Method for controlling solar panels in a solar propelled aircraft

Abstract

A method of controlling solar panels in a solar propelled aircraft which has a wing having solar cell modules mounted therein. The solar propelled aircraft includes: first solar cell modules which are positioned in a main wing or a tail wing of the aircraft and receive solar energy directly from the sun; second solar cell modules which are positioned in a main wing or a tail wing of the aircraft and supplied with directed energy from the earth; and rotating shafts which rotate the first solar cell modules and the second solar cell modules so that the first solar cell modules and the second solar cell modules correspond to each other in both directions. The first solar cell module at the upper surface obtains solar energy from the sun, and the second solar cell module at the lower surface obtains directed energy transferred from the earth.

Claims

1. A method of controlling solar panels in a solar propelled aircraft comprising: a first panel and a second panel each having a first planar surface and a second planar surface, wherein the first planar surface of each panel is parallel and opposite to the second planar surface of each panel; a first solar cell module which is positioned in a main wing or a tail wing of the aircraft, disposed on the first planar surface of the first panel, and receives solar energy directly from the sun; a second solar cell module which is positioned in the main wing or the tail wing of the aircraft, disposed on the second planar surface of the second panel, and supplied with directed energy from a directed energy supply apparatus; and a rotating shaft which is located between and connected to the first and second panels, wherein the rotating shaft is rotated by a controller so that the first and second panels are rotated by the rotating shaft, wherein the second planar surface of the first panel is directly connected to the rotating shaft, wherein the first planar surface of the second panel is directly connected to the rotating shaft, and wherein the second planar surface of the first panel and the first planar surface of the second panel are parallel to and face each other, the method comprising: rotating the rotating shaft using the controller to position the first and second solar cell modules in accordance with a position of the sun or the directed energy supply apparatus.

2. The method of claim 1, wherein the solar propelled aircraft includes a GPS which confirms its own position, a sensor which confirms a position of the sun, and a communication component which locates a position of a base station which transfers the directed energy.

3. A method of controlling solar cell modules in a solar propelled aircraft comprising: a plurality of solar cell modules, each solar cell module comprising: a first substrate and a second substrate each having a first planar surface and a second planar surface, wherein the first planar surface of each substrate is parallel and opposite to the second planar surface of each substrate; a first solar cell panel which is positioned in a main wing or a tail wing of the aircraft, disposed on the first planar surface of the first substrate, and receives solar energy directly from the sun; a second solar cell panel which is positioned in the main wing or the tail wing of the aircraft, disposed on the second planar surface of the second substrate, and supplied with directed energy from a directed energy supply apparatus; and a rotating shaft which is located between and connected to the first and second substrates, wherein the rotating shaft is rotated by a controller so that the first and second substrates are rotated by the rotating shaft, wherein the second planar surface of the first substrate is directly connected to the rotating shaft, wherein the first planar surface of the second substrate is directly connected to the rotating shaft, and wherein the second planar surface of the first substrate and the first planar surface of the second substrate are parallel to and face each other, the method comprising: independently rotating each rotating shaft using the controller to position each solar cell module in accordance with a position of the sun or the directed energy supply apparatus.

4. The method of claim 3, wherein the solar propelled aircraft includes a GPS which confirms its own position, a sensor which confirms a position of the sun, and a communication component which locates a position of a base station which transfers the directed energy.

5. A method of controlling solar panels in an energy supply system for an aircraft, the energy supply system comprising: a solar propelled aircraft and a directed energy supply apparatus located on a ground lower than a flying altitude of the aircraft, wherein the solar propelled aircraft comprises: a first panel and a second panel each having a first planar surface and a second planar surface, wherein the first planar surface of each panel is parallel and opposite to the second planar surface of each panel; a first solar cell module which is positioned in a main wing or a tail wing of the aircraft, disposed on the first planar surface of the first panel, and receives solar energy directly from the sun; a second solar cell module which is positioned in the main wing or the tail wing of the aircraft, disposed on the second planar surface of the second panel, and supplied with directed energy from the directed energy supply apparatus; and a rotating shaft which is located between and connected to the first and second panels, wherein the rotating shaft is rotated by a controller so that the first and second panels are rotated by the rotating shaft, wherein the second planar surface of the first panel is directly connected to the rotating shaft, wherein the first planar surface of the second panel is directly connected to the rotating shaft, and wherein the second planar surface of the first panel and the first planar surface of the second panel are parallel to and face each other, the method comprising: rotating the rotating shaft using the controller to position the first and second solar cell modules in accordance with a position of the sun or the directed energy supply apparatus.

6. The method of claim 5, wherein the solar propelled aircraft includes a GPS which confirms its own position, a sensor which confirms a position of the sun, and a communication component which locates a position of a base station which transfers the directed energy.

Description

DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a configuration view of a solar propelled aircraft in which solar cell modules are mounted in aircraft wings or a tail portion.

(2) FIGS. 2A-2D are side views illustrating the aircraft wing in which the solar cell modules are mounted.

(3) FIGS. 3A-3D are side views illustrating the tail portion of the aircraft in which the solar cell modules are mounted.

(4) FIG. 4 is a configuration view of a solar cell module control method.

