Protection of space solar cells in a string arrangement

Abstract

Protection of space solar cells (WSZ) in a string arrangement (STRA), wherein - at least some of the space solar cells (SSCs) are arranged sequentially in the form of the strand extending in an X direction (STRA), - the string (STRA) comprises at least two space solar cells (WSZ), - two space solar cells (WSZ) that are immediately adjacent in the X direction are electrically connected in series by means of one or more metallic connectors (VB1), - the space solar cells (WSC) each have a receiving surface arranged in an X-direction and in a Y-direction, - the strand (STRA) has a front and a back, with the receiving surfaces of the space solar cells (WSZ) being formed on the front of the strand (STRA), - the strand (STRA) has a first end and a second end opposite the first end, with each of the two ends extending in the y-direction along one side of the space solar cell (WSZ) arranged at the ends of the strand, - each space solar cell (SSC) has a bypass diode (SD) connected to the respective space solar cell (SSC), - the space solar cells (WSC) each have a thickness in a Z-direction between 30 µm and 300 µm or a thickness between 50 µm and 160 µm, wherein - a protective arrangement (SA) is formed on the front side at at least one of the two ends along the y-direction and the protective arrangement is electrically connected to the space solar cell (WSZ) of the string (STRA) arranged at that end by means of one of the metallic connectors (VB1), wherein the protective arrangement (SA) comprises a first string protection diode (DGDS) and a metal strip and a second string protection diode (DGDS), - the metal strip (BUB) has a first end at the head and an intermediate piece and a second end at the head, - in a first alternative, the first string protection diode (DGDS) is connected in series in the y-direction by means of one of the metallic connectors (VB1) with the first head-side end of the metal strip (BUB), and the second string protection diode (DGDS) is connected in series in the y-direction by means of one of the metallic connectors (VB1) with the second head-side end of the metal strip (BUB), wherein the connectors each have two contact surfaces spaced apart from each other by a connecting piece, or - in a second alternative, the first string protection diode (DGDS) is arranged directly at the first head-side end on the metal strip (BUB) and the second string protection diode (DGDS) is arranged directly at the second head-side end on the metal strip (BUB), - in both alternatives, the two string protection diodes (DGDS) are each electrically connected in series in the X-direction to the space solar cell (WSZ) located at the end of the string (STRA) by means of one of the metallic connectors (VB1), - each string protection diode (DGDS) is unpackaged and has exactly one p / n junction and one metal contact on a top side and one metal contact on a bottom side, the metal contacts each covering at least 50% of the total area of ​​the top side and the bottom side, - each string protection diode (DGDS) has its own cover on the top side, the cover being bonded to the top side, - the protective arrangement (SA) is flat overall and has a thickness of less than 1 mm in a Z-direction, - the extent of the entire protective arrangement (SA) in the Y direction is at least a factor of five greater than the extent in the X direction.

Description

[0001] Solar cells for space applications are designed as so-called III-V multi-junction solar cells due to the high efficiency requirements. This means they have multiple p / n junctions connected in series. Currently, at least three stacked p / n junctions are monolithically integrated for this purpose. Generally, in III-V multi-junction solar cells, the bottom p / n junction is formed by a germanium substrate cell.

[0002] Unlike solar cells for terrestrial applications, which are almost exclusively single silicon solar cells housed in large, rectangular, rigid modules, space solar cells are subject to entirely different requirements. Key conditions for space solar cells include minimal weight, an efficiency above 30%, very high reliability and robustness across a wide temperature range, resistance to vibrations, and resistance to high doses of proton and electron radiation. Since heat dissipation—i.e., cooling of electrical components—is only possible through radiation in the vacuum of space, heat removal from electrical components is significantly more complex than in terrestrial applications.

[0003] As a result, the manufacturing and assembly technology for modules for space solar cells, i.e., the type of panels, developed completely separately and differently from the manufacturing and assembly technology of terrestrial solar cell modules.

[0004] Space solar cells, after being thinned to a thickness of less than 150 µm, are arranged sequentially in individual rows, also known as strings. The space solar cells are welded together along the string using special, very lightweight and flexible metal connectors, thus creating an electrical series connection. The rows are flexible along their length and are mounted on ultralight, carbon fiber-reinforced rigid panels or on thin, flexible carrier films.

[0005] A panel generally comprises several strands. On a panel, these strands are interconnected in series and / or parallel via flexible cables on the back of the panel. For this purpose, the panel has a wiring harness on its back. Furthermore, additional electrical components are located on the back of the panel.

[0006] In contrast to the aforementioned designs for space-based solar cells, terrestrial solar cells are rigidly arranged on a mechanically rigid, heavy, and stable substrate and are entirely covered with a rigid, particularly hail-resistant, glass plate. The glass plate for each panel is arranged on a surrounding frame, with each panel being sealed against environmental influences by means of the frame and an adhesive, particularly silicone.

