DE102008007586A1 - Electrical energy generating method for airplane, involves subjecting solar modules to solar radiations treading through window pane and partially convert solar radiations into electrical energy - Google Patents

Abstract

The method involves arranging solar modules (2) having solar cells (9, 11, 13) between a window pane of an airplane window (3) and a displaceably designed jalousie (19) for shading of an airplane window through displacement of the jalousie. The solar modules are subjected to solar radiations treading through a window pane (5) and partially convert the solar radiations into an electrical energy. The solar radiations are deflected to a solar cell surface of the solar cells, such that an angle between perpendiculars to the solar cell surface and the solar radiations is reduced. An independent claim is also included for a solar module comprising solar cells for changing solar radiations into an electrical energy.

Description

The The invention relates to a method for generating electrical energy by means of a solar module in a vehicle, in particular aircraft. In the method, the solar module comprising at least one Solar cell, at least partially between one for solar radiation translucent window pane of an airplane window, and a sliding trained blind to darken the aircraft window, through Moving the blind arranged, in particular clamped, and so exposed by the aircraft window passing solar radiation, wherein the solar rays at least partially into electrical energy be converted.

During one Flight in an airplane, especially in a commercial aircraft while a long-haul flight, the problem often arises that a passenger during of the flight an electrical consumer, in particular an electrical Small appliance, want to operate and no electrical power connection is available. During the Flight is, for example, to operate a computer laptop as an electrical Consumers have an electrical energy available in an accumulator the computer laptop is stored. This can be the computer laptop dependent on from a capacity of the accumulator only a certain time to be operated until the stored energy is consumed.

The The object underlying the invention is therefore a method and to provide a device which operates independently of a mains supply of the electrical consumer during a flight in the aircraft. These Task is solved by the method of the type mentioned. advantageous variants of the method can be found in the dependent claims and in the following description. By the method can be advantageous during a Flight in an airplane, especially an airliner with a variety of seats, which translucent an aircraft window with a solar beam Window pane, in particular a wall facing a passenger interior Interior window pane, generated by means of the solar module electrical energy can be generated from the solar rays.

With the electrical energy can be advantageously supplied during the flight, an electrical consumer, such as a PDA (PDA = Personal Digital Assistant), a computer laptop, a mobile phone, a video player, an MP3 player, an I-pod ^® , a smart phone, a minicomputer, an electronic book, a navigation device, a computer toy, a reading light, a fan, a charger for a telephone, or a charger for charging accumulators, in particular type AAA or type AA batteries. Further advantageously, the shutter of the aircraft window can be a fastening means for arranging the solar module, which is already present in many aircraft windows for darkening the aircraft window.

In a preferred embodiment of the method are preferably obliquely with a directional component parallel to a plane of the windowpane, through the windowpane passing solar radiation by means of beam steering means and / or beam means such to a solar cell surface of Solar cell steered that an angle between a perpendicular to the Solar panel, and the oblique solar rays passing through the window pane upon impact reduced to the solar cell area becomes.

The Beam steering means can for example, by at least one prism, by Fresnel lenses or be formed by mirrors, in particular semipermeable mirrors. The beam means for example be formed by lenses, in particular Fresnel lenses. By the Beam steering means and / or beam means can advantageously obliquely on the Solar module incident rays of the sun's rays such on the solar cell surface be steered that the sky rays are substantially perpendicular hit the solar cell surface. This advantageously achieves that an energy conversion efficiency, which depending from a cosine of an angle of incidence of solar rays on the solar panel increases or decreases, is maximum.

In an advantageous embodiment of the method, the solar cell by means of an adhesive element in such a way friction connected to the window pane that when moving the blind the Solar module remains fixed in a position on the window pane and the blind for arranging, preferably terminals, of the solar module via the solar module slides. The adhesive element can, for example, by an elastomer be formed, which is connected to the solar module and so is arranged, that the adhesive element in arranging the solar module on the window pane with the window pane in operative contact and so on secure the solar module against displacement parallel to the solar cell surface frictionally can. The elastomer may be, for example, a silicone rubber.

The The invention also relates to a solar module comprising at least one Solar cell for converting solar radiation into electrical energy.

