Solar aircraft with multi-wing layout and control method thereof

Abstract

The invention discloses a multi-wing layout solar aircraft and a control method thereof. The multi-wing layout solar aircraft comprises an aircraft body, front wings, motors, paddles, front ailerons, middle wings, rear wings, rear ailerons, vertical empennages and an energy system. The front wings are mounted on two sides of the front part of the fuselage, the middle wings are mounted on two sides of the middle part of the fuselage, and the rear wings are mounted on two sides of the rear part of the fuselage; motors are mounted on the front wing, the middle wing and the rear wing, and are connected with and drive the paddles; the rear edge of the front wing is connected with the front aileron, and the rear edge of the rear wing is connected with the rear aileron; a power device composed of the motors and the paddles is used for controlling the working states of the motors on the front wing, the middle wing and the rear wing, and the yawing action of the aircraft is controlled by controlling the rotating speed difference of the motors on the two sides of the aircraft body. The aircraft is provided with three pairs of wings, the rigidity and the crosswind resistance of the aircraft wings and the longitudinal stability and the transverse lateral stability of the aircraft are improved, the cruise lift coefficient of the aircraft is increased through the design of the multi-wing layout, and the cruise efficiency of the aircraft is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a solar-powered aircraft with a multi-wing layout and a control method thereof. Background Art

[0002] A solar-powered aircraft is one that uses solar energy as its main energy source. Solar panels installed on the surface of the wings absorb solar radiation energy during the day and convert it into electrical energy. While meeting the power required for level flight, the remaining electrical energy is stored in batteries. The batteries are discharged at night to provide energy for the aircraft to fly level.

[0003] Compared with electric aircraft, solar aircraft have the advantages of no pollution, flexible use, low cost, etc. They have longer flight time and are suitable for high-altitude and long-duration flight missions such as monitoring, communication relay, and scientific exploration. In order to increase the flight time of solar aircraft, in addition to increasing the energy density of solar cells, it can also be achieved by increasing the laying area of ​​solar panels. Therefore, solar aircraft need a large aspect ratio, which means that the aircraft's wings are long, the wing stiffness is insufficient, and the aircraft has poor crosswind resistance. Therefore, it is necessary to optimize and improve the layout of solar aircraft to improve the crosswind resistance and the aircraft's cruising efficiency. Summary of the invention

[0004] In view of the above-mentioned deficiencies in the prior art, an object of the present invention is to provide a solar-powered aircraft with a multi-wing layout and a control method thereof, so as to solve the problem that the conventionally-configured solar-powered aircraft in the prior art have insufficient crosswind resistance.

[0005] To achieve the above object, the technical solution adopted by the present invention is as follows:

[0006] A solar powered aircraft with a multi-wing layout of the present invention comprises a fuselage, a front wing, a motor, blades, a front aileron, a middle wing, a rear wing, a rear aileron, a vertical tail and an energy system;

[0007] The front wings are installed on both sides of the front part of the fuselage, the middle wings are installed on both sides of the middle part of the fuselage, and the rear wings are installed on both sides of the rear part of the fuselage; the front wings, middle wings, and rear wings are all equipped with motors, which are connected to and drive the propeller blades; the trailing edge of the front wing is connected to the front aileron, and the trailing edge of the rear wing is connected to the rear aileron;

[0008] The motors and blades form a power device, which is divided into three groups and used to control the working states of the motors on the front wing, the middle wing and the rear wing respectively. The power devices are installed on both sides of the fuselage and are arranged symmetrically along the central axis of the fuselage. The front aileron and the rear aileron are driven by the servos of the front aileron and the rear aileron to deflect to control the pitch and roll movements of the aircraft, and the yaw movement of the aircraft is controlled by controlling the speed difference of the motors on both sides of the fuselage.

[0009] The energy system includes: solar panels, batteries and switches. The solar panels are evenly spread on the upper surfaces of the front wing, the middle wing and the rear wing, and the batteries are installed inside the fuselage. The switch is electrically connected to the solar panels, installed inside the fuselage, connected in parallel with the batteries, and connected to the motor through a circuit with a diode and an electric regulator.

[0010] Among them, when there is sufficient sunlight, the voltage of the solar panel is high and the power is supplied by the solar panel. When there is insufficient sunlight, the power is supplied by the battery, thereby realizing the conversion between solar power supply and battery power supply.

[0011] Furthermore, the solar cell panels adopt high-crystalline silicon solar cells with high photoelectric conversion efficiency, and the paving area of ​​the solar cell panels accounts for more than 90% of the wing area.

[0012] Furthermore, the front wing adopts a rectangular wing, the middle wing and the rear wing adopt a segmented wing, the section close to the fuselage adopts a rectangular wing, and the section far from the fuselage adopts a trapezoidal wing.