[0007] The total weight of a terrestrial solar panel is many orders of magnitude greater than that of an ultralight space-based solar panel. Furthermore, defective panels in terrestrial applications are easily replaceable. Consequently, a terrestrial solar panel also requires very few protection diodes.

[0008] In contrast, in the panels for space, each individual space solar cell has its own bypass diode, so that if one space solar cell fails, not all space solar cells of the respective string fail, i.e., the entire string does not fail.

[0009] In most space-based solar cells, the associated bypass diode is located in one of the two cropped corners. Each bypass diode is directly connected to the respective space-based solar cell via a metallic connector. For reliability, the connectors are always welded.

[0010] To protect the space solar cells from space radiation, the front sides of each space solar cell and the bypass diode located in the corner are protected from short-wave UV light by means of a separate, very thin cover glass.

[0011] The ultrathin cover glasses are each less than 0.2 mm thick and are bonded to the front of the space solar cell using an adhesive. The bypass diodes located in the cropped corners are covered by the cover glass of the associated space solar cells. In other words, the bypass diodes do not have their own separate cover glass.

[0012] One disadvantage of the aforementioned arrangement is that if there is a fault in the pair consisting of a space solar cell and the associated bypass diode, individual parts of a pair can only be replaced with a very large effort.

[0013] If the space-based solar cells are already arranged on the string, replacing a defective part on the string is even more complex, meaning the entire string is defective and must be replaced with a different one. In other words, repair or rework is not economically viable.

[0014] An arrangement of space solar cells is known from DE 10 2004 044 061 A1. The space solar cells are arranged in the form of a string. As described above, each space solar cell has a bypass diode located in the corner of the space solar cell, the bypass diode being electrically connected antiparallel to the respective space solar cell and protected by the common cover glass.

[0015] In addition to the respective bypass diodes, each string of space solar cells contains one or more enclosed or encapsulated (i.e., surrounded by molding compound) string protection diodes. The function of the string protection diode is to suppress currents in a direction reversed compared to normal operation, thereby reducing current losses.

[0016] The string protection diodes are connected in a forward direction, i.e., in series with the space solar cells of a string. In other words, when illuminated by the sun, the space solar cells arranged in the string generate a current of a few amperes, typically 1.5 A, with the entire current then flowing through the forward-biased string protection diode.

[0017] In reverse polarity, voltages generally between 10V and 100V occur, particularly when, for example, one of several interconnected strings receives little or no sunlight, while one of the other strings is exposed to full sunlight. Current flow through the darkened strings is suppressed by the string protection diode, which is now wired in reverse polarity.

[0018] For reasons of reliability and flexibility, in current applications, one or more enclosed string protection diodes are arranged on the back of the panel for each string and connected to the string on the front of the panel via flexible electrical cables. Due to this arrangement, the enclosed string protection diodes on the back of the panel are protected from additional heat input from the sun, so heat dissipation does not become problematic even under higher current loads.

[0019] It should be noted that due to the lack of convection in space, passive cooling only occurs in the form of radiative heat, whereby at the maximum permissible temperatures of less than or equal to 170°C for the string protection diodes, which are usually designed as Si diodes, only a small amount of energy is radiated.

[0020] For redundancy reasons and / or to reduce heat generation, several string protection diodes are often connected in parallel.

[0021] From the US 2018 / 0062011 A1, in particular the Fig. 3a and Fig. 3b and Fig. 4a and Fig. 4b describes an integrated arrangement of string protection diodes located on the front face. For each string, one or more string protection diodes are integrated at the end of each string, similar to the integrated arrangement of the bypass diode, in a second corner of the space solar cell located at the end of the string. The second corner and the first corner are located on the same side of the space solar cell.

[0022] Here, either the back or front of the string protection diode is electrically connected in series to the back or front of the immediately adjacent space solar cell via another metallic connector. A second contact is formed on the top of the string protection diode. This second contact is connected via another connector to a rectangular, continuous metallic contact section at the end of the space solar cell string. Similar to the bypass diode, the string protection diode is also bonded to the cover glass of the immediately adjacent space solar cell.

[0023] As mentioned above, the string protection diodes are integrated with the respective space solar cell, corresponding to the bypass diode; that is, the string protection diode is arranged together with the space solar cell on a plastic carrier film or on the panel.

[0024] This makes the production of strings considerably more complex, since in particular the string protection diodes must be significantly larger and more powerful compared to the bypass diodes in order to cope with the current load of the entire string in the forward direction with the lowest possible electrical losses.

[0025] In other words, space in the corners of space-based solar cells is very limited. It has also been shown that a triangular design is not practical due to the additional effort required to saw the string protection diodes out of the silicon manufacturing substrate.

[0026] Furthermore, solar radiation is significantly more intense in space than on Earth. Cooling the string protection diodes under intense solar radiation, especially during operation when high currents flow through them, is often insufficient. If the temperature of the silicon string protection diodes rises close to 150°C, the electrical power dissipation increases further, potentially leading to failure.