The solar module is preferably formed, at least partially between a translucent for solar radiation window of an aircraft window and a slidably designed blind for darkening of the aircraft window, in particular arranged by moving the blind, preferably to be clamped. A preferred thickness of the solar module is between 1.5 and 10 millimeters, more preferably between 1.5 and 3 millimeters, particularly preferably between 2.5 and 3 millimeters. As a result, the solar module can advantageously be arranged between the shutter and the window pane of the aircraft window.

The For this purpose, the solar module preferably has an adhesive element which is formed and arranged, the solar module with the window so frictionally to connect that when moving the blind the solar panel can stay fixed in a position on the window pane and the shutter for arranging, preferably for clamping, the solar module on the Solar module can slide.

The Adhesive element may advantageously be formed by an elastomer, which is arranged in the region of an edge of the solar module.

By the adhesive element can be advantageous in the position of the solar module stay fixed on the window pane and the blind can be beneficial for arranging, preferably clamping the solar module over the Slide solar module. The solar module can in this embodiment advantageously a smaller area dimension have as the aircraft window, in particular the window pane.

Prefers is the area the solar module according to the peripheral shape and size of the aircraft window, in particular, the window pane is formed. This allows the solar module particularly easy to be arranged on the window pane. The Airplane window, for example, an aircraft window of an Airbus A300, a Boeing 747 or the like. One to shine through intended area the aircraft window can with a rectangular peripheral shape with have round corners.

The Solar module can in another embodiment for fixing the window pane at least one suction cup, preferably a plurality of suction cups have, which is connected to the solar module. The solar module can in this embodiment a smaller area have as the windowpane. The solar module is in this embodiment advantageously formed on a window of a passenger train, or on a window, in particular a skylight, of an automobile to be attached.

The Solar module has in a preferred embodiment beam steering means and / or beam means which are formed by the obliquely through the window with a Directional component parallel to a plane of the window pane the window pane passing solar radiation in such a solar cell surface of the Solar cell directing that an angle of passing through the window pane Solar radiation relative to a plane perpendicular to the solar cell surface Axis can be reduced when hitting the solar cell surface.

The Beam steering means and / or beam means are further preferred formed, sky-scattered sky solar rays and / or cloud cover reflected solar rays to direct the solar cell surface.

By the beam steering means can advantageously an efficiency of solar energy conversion increase. The beam steering means can be formed for example by at least one prism. That at least a prism can, for example, in a cover plate, for example consisting of polycarbonate, be formed.

Prefers has a solar module, in particular the cover plate of the solar module, a variety of prisms on. The prisms preferably have one triangular Cross-section, wherein a formed by the triangular cross-section vertex the prisms are lengthwise in a plane of the solar module, in particular the cover plate extends. The prisms can each form a shape of a rib, wherein the ribs respectively - in particular similar to at furrows - parallel to each other. The prisms preferably extend longitudinally to 70% over a transverse dimension of the cover disk, more preferably 90%, especially preferred, in particular uninterrupted, over the entire transverse dimension the cover letter. This makes the solar module particularly efficient Sky solar rays and solar rays reflected from clouds convert when the longitudinal extent the prisms during a cruise is arranged parallel to the horizon.

In an advantageous embodiment are the prisms with a flat cover disk radiation incidence side covered. This can advantageously a contamination of the prisms be prevented.

The beam steering means may for example be formed by a plurality of mirrors, which are arranged in rows such that solar rays on the solar module with a predetermined angle - especially solar rays and / or cloud clouds reflected solar beams in an angular range between 87 degrees and 10 Degree - to a perpendicular to the solar cell surface arrive, substantially perpendicular or at least with a relative to a vertical of the Solar cell surface reduced angle can be directed to the solar cell surface.

The Mirrors can in each case, for example, be plane mirror, concave mirror or convex mirror.

The Mirror effect advantageous that solar rays, which from a Hemisphere area - formed through a sky - diagonally, namely with a direction component parallel to a plane of the solar cell surface, on the solar cell surface arrive at an improved angle to achieve a better Efficiency to direct the solar cell surface. This can continue advantageous solar radiation, caused by Raleigh scattering, in addition to Direct solar radiation can be directed to the solar cell surface.

