Abstract: A method of fabricating a space vehicle including a solar cell array panel, the method comprising: providing a plurality of multijunction solar cells; dispensing an uncured silicone coaling on each of the solar cells using an automated process with visual recognition; picking a cover glass from a cartridge stack and mounting the cover glass over the discrete respective solar cell to form a discrete Cell-Interconnect-Cover Glass (CIC) assembly; curing the silicone coating on each of the solar cells to mount it to the panel; and mounting the panel on the space vehicle.

Abstract: A method of fabricating a multijunction solar cell array on a carrier using one or more automated processes, the method comprising providing a first multijunction solar cell including a first contact pad and a second contact pad disposed adjacent the top surface of the multijunction solar cell along a first peripheral edge thereof attaching a first electrical interconnect to the first contact pad of said first multijunction solar cell using a pick and place process attaching a second electrical interconnect to the second contact pad of the first multijunction solar cell using a pick and place process positioning in the first multijunction solar cell over an adhesive region of a permanent carrier using an automated machine/vision apparatus and bonding the first multijunction solar cell to the adhesive region using pressure and/or heat.

Abstract: A system and method for removing a backing from a ply of composite material is disclosed. The system includes a roller having a roller axis and a roller surface that circumscribes the roller axis. The system also includes an adhesion feature disposed on the roller surface. The system further includes a roller drive to move the roller along a travel path that is perpendicular to the roller axis and to rotate the roller about the roller axis.

Abstract: A system and method for removing a backing from a ply of composite material is disclosed. The system includes a roller having a roller axis and a roller surface that circumscribes the roller axis. The system also includes an adhesion feature disposed on the roller surface. The system further includes a roller drive to move the roller along a travel path that is perpendicular to the roller axis and to rotate the roller about the roller axis.

Abstract: A method of fabricating a multijunction solar cell panel by providing a plurality of multijunction solar cells; dispensing out uncured silicone coating on the solar cells using an automated process with visual recognition, and curing the silicone coating on the solar cell to complete the Cell-Interconnect-Cover Glass (CIC) assembly.

Abstract: A method of collecting visual data using a mobile image capture device is provided. The method comprises the steps of: capturing image data with the mobile image capture device and associating time and location data with each image; and storing the image data and associated time and location data. The method further comprises monitoring the position and orientation of the image capture device. The method further comprises: defining an area surrounding or next to the location of the mobile image capture device; and identifying a characteristic of the defined area based on one or more of: the density of the image data in the area; the age of the image data in the area; and/or data demand values associated with locations within the defined area. The timing of capture of image data is based on the characteristic of the defined area.

Abstract: A method of fabricating a multijunction solar cell by providing a plurality of multijunction solar cells; dispensing an uncured silicone coating on the solar cells using an automated process with visual recognition, and curing the silicone coating on the solar cell.

Abstract: A method of fabricating a multijunction solar cell panel by providing a plurality of multijunction solar cells; dispensing out uncured silicone coating on the solar cells using an automated process with visual recognition, and curing the silicone coating on the solar cell to complete the Cell-Interconnect-Cover Glass (CIC) assembly.

Abstract: A space-qualified solar cell assembly comprising a plurality of space-qualified solar cells mounted on a support, the support comprising a plurality of conductive vias extending from the top surface to the rear surface of the support. Each one of the pluralities of space-qualified solar cells is placed on the top surface with the first contact of a first polarity of the space-qualified solar cell electrically connected to the first conductive via. A second contact of a second polarity of each space-qualified solar cell can be connected to a second conductive via so that the first and second conductive portions form terminals of opposite conductivity type. The space-qualified solar cells on the module can be interconnected to form a string or an electrical series and/or parallel connection by suitably interconnecting the terminal pads of the vias on the back side of the module.

Abstract: The present disclosure provides methods of fabricating a multijunction solar cell panel in which one or more of the steps are performed using an automated process. In some embodiments, the automated process uses machine vision.