[0027] Furthermore, the expert knows that the reject rate also increases during string manufacturing. Precisely because of the high level of integration, repair (i.e., rework) in the event of faults in the connection between the string protection diode and the space solar cell, or in the protection diodes themselves, is not feasible either economically or due to the high reliability requirements.

[0028] Due to the aforementioned disadvantages of an integrated arrangement on the front of the panel, the discrete arrangement of string protection diodes described above is used on the back of the panels using flexible cables in the manufacture of space solar panels.

[0029] One such embodiment is described in the Fig. Figure 4 shows a section of the back of a panel for space applications. The individual strands formed on the front of the panel are each connected to circuit boards (PLTs) on the back via a multitude of flexible cables (ELK). The numerous cables (ELKs) are grouped into cable harnesses (KBs). Individual, enclosed strand protection diodes (SSDs) are arranged on the larger circuit boards (PLTs).

[0030] It goes without saying that one of those in the Fig. The 4th typical setup shown requires a certain amount of effort and causes some additional weight.

[0031] Against this background, the object of the invention is to provide a device that further develops the state of the art.

[0032] The problem is solved by a strand arrangement of space solar cells with the features of claim 1. Advantageous embodiments of the invention are the subject of dependent claims.

[0033] The subject matter of the present invention is an arrangement for the protection of space solar cells, wherein at least a part of the space solar cells are arranged in a row in the form of a strand along an X-direction.

[0034] It is understood that longer strands formed in the X direction, especially due to the geometric requirements of panels, can also be arranged in several rows, particularly next to each other, and connected in series.

[0035] The string comprises at least two space solar cells arranged one after the other, wherein the space solar cells immediately adjacent along the X-direction are electrically interconnected in series by means of one or more metallic connectors.

[0036] The space solar cells each have a receiving surface formed in an X direction and in a Y direction.

[0037] Furthermore, the strand has a front and a back, with the receiving surfaces of the space solar cells being formed on the front of the strand.

[0038] Furthermore, the strand has a first end and a second end opposite the first end, with each of the two ends extending in the y-direction along one side of the space solar cell arranged at the ends of the strand.

[0039] Each space solar cell has a bypass diode connected to the respective space solar cell, wherein the space solar cells each have a thickness in a Z-direction between 30 µm and 300 µm or a thickness between 50 µm and 160 µm.

[0040] Furthermore, a protective arrangement is formed on the front side at at least one of the two ends along the y-direction, wherein the protective arrangement is electrically connected to the space solar cell of the string located at that end by means of one of the metallic connectors.

[0041] The protective arrangement comprises a first string protection diode and a metal strip, and a second string protection diode. The metal strip has a first end at the top, an intermediate section, and a second end at the top.

[0042] In a first alternative, the first string protection diode in the y-direction is connected in series with the first head-side end of the metal strip by means of one of the metallic connectors.

[0043] Furthermore, the second string protection diode is connected in series in the y-direction to the second head-side end of the metal strip by means of one of the metallic connectors.

[0044] The connectors each have two contact surfaces spaced apart from each other by a connecting piece.

[0045] Alternatively, in a second alternative, the first string protection diode is arranged directly at the first head-side end on the metal strip and the second string protection diode is arranged directly at the second head-side end on the metal strip.

[0046] In both alternatives, in a first embodiment, the two string diodes are each electrically connected in series in the X-direction to the space solar cell located at the end of the string by means of one of the metallic connectors.

[0047] In an unclaimed embodiment, in both alternatives in a second embodiment, the string protection diodes are each connected to a flexible connecting cable by means of one of the metallic connectors, wherein the metal strip is connected in the X-direction to the space solar cell arranged at one end of the string by means of the connectors in one or more ways.

[0048] It is understood that each string protection diode is unpackaged and has exactly one p / n junction and one metal contact on one top side and one metal contact on one bottom side.

[0049] In this case, the metal contacts each cover at least 50% of the total surface area of ​​the top and bottom surfaces.

[0050] Furthermore, each string protection diode has its own separate cover on the top side, with the cover being bonded to the top side of the string protection diode.

[0051] Furthermore, the protective arrangement is flat overall and has a thickness of less than 1 mm in a Z-direction.

[0052] In the Y-direction, the extent of the entire protective arrangement is at least five times greater than in the X-direction.

[0053] Surprisingly, it turned out that integrating the string protection diodes on the front side of the string using the present arrangement is of considerable advantage.

[0054] In particular, one advantage of the protective arrangement is that the wiring effort on the back of the string or panel is significantly reduced.

[0055] Furthermore, the advantageous arrangement of the two strand protection devices in conjunction with the metal strip allows the individual strand protection diode to be replaced in the event of a manufacturing defect without mechanically affecting the strand.

[0056] It was also shown that the advantageous integration of the string protection diodes in conjunction with the metal strip reduces manufacturing costs and increases reliability.