[0013] Furthermore, the solar panels are evenly laid on the upper surfaces of the front wing, the middle wing and the rear wing.

[0014] Furthermore, the motors are installed on the leading edges of the front wing, the middle wing and the rear wing.

[0015] Furthermore, the front wing and the middle wing are mid-wing, and the rear wing is a high-wing.

[0016] Furthermore, the blades on the leading edges of the front wing, the middle wing and the rear wing are all thrust propellers to improve the flight efficiency of the aircraft.

[0017] The present invention also provides a control method for a solar-powered aircraft with a multi-wing layout. Based on the above solar-powered aircraft, the steps are as follows:

[0018] Establish the aircraft body coordinate system, with the origin at the center of mass of the aircraft, the x-axis in the aircraft symmetry plane, parallel to the fuselage axis and pointing forward; the z-axis in the aircraft symmetry plane, pointing downward; the y-axis is perpendicular to the symmetry plane and pointing to the right;

[0019] Control the front aileron to deflect downward and the rear aileron to deflect upward, so that the aircraft generates a counterclockwise pitch moment around the y-axis, which lifts the nose of the aircraft; control the front aileron to deflect upward and the rear aileron to deflect downward, so that the aircraft generates a clockwise pitch moment around the y-axis, which presses the nose of the aircraft downward;

[0020] Control the front aileron and rear aileron on the left side of the fuselage to deflect downward, and the front aileron and rear aileron on the right side to deflect upward, so that the aircraft generates a counterclockwise rolling moment around the x-axis, causing the aircraft to roll to the right; the front aileron and rear aileron on the left side are deflected upward, and the front aileron and rear aileron on the right side are deflected downward, so that the aircraft generates a clockwise rolling moment around the x-axis, causing the aircraft to roll to the left;

[0021] Increasing the speed of the motor on the left side of the fuselage and reducing the speed of the motor on the right side of the fuselage will cause the aircraft to generate a counterclockwise yaw moment around the z-axis, causing the aircraft to yaw to the right; increasing the speed of the motor on the right side of the fuselage and reducing the speed of the motor on the left side of the fuselage will cause the aircraft to generate a clockwise yaw moment around the z-axis, causing the aircraft to yaw to the left.

[0022] Beneficial effects of the present invention:

[0023] The multi-wing layout solar aircraft proposed in the present invention has three pairs of wings with a large total wing surface area. Compared with conventional layout solar aircraft, more solar panels can be arranged, so that the aircraft has a longer flight time. The aspect ratio of a single wing is relatively small and the span is relatively small, which improves the rigidity and crosswind resistance of the aircraft wing, and also improves the longitudinal stability and lateral stability of the aircraft. The design of the multi-wing layout improves the cruising lift coefficient of the aircraft and improves the cruising efficiency of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic structural diagram of the solar powered aircraft of the present invention.

[0025] Figure 2 It is a schematic diagram of the structure of the solar panel installation in the present invention. DETAILED DESCRIPTION

[0026] In order to facilitate the understanding of those skilled in the art, the present invention is further described below in conjunction with embodiments and drawings. The contents mentioned in the implementation modes are not intended to limit the present invention.

[0027] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they should not be understood as limitations on the present invention.

[0028] Reference Figure 1 , Figure 2As shown, a solar powered aircraft with a multi-wing layout of the present invention comprises a fuselage 1, a front wing 2, a motor 3, a blade 4, a front aileron 5, a middle wing 6, a rear wing 7, a rear aileron 8, a vertical tail 9 and an energy system 10;

[0029] The front wing 2 is installed on both sides of the front part of the fuselage 1, the middle wing 6 is installed on both sides of the middle part of the fuselage 1, and the rear wing 7 is installed on both sides of the rear part of the fuselage 1; the front wing 2, the middle wing 6, and the rear wing 7 are all installed with a motor 3, and the motor 3 is connected to and drives the blade 4; the trailing edge of the front wing 2 is connected to the front aileron 5, and the trailing edge of the rear wing 7 is connected to the rear aileron 8;

[0030] The motors and blades form a power device, which is three in number and is used to control the working states of the motors 3 on the front wing 2, the middle wing 6, and the rear wing 7, respectively. The power devices are installed on both sides of the fuselage 1 and are arranged symmetrically along the central axis of the fuselage 1. The front aileron 5 and the rear aileron 8 are driven by the servos to deflect the front aileron and the rear aileron to control the pitch and roll movements of the aircraft, and the yaw movement of the aircraft is controlled by controlling the speed difference of the motors on both sides of the fuselage 1.