Abstract: A manufacturing apparatus for mounting an array of solar cells on a flexible support or panel comprising: a first roller having an axis and supporting a release carrier on which a sequence of solar cell assemblies are mounted on a spool and wound around the axis; a second roller having an axis parallel to the axis of the first roller and supporting a polyimide sheet having a sequence of pressure sensitive adhesive (PSA) patches on which the solar cell assemblies are to be mounted; wherein the first and second rollers are aligned and rotate in the opposite directions (i.e.

Abstract: Solar cell array assemblies or modules mounted on a space vehicle having discrete predefined pressure sensitive adhesive (PSA) regions thereon. In certain embodiments, the solar cell array modules may be conveniently mounted on the surface of a panel of a space vehicle or satellite with the discrete predefined PSA regions sized and shaped to match portions of the panel.

Abstract: Solar cell array assemblies or modules and methods of making and using such solar cell array assemblies or modules, having discrete predefined pressure sensitive adhesive (PSA) regions thereon. In certain embodiments, the solar cell array modules may be conveniently mounted on the surface of a panel of a space vehicle or satellite with the discrete predefined PSA regions.

Abstract: Solar cell array assemblies or modules mounted on a space vehicle having discrete predefined pressure sensitive adhesive (PSA) regions thereon. In certain embodiments, the solar cell array modules may be conveniently mounted on the surface of a panel of a space vehicle or satellite with the discrete predefined PSA regions sized and shaped to match portions of the panel.

Abstract: A space-qualified solar cell assembly comprising a plurality of space-qualified solar cells mounted on a support, the support comprising a plurality of conductive vias extending from the top surface to the rear surface of the support. Each one of the plurality of space-qualified solar cells is placed on the top surface with the first contact of a first polarity of the space-qualified solar cell electrically connected to the first conductive via. A second contact of a second polarity of each space-qualified solar cell can be connected to a second conductive via so that the first and second conductive portions form terminals of opposite conductivity type. The space-qualified solar cells on the module can be interconnected to form a string or an electrical series and/or parallel connection by suitably interconnecting the terminal pads of the vias on the back side of the module.

Abstract: A solar cell assembly in which a solar cell component is bonded to a flexible support is disclosed. The solar cell assembly comprises a flexible support with a predetermined size, a solar cell component, bonding adhesive between the support and the solar cell component, wherein the support with the predetermined size has a uniform borders of 0.003 inch to 0.2 inch in width extending beyond the edges of the solar cell component.

Abstract: Solar cell array assemblies or modules and methods of making and using such solar cell array assemblies or modules, having discrete predefined pressure sensitive adhesive (PSA) regions thereon. In certain embodiments, the solar cell array modules may be conveniently mounted on the surface of a panel of a space vehicle or satellite with the discrete predefined PSA regions.

Abstract: The method for producing solar cells comprises the step of dividing a non-rectangular solar cell wafer into a plurality of solar cells, the plurality of solar cells comprising at least one solar cell having a first geometric configuration, and at least one solar cell having a second geometric configuration, different from the first geometric configuration. The solar cells can have a rectangular shape and be re-arranged and combined into a rectangular solar cell assembly.

Abstract: The method for producing solar cells comprises the step of dividing a non-rectangular solar cell wafer into a plurality of solar cells, the plurality of solar cells comprising at least one solar cell having a first geometric configuration, and at least one solar cell having a second geometric configuration, different from the first geometric configuration. The solar cells can have a rectangular shape and be re-arranged and combined into a rectangular solar cell assembly.

Abstract: A solar cell assembly or module comprising a plurality of solar cells mounted on a support, the support comprising a plurality of conductive vias extending from the top surface to the rear surface of the support. Each one of the plurality of solar cells is placed on the top surface with the first contact of a first polarity of the solar cell electrically connected to the first conductive via. A second contact of a second polarity of each solar cell can be connected to a second conductive via so that the first and second conductive portions form terminals of opposite conductivity type. The solar cells on the module can be interconnected to form a string or an electrical series and/or parallel connection by suitably interconnecting the terminal pads of the vias on the back side of the module.