[0057] By connecting the string protection diodes directly to the metal strip or by means of a large-area connector, the string protection diodes do not get too hot even at maximum power and direct exposure to sunlight.

[0058] Besides good thermal coupling, the high reflectivity of the metal surface on the top of the string protection diode is also important. Preferably, the overall reflectivity of the arrangement in the visible and infrared ranges is above 80% or above 90%. It is advantageous if the cover layer is transparent to infrared radiation, allowing the string protection diodes to dissipate heat by means of infrared radiation.

[0059] In one embodiment, the top of the string protection diode has a continuous metallic layer or a metallic layer covering more than 80% of the surface in order to reflect solar radiation or to effectively dissipate the heat of the component.

[0060] In one embodiment, the distance formed in the X direction between the space solar cell arranged at the end of the string and the protective arrangement lies in a range between 0.01 mm and 2.0 mm, or in a range between 0.1 mm and 1 mm, or in a range between 0.2 mm and 0.5 mm.

[0061] Furthermore, the receiving area of ​​the space solar cell is between 4 cm². 2 and 500 cm 2 or between 30 cm 2 and 350 cm 2 or between 70 cm 2 and 160 cm 2 .

[0062] It should be noted that the term "metallic connector" refers to a connector consisting entirely of or comprised of a metal. In particular, a metallic connector also includes a multilayer structure, for example, consisting of one and one or more organic support layers, or several metal layers and at least one organic support layer, or several different metal layers and one or more organic support layers.

[0063] It is understood that the term "interconnected" refers to an electrical connection.

[0064] In a further training course, the electrical connection between the string protection diode and the first contact surface of the connector and / or the electrical connection between the second contact surface and the metal strip or the space solar cell is formed by a material bond.

[0065] In another training course, the contact resistance in the electrical connection is below 10 ohms, or below 5 ohms, or below 1 ohm.

[0066] Since a string contains a larger number of space solar cells, the electrical performance of the string protection diode must be matched to the electrical performance of the space solar cell string. In other words, the current-carrying capacity of the string protection diodes is at least 50% higher than the maximum current of the string under full sunlight and generally covers a few amperes.

[0067] Preferably, the current carrying capacity of the string protection diode is in a range between 100 mA and 10 A or between 1 A and 5 A.

[0068] Preferably, the string protection diodes are made of silicon or GaAs.

[0069] One advantage of GaAs over Si-silicon is that the voltage drop in the forward direction is lower.

[0070] In a training course, "Kovar" material is used as a connector and / or as a metal strip.

[0071] In one embodiment, the connector and / or the metal strip preferably comprises more than 50% iron, more preferably more than 20% cobalt, and more preferably more than 10% nickel.

[0072] In another embodiment, an "Invar" connector is used.

[0073] In a further development, the connector and / or the metal strip comprises or consists of pure silver and / or molybdenum, wherein the molybdenum is preferably coated with silver on one or both sides.

[0074] To ensure a reliable electrical and mechanical connection, the connectors preferably feature metal tabs. In particular, these metal tabs are designed for welding processes.

[0075] In a further training course, the connectors of the protective assembly are welded to one end of the strand multiple times, i.e., between two and six times. It is understood that the welds are spaced apart from each other in the Y-direction.

[0076] In another further development, the contact surfaces or contact tabs of the connectors at one end of the string are welded to the space solar cell and / or the bypass diode located at the end at exactly two contact points spaced apart from each other in the y-direction. Here, the distance between the two contact points in the y-direction is a multiple of the distance between the respective contact point and the edge of the space solar cell formed along the x-direction.

[0077] In other words, the two weld points for the connection to the strand protection diodes are located near the respective outer edge of the strand formed in the x-direction.

[0078] In one embodiment, each string protection diode comprises at least two string protection diodes connected in parallel. The two parallel-connected string protection diodes are preferably arranged parallel in the x-direction and spaced apart from each other in the y-direction. An advantage is that the parallel connection provides simple redundancy in the event of a failure of one of the string protection diodes.

[0079] In this further development, exactly four string protection diodes are arranged per string, i.e., connected to the string. Two of the string protection diodes are connected in series, forming two parallel branches, with the two nodes of the branches directly connected to each other, i.e., short-circuited.

[0080] One advantage, despite the slightly higher resistance of the series connection in the forward direction, is that due to the increased redundancy (i.e., more than double redundancy), even if more than one string protection diode fails, the respective string is still protected by one or more string protection diodes in the reverse direction.

[0081] In a further development, two string protection diodes are connected in parallel at each end. This results in a series circuit consisting of the string protection diode, the solar cells of the string or the bypass diodes, and the string protection diode.

[0082] One advantage is that the more than twofold redundancy further increases reliability compared to the embodiment with only two string protection diodes. Preferably, the string protection diodes have identical electrical specifications or, to a first approximation, nearly identical electrical specifications.