[0031] The energy system 10 includes: solar panels, batteries and switches. The solar panels are evenly laid on the upper surfaces of the front wing 2, the middle wing 6 and the rear wing 7, and the batteries are installed inside the fuselage. The switch is electrically connected to the solar panels, installed inside the fuselage, connected in parallel with the batteries, and connected to the motor through a circuit with a diode and an electric regulator.

[0032] Among them, when there is sufficient sunlight, the voltage of the solar panel is high and the power is supplied by the solar panel. When there is insufficient sunlight, the power is supplied by the battery, thereby realizing the conversion between solar power supply and battery power supply.

[0033] Specifically, the solar cell panels use high-crystalline silicon solar cells with high photoelectric conversion efficiency, and the paving area of ​​the solar cell panels accounts for more than 90% of the wing area.

[0034] Specifically, the front wing adopts a rectangular wing, the middle wing and the rear wing adopt segmented wings, the section close to the fuselage adopts a rectangular wing, and the section far from the fuselage adopts a trapezoidal wing.

[0035] Specifically, the solar cell panels are evenly paved on the upper surfaces of the front wing 2 , the middle wing 6 , and the rear wing 7 .

[0036] Specifically, the motor 3 is installed on the leading edges of the front wing 2 , the middle wing 6 , and the rear wing 7 .

[0037] Specifically, the front wing and the middle wing are mid-wing, and the rear wing is a high-wing.

[0038] Specifically, the blades on the leading edges of the front wing, the middle wing and the rear wing are all thrust propellers to improve the flight efficiency of the aircraft.

[0039] The present invention controls the pitch and roll motions of the aircraft by controlling the rudder deflection angles of the front aileron and the rear aileron, and controls the rotation speeds of the motors 3 at both ends of the fuselage 1 to make use of the motor rotation speed difference to enable the aircraft to achieve yaw motion; the vertical tail 9 located at the rear of the fuselage is used to improve the lateral stability of the aircraft.

[0040] The present invention can greatly improve the cruising lift coefficient of the aircraft through the front, middle and rear wings, thereby improving the range and flight time of the aircraft; the middle wing and the rear wing are composed of a rectangular wing part and a trapezoidal wing part, and the wing combined with the rectangular wing and the trapezoidal wing can reduce the resistance of the aircraft during flight, improve the lift-to-drag ratio of the aircraft, and at the same time reduce the weight of the wing and improve the flight efficiency; and through experimental verification, the wing of the above structure has sufficient strength and rigidity to withstand the effect of aerodynamic loads. In addition, the dihedral design is adopted between the rectangular wing and the trapezoidal wing, which can improve the stability of the aircraft.

[0041] In the present invention, a storage battery connected to each solar cell panel is arranged on the fuselage 1, and the storage battery is connected to each electrical component, so that the power supply is more stable and the battery life is longer.

[0042] In the example, the solar panel of the present invention is composed of several 125mm*125mm small panels 13, which can maximize the use of the wing area and improve the efficiency of the solar panel. Considering the small deformation of the wing caused by the load and the possible maneuvers of the aircraft, the present invention provides a gap 14 between each side of each small solar panel 13 and the adjacent small solar panel and wing rib 12, and the gap 14 ranges from 1-2mm to prevent damage to the solar panel due to factors such as wing deformation; the solar panel is tightly attached to the upper surface of the wing to reduce the influence of air resistance during flight.

[0043] The present invention also provides a control method for a solar-powered aircraft with a multi-wing layout. Based on the above solar-powered aircraft, the steps are as follows:

[0044] Establish the aircraft body coordinate system, with the origin at the center of mass of the aircraft, the x-axis in the aircraft symmetry plane, parallel to the fuselage axis and pointing forward; the z-axis in the aircraft symmetry plane, pointing downward; the y-axis is perpendicular to the symmetry plane and pointing to the right;

[0045] Control the front aileron to deflect downward and the rear aileron to deflect upward, so that the aircraft generates a counterclockwise pitch moment around the y-axis, which lifts the nose of the aircraft; control the front aileron to deflect upward and the rear aileron to deflect downward, so that the aircraft generates a clockwise pitch moment around the y-axis, which presses the nose of the aircraft downward;

[0046] Control the front aileron and rear aileron on the left side of the fuselage to deflect downward, and the front aileron and rear aileron on the right side to deflect upward, so that the aircraft generates a counterclockwise rolling moment around the x-axis, causing the aircraft to roll to the right; the front aileron and rear aileron on the left side are deflected upward, and the front aileron and rear aileron on the right side are deflected downward, so that the aircraft generates a clockwise rolling moment around the x-axis, causing the aircraft to roll to the left;

[0047] Increasing the speed of the motor on the left side of the fuselage and reducing the speed of the motor on the right side of the fuselage will cause the aircraft to generate a counterclockwise yaw moment around the z-axis, causing the aircraft to yaw to the right; increasing the speed of the motor on the right side of the fuselage and reducing the speed of the motor on the left side of the fuselage will cause the aircraft to generate a clockwise yaw moment around the z-axis, causing the aircraft to yaw to the left.