The Beam means are formed for example by a plurality of Fresnel lenses, which are each formed, solar rays which in a predetermined Angle range to a vertical on the solar cell surface arrive, redirect so that the solar rays of the angular range in the essentially perpendicular or at least bundled arrive on the solar cell surface.

The pre-prisms can preferably have mirrors, the mirrors being semipermeable mirrors are formed. The semipermeable Mirrors can each with a smooth surface the prisms or by one - for example steamed - metal film be formed.

The Prisms are preferably formed in a cover plate of the solar module.

Additionally or independently to the prisms in the cover disk, the solar cell can be a structure of solar cell surface exhibit. The structure may be, for example, a pyramidal structure or structure with parallel grooves.

The Solar cell is preferably a semiconductor solar cell. The semiconductor solar cell For example, a crystalline solar cell, in particular a Silicon solar cell or a thin-film solar cell be. The semiconductor solar cell is, for example, a solar cell based on silicon, in particular multicrystalline or monocrystalline Silicon or amorphous silicon, or based on copper indium disulfide or copper indium diselenide, or based on gallium arsenide or a combination of these.

In a preferred embodiment For example, the solar cell has an antireflection layer which is formed is, with a directional component parallel to the solar cell surface the solar cell surface impinging solar radiation into a semiconductor material of the solar cell to steer.

In another embodiment is an optical refractive index of the antireflection layer chosen so that Reflection losses of solar radiation impinging on the solar cell surface reduced compared to a solar cell without antireflection coating are or disappear. The optical refractive index is preferred between 2.2 and 2.4, more preferably 2.3.

A Layer thickness of the antireflection layer is preferably between 60 and 110 nanometers or exactly 110 nanometers, more preferably less as 70 or exactly 70 nanometers, more preferably between 60 and 70 nanometers. As a result, the solar cell reaches a high efficiency at a solar spectrum at 10000 meters altitude. The layer thickness can through Process control can be set when manufacturing the solar cell, for example, by changing a gas discharge current and / or an exposure time during cathodic sputtering.

The Antireflection layer is preferably wavelength selective trained to solar radiation in the wavelength range between 400 and 700 nanometers stronger to transmit than in the wavelength range between 700 and 1100 nanometers.

The Antireflection layer may, for example, silicon nitride, silicon oxide, Zinc oxide, titanium dioxide or a combination of these. By the anti-reflection layer can advantageously an efficiency the solar energy conversion increased become.

In a preferred embodiment the solar module is formed with one facing the blind Side of the window to seal so that a convection flowing Air between the solar module and the window at least partially or can be completely prevented. The solar module may be preferred have a sealant which, for example, by the above-mentioned adhesive element, in particular a trained as an elastic edge of the solar module Elastomer is formed.

The Sealant causes a favorable thermal transition between the solar panel and the window pane, leaving the solar panel while Bonding with the window pane substantially one Can assume the temperature of the windowpane.

It was in fact recognized that solar cells during energy conversion of solar radiation in heat electrical energy and thereby achieve a poorer efficiency in converting the solar radiation into electrical energy. It has also been recognized that windowpanes in an aircraft during a flight have a colder temperature than a passenger compartment. In this embodiment, the solar module is advantageously particularly well thermally coupled with the window pane, which is colder than the passenger compartment.

In an advantageous embodiment the at least one solar cell of the solar module has a solar cell output to dispense electrical energy. The solar cell output is with a voltage converter with an output for supplying a electrical consumer electrically connected. The voltage converter is formed, an output at the solar cell output voltage to receive and output a constant voltage to operate of the electrical consumer.

By the voltage converter can advantageously the aforementioned electrical Consumers, especially the small electrical appliance, safe operate.

In a preferred embodiment For example, a solar module has at least one solar cell, more preferably a Mehrzehl of solar cells, wherein the solar module for the solar rays translucent cover plate and a back plate has. The at least one solar cell is in this embodiment between the cover plate and the back panel arranged.

In a preferred embodiment For example, the solar module has a plurality of solar cells, each of which independently are connected to each other with the voltage converter. The voltage converter preferably for each solar cell has a separate input and one with the input connected separate voltage converter. This can be advantageous in the case of shading a solar cell, the solar module with a high efficiency work. In a preferred embodiment does the solar module have an MPP tracker (MPP = maximum power point) on. The maximum power point tracker is formed, the at least a solar cell in an operating state maximum electrical delivered To operate power.