[0083] In another embodiment, instead of a single string protection diode, two string protection diodes are connected in series. In a further development, one or both of the series-connected string protection diodes are formed from a combination of series- and parallel-connected string protection diodes. An advantage is that a higher reverse voltage can be easily achieved with the series connection.

[0084] In one embodiment, the string protection diode is made of silicon or GaAs.

[0085] In another further development, the string protection diode has a reverse voltage range between 10 V and 1000 V, or between 30 V and 600 V, or between 80 V and 300 V, or between 10 V and 300 V.

[0086] In one embodiment, the string protection diode has a current range between 0.1 A and 5 A or between 0.5 A and 2 A.

[0087] In one embodiment, only III-V multi-space solar cells are arranged on the string as a space solar cell.

[0088] In another embodiment, at least two and at most twenty III-V multi-space solar cells are electrically connected in series on one string.

[0089] In a further training course, the serial connection of the space solar cells comprises or consists of five space solar cells, ten space solar cells, or twenty space solar cells.

[0090] In another advanced training, the serial connection comprises or consists of a total of no more than forty or no more than one hundred space solar cells connected in series.

[0091] In a further training course, the serially connected space solar cells are distributed across at least two or three strings. At most, the serially connected space solar cells are distributed across ten strings.

[0092] In one embodiment, a strand, hereinafter also referred to as the overall strand, is divided into several immediately adjacent segments, wherein the segments are connected in series and the first end is no longer opposite the second end in the X-direction. It is understood that the two segments are preferably arranged parallel to each other and spaced apart in the Y-direction. It should also be noted that the two segments of the overall strand may or may not be of the same length.

[0093] In this case, the receiving surfaces of the space solar cells are exclusively parallel to the X-direction and parallel to the Y-direction. In other words, the receiving surfaces preferably lie in an XY plane.

[0094] In a further development, the connectors have a first contact surface and a second contact surface, wherein one of the two contact surfaces is connected to the metal contact on the underside or to the metal contact on the top side of the string protection diode and the other of the two contact surfaces is connected to the metal strip.

[0095] In one advanced training, the two contact surfaces of the connectors are either identical or differently designed. In another advanced training, at least one or both contact surfaces of the connectors have one or more contact tabs.

[0096] In a further training course, the connecting piece between the two contact surfaces is designed in a meandering shape in at least some of the connectors in order to mechanically decouple the two contact surfaces from each other.

[0097] The term meandering here clarifies that in the connectors, the connecting piece has a greater extent perpendicular to a straight line connecting the two contact surfaces than in the direction of the straight line and optionally has several bulges and recesses perpendicular to the direction of the straight line.

[0098] In other words, in some designs of the connector, the connecting piece resembles the shape of a meander.

[0099] In a further development, the two contact surfaces of the connectors are each flat and have a thickness in the Z-direction of between 0.01 mm and 0.7 mm. Preferably, the thickness of the contact surfaces is constant over their entire length.

[0100] In a further development, the connectors have a rectangular surface, with the long side of the rectangular surface having an extent at least 5 times greater than the short side.

[0101] In another advanced development, all space solar cells in the string each have a bypass diode, with the bypass diode being directly connected to the respective space solar cell.

[0102] In a further training, one of the two string protection diodes is directly connected to the bypass diode of the space solar cell located at one of the two ends.

[0103] In one embodiment, a protective arrangement is formed at both ends of the strand. An advantage of this is that it increases redundancy.

[0104] In a further training course, when light falls on the front of the space solar cells, current flows exclusively through the string protection diodes and the metal strip to the connecting cable.

[0105] In a further training course, the contact flags have a thickness between 0.01 mm and 0.5 mm or between 0.02 mm and 0.2 mm.

[0106] In one embodiment, the cover of the string protection diode has a high transmission in the infrared range or is transparent in the infrared range in order to reflect the thermal radiation or not to suppress the emission of heat from the string protection diode.

[0107] In another embodiment, the protective arrangement is formed directly at one of the two ends, wherein the distance in the X direction between the protective arrangement and the space solar cell connected to the protective arrangement is in a range between 10 µm and 10 mm or in a range between 100 µm and 2 mm.

[0108] In a further training course, cooling for the string protection diodes is designed using the metal strips and / or the connecting cable.

[0109] The invention is explained in more detail below with reference to the drawings. Similar parts are labelled with identical designations. The illustrated embodiments are highly schematic; that is, the distances and the lateral and vertical extents are not to scale and, unless otherwise indicated, do not exhibit any derivable geometric relationships to one another. The drawings show that Fig. 1a, Fig. 1b different designs of a string of space solar cells with a protective arrangement formed at both ends, each connected to one of the space solar cells arranged at the respective end, Fig. 2a - 2e show detailed views, including of the front, side and back of the protective arrangement SA connected to a space solar cell WSZ, Fig. 3a - 3f various detailed views of the protection arrangement and the connectors with string protection diodes, Fig. 4 a top view of a discrete embodiment of string protection diodes on the back of a panel according to the prior art.

