the payload equipment, and avoidance of problems such as nowhere to place airborne equipment, insecure external equipment, and vulnerable connection cables. Through 3D simulation and simulation of the fuselage 1, the pods and mission payloads inside the cabin, etc., it is convenient to carry various airborne equipment, and it can ensure the normal operation after carrying the equipment payload, increasing the application range of the solar UAV; the control system includes an MPPT controller, a flight controller and a storage battery. The solar panels are connected to the MPPT controller of the control system. The MPPT controller is electrically connected to the storage battery. The storage battery is electrically connected to the flight controller of the control system and provides electric energy for the flight controller. The storage battery is electrically connected to the power system and provides electric energy for the power system. The flight controller is signal-connected to the power system and can control the power system to provide flight power. The solar panels provide electric energy for the power system 4, ensuring that the solar UAV has a long endurance time in the air, a longer flight distance, and can perform long-term cruise missions; the outer-section wings 22 connected to both sides of the middle-section horizontal wing 21 both have anhedral angles. When the solar UAV is disturbed during flight, the anhedral angle has a self-correction function and can return the UAV to the original state before being disturbed within a short time, ensuring the stability of the UAV during flight.

[0023] In a further preferred embodiment of the present invention, the range of the anhedral angle is 4° - 6°. In this embodiment, a preferred anhedral angle of 5° can increase the flight stability of the UAV.

[0024] In a further preferred embodiment of the present utility model, the power system 4 includes a motor and a propeller assembly. The propeller assembly is fixedly connected to the output shaft of the motor. The motor and the propeller assembly can provide the power required for the UAV to fly. The propeller assembly includes a hub and at least two propeller blades. The propeller blades are fixedly connected to one end of the hub, and the other end of the hub is fixedly connected to the output shaft of the motor. Two sets of power systems 4 are provided, and the two sets of power systems 4 are respectively symmetrically fixed at the left and right front ends of the middle-section horizontal wing 21. After the fuselage 1 carries a load, the weight increases. With dual power output, it can avoid insufficient power after carrying equipment.

[0025] In a further preferred embodiment of the present utility model, the tail wing 3 is a T-shaped tail wing 3. The T-shaped tail wing 3 includes a horizontal stabilizer 31 and a vertical stabilizer 32. The vertical stabilizer 32 is vertically and fixedly connected to the bottom surface of the horizontal stabilizer 31. The vertical stabilizer 32 is fixed on the axis of symmetry of the horizontal stabilizer 31. The T-shaped tail wing 3 can avoid the wake interference of the wing 2, improve the control efficiency of the horizontal stabilizer 31, and can also reduce the area of the horizontal stabilizer 31, thereby reducing the structural weight and further increasing the flight endurance time.

[0026] In a further preferred embodiment of the present utility model, the connecting member is a tail pipe 5. One end of the tail pipe 5 is fixedly connected to the fuselage 1, and the other end of the tail pipe 5 is fixedly connected to the end of the vertical stabilizer 32 away from the horizontal stabilizer 31. Connecting the fuselage 1 and the tail wing 3 through the tail pipe 5 can reduce the overall weight of the solar UAV and increase the flight time.

[0027] In a further preferred embodiment of the present utility model, equipment hatch covers are provided on both sides of the fuselage 1 perpendicular to the middle-section horizontal wing 212. By opening the equipment hatch covers on both sides of the fuselage 1, the equipment load in the cabin can be replaced in a timely and convenient manner.

[0028] Specific examples are applied in the present utility model to elaborate on the principle and implementation manner of the present utility model. The description of the above embodiments is only used to help understand the method and its core idea of the present utility model; at the same time, for those of ordinary skill in the art, according to the idea of the present utility model, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present utility model.

Claims

1. A solar-powered drone, characterized in that: The invention comprises a fuselage, wings, a tail and a power system. A cabin is provided in the fuselage, a control system and a payload can be placed in the cabin, a solar panel is arranged on the upper surface of the wing, the control system is connected to the solar panel and can store the electric energy collected by the solar panel, the control system is connected to the power system signal and can control the power system to provide power output, the wing comprises a middle horizontal wing and two outer wings, the two sides of the middle horizontal wing are respectively fixedly connected to the two outer wings, and the two outer wings have an upward dihedral angle, and the angle range of the upward dihedral angle is 4°-6°, the middle horizontal wing is fixedly connected to the top of the fuselage, and the plane formed by the symmetry axis of the fuselage and the symmetry axis of the middle horizontal wing is perpendicular to the middle horizontal wing, one end of the fuselage is fixedly connected to the tail through a connector, and the power system is installed on the wing for providing power.

2. The solar-powered drone according to claim 1, characterized in that: The power system comprises a motor and a propeller assembly, and the propeller assembly is fixedly connected to the output shaft of the motor.

3. The solar-powered drone according to claim 2, characterized in that: The propeller assembly includes a hub and at least two blades, wherein the blade is fixedly connected to one end of the hub, and the other end of the hub is fixedly connected to the output shaft of the motor.

4. The solar-powered drone according to claim 3, characterized in that: The power system is provided with two groups, and the two groups of the power system are symmetrically fixed on the left and right front ends of the middle horizontal wing.

5. The solar-powered drone according to claim 1, characterized in that: The tail is a T-shaped tail, and the T-shaped tail includes a horizontal tail and a vertical tail. The vertical tail is vertically fixedly connected to the bottom surface of the horizontal tail, and the vertical tail is fixed on the symmetry axis of the horizontal tail.

6. The solar-powered drone according to claim 5, characterized in that: The connecting member is a tail pipe, one end of which is fixedly connected to the fuselage, and the other end of which is fixedly connected to an end of the vertical tail away from the horizontal tail.

7. The solar-powered drone according to claim 1, characterized in that: Equipment hatch covers are arranged on both sides of the fuselage perpendicular to the middle horizontal wing.

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