The solar module can advantageously work optimally by the beam-bundling means, the beam steering means, or the antireflection coating at an incident angle distribution of the solar beams through the aircraft window, in particular at an altitude of 10,000 meters. Preferably, a structure of the solar cell by material selection and doping of the semiconductor material is adapted to a spectrum of solar radiation at 10000 meters altitude. For this purpose, the doping may be selected such that a band gap of a pn junction of the solar cell is greater than in the case of solar cells provided for terrestrial application. More preferably, the doping of the acceptor concentration N _A in a p-base of a silicon solar cell is increased compared to solar cells for terrestrial applications.

Heaven solar rays and / or solar clouds reflected by cloud cover can do so optimally converted into electrical energy.

Advantageous can be an arrangement for generating electrical energy in a Plane an aircraft window and a solar module of the above Include type. Preferably, the aircraft window has a blind on. The arrangement can advantageously electrical energy for Operating small electrical appliances during a flight, in particular Long-haul flight are provided.

The Invention will now be described below with reference to figures and others embodiments described.

1 schematically shows an embodiment of an arrangement and a method for generating electrical energy from solar radiation in an aircraft.

1 schematically shows an embodiment of an arrangement 1 for network-independent generation of electrical energy in an aircraft. The order 1 has an airplane window 3 on. The airplane window 3 includes an exterior windowpane 7 and an interior windowpane 5 which are each spaced apart by a gap. The airplane window 3 is shown in this embodiment in sections in a sectional view as a double window, which may for example also be part of a triple window for an aircraft, in particular a commercial aircraft.

The order 1 also includes a solar module 2 , The solar module 2 has a plurality of solar cells, namely, in this embodiment, the solar cells 9 . 11 and 13 , The solar cells 9 . 11 and 13 are each by means of a binder 14 , in particular a translucent for solar radiation resin, between a back plate 15 and a cover disk 17 integrated of the solar module. The synthetic resin may be, for example, PVA (PVA = polyvinyl acetate), EVA (EVA = ethylene-vinyl acetate), TPU (TPU = thermoplastic polyurethane), or an ionomer.

The cover disk 17 of the solar module 2 has a variety of prisms, of which the prism 21 is designated by way of example. The prisms 21 are each formed in the cover plate and have a triangular cross-section. The prisms 21 each extend longitudinally in the form of ribs in a plane of the cover plate 17 , wherein the ribs in each case - in particular similar to field furrows - parallel to each other. The cover disk 17 may be formed, for example, of polycarbonate. The solar module 2 has in the region of an edge of the solar module a circumferentially formed seal 16 which is formed in this embodiment by an elastomer. The seal 16 is formed, the solar module 2 on the interior windowpane 5 hold frictionally.

The airplane window 3 also has a blind 19 on, which is intended to darken the aircraft window. The blind 19 of the aircraft window 3 is along a direction of displacement 20 back and forth and formed, for example in the form of a plate. The blind can do so in two grooves of a frame of the aircraft window 3 be guided.

The solar module 2 has a solar cell output 22 for discharging electrical energy. The solar cell output 22 is via a connection line 40 with a voltage converter 24 the arrangement 1 connected. The voltage converter 24 is formed, an input side via the connecting line 40 receive received voltage and the output side via a connecting line 42 issue. The voltage converter 24 is over the connection line 42 with an adapter 26 connected, which is designed for connecting mutually different electrical loads.

In this embodiment is a computer laptop 50 over a connecting line 44 and a plug 28 with the adapter 26 connected. Also conceivable are other small electrical appliances, which are connected to the adapter 26 can be connected.

The operation of the arrangement will now be explained below:
The solar module 2 is by moving the blind 19 along the direction of displacement 20 between the blinds 19 and the interior windowpane 5 of the aircraft window 3 arranged there clamped. The seal 16 , which both an adhesive element for holding the solar module 2 as well as a sealant for preventing convection, causes the solar module 2 in a position with the inner windowpane 5 remains frictionally connected. The solar module 2 also has sliding cams 18 on which with the back panel 15 are connected and when moving the blind 19 a slight gliding of the blind 19 for clamping the solar module 2 cause.