[0048] The present invention has many specific application paths. The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principle of the present invention. These improvements should also be regarded as the protection scope of the present invention.

Claims

1. A solar powered aircraft with a multi-wing layout, characterized in that: Including fuselage, front wing, motor, blades, front aileron, middle wing, rear wing, rear aileron, vertical tail and energy system; The front wings are installed on both sides of the front part of the fuselage, the middle wings are installed on both sides of the middle part of the fuselage, and the rear wings are installed on both sides of the rear part of the fuselage; the front wings, middle wings, and rear wings are all equipped with motors, which are connected to and drive the propeller blades; the trailing edge of the front wing is connected to the front aileron, and the trailing edge of the rear wing is connected to the rear aileron; The motors and blades form a power device, which is divided into three groups and used to control the working states of the motors on the front wing, the middle wing and the rear wing respectively. The power devices are installed on both sides of the fuselage and are arranged symmetrically along the central axis of the fuselage. The front aileron and the rear aileron are driven by the servos of the front aileron and the rear aileron to deflect to control the pitch and roll movements of the aircraft, and the yaw movement of the aircraft is controlled by controlling the speed difference of the motors on both sides of the fuselage. The energy system includes: solar panels, batteries and switches. The solar panels are evenly spread on the upper surfaces of the front wing, the middle wing and the rear wing, and the batteries are installed inside the fuselage. The switch is electrically connected to the solar panels, installed inside the fuselage, connected in parallel with the batteries, and connected to the motor through a circuit with a diode and an electric regulator.

2. The solar powered aircraft with multiple wings layout according to claim 1, characterized in that: The solar cell panels adopt high-crystalline silicon solar cells with high photoelectric conversion efficiency, and the paving area of ​​the solar cell panels accounts for more than 90% of the wing area.

3. The solar powered aircraft with multiple wings layout according to claim 1, characterized in that: The front wing adopts a rectangular wing, the middle wing and the rear wing adopt a segmented wing, the section close to the fuselage adopts a rectangular wing, and the section far from the fuselage adopts a trapezoidal wing.

4. The solar powered aircraft with multiple wings layout according to claim 1, characterized in that: The solar cell panels are evenly paved on the upper surfaces of the front wing, the middle wing and the rear wing.

5. The solar powered aircraft with multiple wings layout according to claim 1, characterized in that: The motors are installed on the leading edges of the front wing, the middle wing and the rear wing.

6. The solar powered aircraft with multiple wings layout according to claim 1, characterized in that: The front wing and the middle wing adopt the mid-monoplane wing, and the rear wing adopts the high-monoplane wing.

7. The solar powered aircraft with multiple wings layout according to claim 1, characterized in that: The blades on the leading edges of the front wing, the middle wing and the rear wing are all tension propellers.

8. A control method for a solar-powered aircraft with a multi-wing layout, based on the solar-powered aircraft according to any one of claims 1 to 7, characterized in that: The steps are as follows: Establish the aircraft body coordinate system, with the origin at the center of mass of the aircraft, the x-axis in the aircraft symmetry plane, parallel to the fuselage axis and pointing forward; the z-axis in the aircraft symmetry plane, pointing downward; the y-axis is perpendicular to the symmetry plane and pointing to the right; Control the front aileron to deflect downward and the rear aileron to deflect upward, so that the aircraft generates a counterclockwise pitch moment around the y-axis, which lifts the nose of the aircraft; control the front aileron to deflect upward and the rear aileron to deflect downward, so that the aircraft generates a clockwise pitch moment around the y-axis, which presses the nose of the aircraft downward; Control the front aileron and rear aileron on the left side of the fuselage to deflect downward, and the front aileron and rear aileron on the right side to deflect upward, so that the aircraft generates a counterclockwise rolling moment around the x-axis, causing the aircraft to roll to the right; the front aileron and rear aileron on the left side are deflected upward, and the front aileron and rear aileron on the right side are deflected downward, so that the aircraft generates a clockwise rolling moment around the x-axis, causing the aircraft to roll to the left; Increasing the speed of the motor on the left side of the fuselage and reducing the speed of the motor on the right side of the fuselage will cause the aircraft to generate a counterclockwise yaw moment around the z-axis, causing the aircraft to yaw to the right; increasing the speed of the motor on the right side of the fuselage and reducing the speed of the motor on the left side of the fuselage will cause the aircraft to generate a clockwise yaw moment around the z-axis, causing the aircraft to yaw to the left.

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