[0110] The illustrations of Fig. 1a and the Fig. Figure 1b shows different configurations of a string STRA of space solar cells WSZ with a protective arrangement SA formed at both ends, wherein the respective protective arrangement SA is connected to one of the space solar cells WSZ arranged at the respective end.

[0111] The protective arrangement SA is flat overall and has a thickness of less than 1 mm in a Z-direction.

[0112] The extent of the entire protective arrangement SA is at least five times greater in the Y direction than in the X direction.

[0113] One of the two ends of the protective arrangement WSZ is designed as a positive voltage pole + and the other end as a negative voltage pole -.

[0114] However, it is understood that in an embodiment not shown, only one protective arrangement SA is formed either at the end with the positive voltage pole + or at the end with the negative voltage pole -.

[0115] The space solar cells (WSZ) are arranged sequentially in the form of the string STRA extending in an X direction, with the string STRA comprising a total of five space solar cells (WSZ). Each of the five space solar cells (WSZ) is protected on its top side by its own cover glass (DGS).

[0116] Two space solar cells WSZ that are immediately adjacent in the X direction are electrically connected in series with each other by means of exactly two metallic connectors VB1.

[0117] The space solar cells (WSZ) each have a receiving surface arranged in an X direction and in a Y direction.

[0118] The strand STRA has a front and a back, with the front being shown in the top view.

[0119] In this case, the receiving surfaces of the space solar cells WSZ are formed on the front of the string STRA.

[0120] The STRA strand has a first end and a second end opposite the first end, with each of the two ends extending in the y-direction along one side of the space solar cell WSZ arranged at the ends of the strand.

[0121] In this case, each of the space solar cells WSZ has a bypass diode SD connected to the respective space solar cell WSZ. The bypass diodes SD are each located in a corner of the assigned space solar cell WSZ and are connected by two connectors VB1 and VB2 to the space solar cell WSZ immediately adjacent in the X-direction and the space solar cell immediately adjacent in the Y-direction, respectively.

[0122] It is understood that the bypass diode SD and the space solar cell WSZ assigned in the X direction are covered by a single cover glass DGS.

[0123] The space solar cells (WSZ) each have a thickness in a Z-direction between 30 µm and 300 µm or a thickness between 50 µm and 160 µm.

[0124] The protective arrangements SA located on the front of the STRA strand are each formed along the y-direction.

[0125] The protective arrangements SA are electrically connected to the space solar cells WSZ of the string STRA, which are arranged at both ends, by means of several metallic connectors.

[0126] The protective arrangement SA comprises a first string protection diode DGDS and a metal strip BUB, and a second string protection diode DGDS. Furthermore, it is preferred to form contact tabs with contact surfaces K1 on the metal strip, wherein the contact tabs and the metal strip are generally formed in one piece.

[0127] The metal strip BUB has a first end at the head and an intermediate piece and a second end at the head.

[0128] In the embodiment shown in the Fig. 1a, also referred to as the first alternative, is the first string protection diode DGDS in the y-direction connected in series with the first head-side end of the metal strip BUB by means of one of the metallic connectors VB1.

[0129] Furthermore, the second string protection diode DGDS is also connected in series in the y-direction by means of one of the metallic connectors VB1 with the second head-side end of the metal strip BUB.

[0130] The VB1 connectors each have two contact surfaces separated from each other by a connecting piece - not shown.

[0131] In the SA protection arrangement, connected to the end where the positive potential + is applied, the two string protection diodes DSGS are each connected to the space solar cell WSZ via one of the connectors VB1 formed in the X direction. In other words, the two branches of the string protection diodes DGDS are parallel to each other, thus forming redundancy.

[0132] The metal strip BUB has two contact tabs K1 for connecting one flexible cable each (not shown).

[0133] It should be noted that in each of the two branches, the flexible cable (not shown) is connected in series via the contact tabs K1 to the metal strip BUB, the string protection diode DGDS and the space solar cell WSZ.

[0134] In the protective arrangement SA, connected to the end where the negative potential is applied, the two string protection diodes DSGS are each connected in the negative X-direction via one of the connectors VB1 to a flexible cable (not shown) via one of the respective contact lugs K1.

[0135] Furthermore, one of the string protection diodes DGDS is connected to the bypass diode of the space solar cell WSZ via one of the connectors VB1. The metal strip BUB is connected to the space solar cell WSZ, which is located at the end of the string, via two connectors VB1.

[0136] Furthermore, the first string protection diode DGDS and the second string protection diode DGDS are also connected in series in the y-direction by means of one of the metallic connectors VB1 with the second head-side end of the metal strip BUB.

[0137] Here too, the two branches of the string protection diodes DGDS are connected in parallel to each other, thus forming a redundancy.

[0138] It should be noted that in each of the two branches, the space solar cell WSZ is connected in series via the metal strip BUB to the string protection diode DGDS and the flexible connecting cables.