If an airplane with the airplane window 3 For example, flying at an altitude of 10000 meters, so can one from a sun 34 generated solar beam 30 - For example, by Raleigh scattering - be reflected on a variety of aerosol particles, of which the aerosol particles 35 is shown by way of example. From the aerosol particle 35 becomes a solar beam 32 to the airplane window 3 reflects and transmits through the outer windowpane 7 , the interior windowpane 5 and hits the cover disk 17 and there on a prism 21 the cover disk 17 , The solar beam 32 so can about the prism 21 with a smaller angle to a vertical 37 to a solar cell surface on the solar cell surface of the solar cell 9 be steered, as at an angle 38 between the solar rays 32 and the vertical 37 , From the sun 34 is also a solar beam 31 emits and hits a cloud 29 , From the cloud 29 becomes a solar beam 33 reflects and hits through the aircraft window 3 on the cover disk 17 and can from there via a prism of the cover disk 17 on the solar cell 13 be steered. From the sun 34 also becomes a direct solar beam 36 emitted by the aircraft window 3 on the cover disk 17 meets and there from a prism 21 on the solar cell 11 is steered. The solar cells 9 . 11 and 13 can from the respectively received solar rays 32 . 33 respectively 36 generate electrical energy and this at the solar cell output 22 provide.

The computer laptop 50 For example, may have a connection to the power supply, which via the adapter 26 can be supplied with electrical energy. The solar module 2 , especially the adapter 26 , For example, has a USB interface (USB = Universal Serial Bus), wherein the USB interface has at least one connection for powering an electrical load, in particular small electrical appliance. The connection for supplying power can have at least one ground connection and one voltage connection, in particular a plus connection or a minus connection.

The voltage converter 24 For example, it can generate an output voltage for supplying a USB interface, in particular 5 volts. For example, an output current may be up to 0.5 amperes according to a USB standard or greater than 0.5 amperes.

Also conceivable are other output voltages from the voltage converter 24 can be generated, for example, low voltages for operating small electrical appliances, for example in the range between 1.2 volts and 20 volts.

The solar module 2 For example, can also be flexible, so that the solar module 2 in the case of a curved inner windowpane 5 of the aircraft window 3 full-surface to the inner window pane 5 can be nestled.

The voltage converter 24 can be an M22 tracker 25 which is formed, an input resistance of the voltage converter 24 to change so that the solar cells 9 . 11 and 13 with varying irradiance through the solar beams, with varying solar cell temperature or with varying electrical load at the output of the voltage converter, or a combination of these can deliver a maximum electrical power.

1

arrangement

2

solar module

3

airplane window

5

Indoor window

7

Exterior window pane

9 11, 13

solar cell

14

binder

10

Back plate

16

Adhesive element sealant

17

cover disc

18

sliding cam

19

louvre

20

Move direction

21

prism

22

solar cell output

24

DC converter

25

MPP trackers

26

adapter

28

plug

30 31, 32, 33, 36

solar radiation

34

Sun

35

aerosol particles

37

vertical

38

angle

40 42, 44

connecting line

50

Computer Laptop

Claims (12)