DESCRIPTION OF MAIN REFERENCE NUMERALS OF DRAWINGS

(5) 10: Main wing

(6) 11: First solar cell module

(7) 12: Second solar cell module

(8) 13: Rotating shaft

(9) 20: Tail wing

(10) 30: Body

(11) 31: Propeller

(12) 32: Directed energy

(13) 40: GPS, check position

(14) 50: Sensor, check position of sun

(15) 60: Communication

(16) 70: Controller

(17) 80: Control supply system

(18) 100: Aircraft

BEST MODE

(19) FIG. 1 is a configuration view of a solar propelled aircraft 100 in which solar cell modules are mounted in aircraft wings or a tail portion, FIGS. 2A-2D are side views illustrating an aircraft wing 10 in which the solar cell modules are mounted, and FIGS. 3A-3D are side views illustrating a tail portion 20 of the aircraft in which the solar cell modules are mounted. As illustrated in the drawings, the solar propelled aircraft 100 includes a body 30, a main wing 10, the tail wing 20, and a propeller 31. It is not necessary to store fuel in the solar propelled aircraft 100 because the solar propelled aircraft 100 does not have a turbine engine, and as a result, there is no reason why a fuel tank should be provided in an internal space in the wing. Therefore, solar cell modules are mounted in the internal space where the fuel tank would have been provided, thereby utilizing a space.

(20) The solar cell modules are attached to both surfaces, an upper surface and a lower surface of a panel, so as to correspond to both directions, and the panel having the upper surface and the lower surface on which the solar cell modules are attached is connected with a rotating shaft 13. A first solar cell module 11 attached to the upper surface obtains solar energy, and a second solar cell module 12 attached to the lower surface obtains directed energy 32 transferred from the earth. While the rotating shaft 13 is rotated by a controller along the path of the sun, the solar cell module is directed toward the sun and obtains energy, and the second solar cell module attached to the lower surface receives the directed energy 32 from a directed energy supply apparatus on earth. Directions of the first solar cell module 11 and the second solar cell module 12 disposed in the aircraft wing 10 or the tail wing 20 are controlled so that the first solar cell module 11 and the second solar cell module 12 are directed toward energy sources.

(21) As illustrated in FIGS. 2A and 2B, the first solar cell modules 11 in the main wing 10 obtain energy while rotating along the path of the sun. In FIGS. 2C and 2D, the second solar cell modules 13 in the main wing 10 obtain the directed energy 32 in a direction in which the directed energy supply apparatus transfers the directed energy 32.

(22) In FIGS. 3A and 3B, the first solar cell modules 11 in the tail wing 20 obtain energy while rotating along the path of the sun. In FIGS. 3C and 2D, the second solar cell modules 12 in the tail wing 20 obtain the directed energy 32 in a direction in which the directed energy supply apparatus transfers the directed energy 32.

(23) Hereinafter, an operating method will be described.

(24) A power supply system 80 is configured so that the directions of the first solar cell module 11 and the second solar cell module 12 disposed in the aircraft wing 10 or the tail wing 20 is controlled so that the first solar cell module 11 and the second solar cell module 12 are directed toward the energy sources. The aircraft 100 always checks its own position using a GPS 40, and confirms a position of the sun using a sensor 50. After confirming the position of the sun, the aircraft 100 allows the first solar cell modules 11 to be directed toward the sun and obtain energy.

(25) In addition, a position of a base station, which transfers directed energy, is confirmed, communication 60 is always carried out with the earth, and the second solar cell modules 12 are supplied with the directed energy 32 from the directed energy supply apparatus. A controller 70 mounted in the solar cell unmanned aircraft 100 calculates its own position relative to the energy sources, and latitude, calculates an angle at which the solar cell modules may obtain maximum energy, and rotates the solar cell modules in accordance with the position.

(26) Because the first solar cell modules 11 and the second solar cell modules 12 are present in the wing 10, the first solar cell modules 11 and the second solar cell modules 12 are less affected by the environment while flying such that durability thereof is greatly improved, and dust and the like are not attached to the first solar cell modules 11 and the second solar cell modules 12 such that the products may be used for a longer time in a clean state. The first solar cell modules 11 and the second solar cell modules 12 are rotated in the wings by the controller 70 instead of being installed on the surfaces of the aircraft, thereby obtaining a larger amount of energy. In addition, the surface of the wing 10 or the tail wing 20 is made of a material that is transparent or capable of allowing energy to penetrate, such that a larger amount of energy may be obtained, and the first solar cell modules 11 and the second solar cell modules 12 are moved by confirming the relative position such that energy may be efficiently obtained.

(27) Meanwhile, the present invention may include any one of the first solar cell module and the second solar cell module (including the rotating shaft, the controller and the like associated with each solar cell module).

(28) As the foregoing, the present invention has been described with reference to particular configurations such as specific constituent elements, the limited exemplary embodiments and the drawings, but the configurations, the exemplary embodiments, and the drawings are provided for better understanding of the present invention. In addition, the present invention is not limited to the exemplary embodiments, but the present invention may be variously corrected and modified from the exemplary embodiments by those skilled in the technical field to which the present invention pertains. Thus, it should be interpreted that the spirit of the present invention is not defined as being limited to the exemplary embodiments, the appended claims, all of the modified forms induced from the scope of the claims, and the equivalent concept thereto are included in the scope of the present invention.