[0139] In the embodiment shown in the Fig. 1b, also referred to as the second alternative, only the differences to the embodiment are listed, in conjunction with the drawing documents of the Fig. 1a, explained.

[0140] The first string protection diode DGDS is arranged directly on the metal strip BUB at the first end facing the head, where the positive potential + is applied, without a connector VB1. This allows for a different approach compared to the embodiment shown in the Fig. 1a, save two VB1 connectors.

[0141] Furthermore, the second string protection diode DGDS is arranged directly on the metal strip BUB at the second head-side end.

[0142] In the two in the Fig. 1a or the Fig. In the alternatives shown in 1b, the two string protection diodes DGDS are each electrically connected in series in the X-direction by means of one of the metallic connectors VB1 with the space solar cell WSZ located at the end of the string STRA.

[0143] It should be noted that in this case, each of the DGDS string protection diodes has its own cover in the form of a glass cover. It is understood that the cover is bonded to each individual DGDS string protection diode.

[0144] In the illustrations of Fig. Figures 2a - 2e show detailed views, including of the front, side and back of the protective arrangement SA connected to a space solar cell WSZ.

[0145] In detail, this shows the Fig. 2b a side view that Fig. 2c a top view of the back and the Fig. 2 c a perspective view of the arrangement of Fig. 2a.

[0146] The Fig. Figure 2e shows a detailed side view of a string protection diode DGDS in a section.

[0147] The following section explains only the differences from the previous embodiments.

[0148] The Fig. Figure 2a shows a top view of the front of one of the space solar cells WSZ, covered with a cover glass DGS. At one of the two ends, which form an edge of the space solar cell WSZ in the Y direction, the contact tabs K1 of a total of three connectors VB1 are visible for serial connection with an adjacent space solar cell WSZ (not shown).

[0149] The VB1 connectors have a first contact surface and a second contact surface. One of the two contact surfaces of each of the three VB1 connectors is welded to the top surface of the WSZ space solar cell. The other contact surface is intended for connection to another WSZ space solar cell. In this case, both contact surfaces are identical.

[0150] Both contact surfaces have several contact tabs K1. The respective connecting pieces between the two contact surfaces of the connectors VB1 are designed in a meandering shape to mechanically decouple the two contact surfaces from each other.

[0151] On the opposite long edge of the space solar cell WSZ, the protective arrangement SA is formed with the two string protection diodes DGDS, protected by a cover glass layer, and the metal strip BUB. It is understood that the cover glass is transparent in the infrared.

[0152] The metal strip BUB has a total of three contact tabs K1 for connecting the flexible cables.

[0153] In the side view of the Fig. Figure 2b shows the small thickness of the strand STRA, which is less than one millimeter. Furthermore, a step is formed between the metal strip BUB and the contact tabs K1.

[0154] From the rear view of the Fig. From 2c, it follows that the bypass diode SD is connected to the underside of the space solar cell WSZ via a wide connector VB2. Furthermore, the protective arrangement SA is connected to the opposite edge via the contact surfaces of the connectors VB1.

[0155] From the presentation of Fig. 2e shows that one of the two contact surfaces of connector VB1 is connected to the top surface of the string protection diode DGDS and is covered by the cover glass. Furthermore, connector VB1 has a step between the two contact surfaces.

[0156] In the illustrations of Fig. Figures 3a-3f show detailed views of the SA protection arrangement, the VB1 connectors, and the structure of the DGDS string protection diodes. The following explains only the differences compared to the preceding figures.

[0157] It is evident that the contact surfaces of the VB1 connectors each have exactly three contact tabs. The side view also shows that... Fig. 3b that the protective arrangement is very thin in the Z direction and preferably has a thickness of less than 1 mm.

[0158] In the enlarged section of the Fig. 3d shows that on one side of the string protection diode DGDS a cover glass DG is arranged by means of an adhesive KL on one side of the protection diode DS.