Method for generating electrical energy by means of a solar module ( 2 ) in an aircraft in which the solar module ( 2 ) comprising at least one solar cell ( 9 . 11 . 13 ), at least partially between one for solar radiation ( 32 . 33 . 36 ) translucent window pane of an aircraft window ( 3 ) and a sliding blind ( 19 ) to darken the aircraft window by moving ( 20 ) of the blind ( 19 ) is arranged, in particular clamped, and so through the window pane ( 5 ) passing solar radiation ( 9 . 11 . 13 ) and the solar beams ( 9 . 11 . 13 ) are at least partially converted into electrical energy. A method according to claim 1, characterized in that the through the window pane ( 5 ) obliquely with a directional component parallel to a plane of the window pane through the window pane ( 5 ) passing solar radiation ( 9 . 11 . 13 ) by means of beam steering means ( 17 ) and / or beam-bundling means in such a way to a solar cell surface of the solar cell ( 9 . 11 . 13 ), that an angle between a perpendicular to the solar cell surface and the solar rays obliquely passing through the window ( 32 . 33 . 36 ) is reduced when hitting the solar cell surface. Method according to one of Claims 1 or 2, in which the solar module ( 2 ) by means of an adhesive element ( 16 ) frictionally engaged with the window pane ( 5 ), that when moving the blind ( 19 ) the solar module ( 2 ) remains fixed in a position on the window pane and the blind ( 19 ) for arranging the solar module ( 2 ) via the solar module ( 2 ) slides. Solar module ( 2 ) comprising at least one solar cell ( 9 . 11 . 13 ) for converting solar radiation ( 32 . 33 . 36 ) into electrical energy, characterized in that the solar module ( 2 ) is formed, at least partially between one for the solar radiation ( 32 . 33 . 36 ) translucent window pane ( 5 ) of an aircraft window ( 3 ), and a slidably formed Venetian blind ( 19 ) to darken the aircraft window ( 19 ), by moving the blind ( 19 ), whereby the solar module ( 2 ) an adhesive element ( 16 ), which is formed and arranged, the solar module ( 2 ) with the window pane ( 5 ) frictionally connect such that when moving the blind ( 19 ) the solar module in a position on the window pane ( 5 ) can remain fixed and the blind ( 19 ) to the terminals of the solar module ( 2 ) via the solar module ( 2 ) can slide. Solar module ( 2 ) according to claim 4, characterized in that the solar module ( 2 ) Beam steering means ( 17 ) and / or beam means, which are formed by the window pane ( 5 ) obliquely with a directional component parallel to a solar cell surface of the solar cell ( 9 . 11 . 13 ) through the window pane ( 5 ) passing solar radiation ( 32 . 33 . 36 ) to the solar cell surface of the solar cell ( 9 . 11 . 13 ) to direct an angle ( 38 ) through the window pane ( 5 ) passing solar radiation relative to a plane perpendicular to the solar cell surface axis ( 37 ) can be reduced when hitting the solar cell surface. Solar module ( 2 ) according to one of claims 4 or 5, characterized in that the solar module ( 2 ) has an antireflection layer which is formed with a directional component parallel to the solar cell surface on the solar cell ( 9 . 11 . 13 ) impinging solar beams ( 32 . 33 . 36 ) in a semiconductor material of the solar cell ( 9 . 11 . 13 ) to steer. Solar module ( 2 ) according to one of claims 4 to 6, characterized in that the solar module ( 2 ), with one to the blind ( 19 ) facing side of the window pane ( 5 ) such that a convection of flowing air between the solar module ( 2 ) and the window pane ( 5 ) is at least partially or completely prevented. Solar module ( 2 ) according to one of claims 4 to 7, characterized in that the at least one solar cell ( 9 . 11 . 13 ) a solar cell output ( 22 ) for discharging electrical energy, and having a with the solar cell output ( 22 ) electrically connected voltage transformers ( 24 ) having an output for supplying an electrical load ( 50 ), the voltage converter ( 24 ), one at the solar cell output ( 22 ) received electrical voltage and the output side, a constant voltage for operating the electrical load ( 50 ) to create. Solar module ( 2 ) according to one of claims 4 to 8, comprising one for the solar beams ( 32 . 33 . 36 ) at least partially translucent cover plate ( 17 ) and a back plate ( 15 ), wherein the at least one solar cell ( 9 . 11 . 13 ) between the cover disc ( 17 ) and the back plate ( 15 ) is arranged. Solar module ( 2 ) according to claim 8 and 9, characterized in that the solar module ( 2 ) a plurality of solar cells ( 9 . 11 . 13 ), which in each case independently with the voltage converter ( 24 ) are connected. Solar module ( 2 ) according to one of claims 9 or 10, characterized in that the solar module ( 2 ) a maximum power point tracker ( 25 ), which is formed, the at least one solar cell ( 9 . 11 . 13 ) to operate in an operating state of maximum output electric power. Arrangement ( 1 ) for generating electrical energy in an aircraft, the arrangement comprising an aircraft window with a shutter ( 19 ) and a solar module ( 2 ) according to one of the preceding claims 4 to 11.