Claims

[1] Protection of space solar cells (SSCs) in a string arrangement (STRA), wherein - at least some of the space solar cells (SSCs) are arranged sequentially in the form of the strand extending in an X direction (STRA), - the string (STRA) comprises at least two space solar cells (WSZ), - two space solar cells (WSZ) that are immediately adjacent in the X direction are electrically connected in series by means of one or more metallic connectors (VB1), - the space solar cells (WSC) each have a receiving surface arranged in an X-direction and in a Y-direction, - the strand (STRA) has a front and a back, with the receiving surfaces of the space solar cells (WSZ) being formed on the front of the strand (STRA), - the strand (STRA) has a first end and a second end opposite the first end, with each of the two ends extending in the y-direction along one side of the space solar cell (WSZ) arranged at the ends of the strand, - each space solar cell (SSC) has a bypass diode (SD) connected to the respective space solar cell (SSC), - the space solar cells (WSC) each have a thickness in a Z-direction between 30 µm and 300 µm or a thickness between 50 µm and 160 µm, wherein - a protective arrangement (SA) is formed on the front side at at least one of the two ends along the y-direction and the protective arrangement is electrically connected to the space solar cell (WSZ) of the string (STRA) arranged at that end by means of one of the metallic connectors (VB1), wherein the protective arrangement (SA) comprises a first string protection diode (DGDS) and a metal strip and a second string protection diode (DGDS), - the metal strip (BUB) has a first end at the head and an intermediate piece and a second end at the head, - in a first alternative, the first string protection diode (DGDS) is connected in series in the y-direction by means of one of the metallic connectors (VB1) with the first head-side end of the metal strip (BUB), and the second string protection diode (DGDS) is connected in series in the y-direction by means of one of the metallic connectors (VB1) with the second head-side end of the metal strip (BUB), wherein the connectors each have two contact surfaces spaced apart from each other by a connecting piece, or - in a second alternative, the first string protection diode (DGDS) is arranged directly at the first head-side end on the metal strip (BUB) and the second string protection diode (DGDS) is arranged directly at the second head-side end on the metal strip (BUB), - in both alternatives, the two string protection diodes (DGDS) are each electrically connected in series in the X-direction to the space solar cell (WSZ) located at the end of the string (STRA) by means of one of the metallic connectors (VB1), - each string protection diode (DGDS) is unpackaged and has exactly one p / n junction and one metal contact on a top side and one metal contact on a bottom side, the metal contacts each covering at least 50% of the total area of ​​the top side and the bottom side, - each string protection diode (DGDS) has its own cover on the top side, the cover being bonded to the top side, - the protective arrangement (SA) is flat overall and has a thickness of less than 1 mm in a Z-direction, - the extent of the entire protective arrangement (SA) in the Y direction is at least a factor of five greater than the extent in the X direction. [2] Arrangement of space solar cells (WSC) according to claim 1, wherein the connectors have a first contact surface and a second contact surface, wherein one of the two contact surfaces is connected to the metal contact on the underside or to the metal contact on the top side of the string protection diode (DGSD) and the other of the two contact surfaces is connected to the metal strip (BUB). [3] Arrangement of space solar cells (WSZ) according to claim 1 or claim 2, wherein the two contact surfaces of the connectors (VB1, VB2) are the same or different. [4] Arrangement of space solar cells (WSZ) according to one of the preceding claims, wherein in the connectors (VB1) at least one of the two contact surfaces or both contact surfaces each have a contact flag (K1) or several contact flags (K1). [5] Arrangement of space solar cells (WSZ) according to one of the preceding claims, wherein in the connectors (VB1) the connecting piece between the two contact surfaces is designed in a meandering shape to mechanically decouple the two contact surfaces from each other. [6] Arrangement of space solar cells (WSZ) according to one of the preceding claims, wherein the two contact surfaces of the connectors (VB1) are each flat and each have a thickness in the Z direction between 0.01 mm and 0.7 mm. [7] Arrangement of space solar cells (WSZ) according to any of the preceding claims, wherein the connectors (VB1) have a rectangular surface and the long side of the rectangular surface has an extent at least 5 times greater than the short side. [8] Arrangement of space solar cells (SSCs) according to one of the preceding claims, wherein the bypass diode (SD) is directly connected to the respective space solar cell (SSC) by means of a wide connector (VB2). [9] Arrangement of space solar cells (WSZ) according to one of the preceding claims, wherein one of the two string protection diodes (DGDS) is directly connected to the bypass diode (SD). [10] Arrangement of space solar cells (WSZ) according to one of the preceding claims, wherein a protective arrangement (SA) is formed at both ends of the string. [11] Arrangement of space solar cells (SSCs) according to one of the preceding claims, wherein when light is incident on the front of the space solar cells (SSCs) the current flows exclusively through the string protection diodes (DGDS) and the metal strip (BUB) to a connecting line. [12] Arrangement of space solar cells (SSCs) according to any of the preceding claims, wherein the contact tabs have a thickness between 0.01 mm and 0.5 mm or between 0.02 mm and 0.2 mm. [13] Arrangement of space solar cells (WSC) according to any of the preceding claims, wherein the cover of the string protection diode (DGDS) is transparent in the infrared to reflect solar radiation and / or the cover is designed as a cover glass and the top of the string protection diode (DGDS) has a continuous metallic layer or a metallic layer covering more than 80% of the surface to reflect solar radiation. [14] Arrangement of space solar cells (WSC) according to one of the preceding claims, wherein the protective arrangement (SA) is formed directly at one of the two ends and the distance in the X direction between the protective arrangement (SA) and the space solar cell connected to the protective arrangement (SA) is in a range between 10 µm and 10 mm or in a range between 100 µm and 2 mm. [15] Arrangement of space solar cells (WSZ) according to one of the preceding claims, wherein a cooling for the string protection diodes (DGDS) is formed by means of the metal strip (BUB).

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