The present invention relates to a photovoltaic module, comprising: a glass panel, a back panel, a cell string including a plurality of cells encapsulated between the glass panel and the back panel, and a film containing metal oxides and/or silicon oxides disposed between the glass panel and the cell string. The photovoltaic module can block the migration of alkali metal ions and achieve the PID resistance.

A solar module lifting apparatus includes a base supported on the ground, a cylinder module including cylinder units disposed on the base and changing in height by contracting and stretching, and a rotary supply plate having one side supporting a solar module and the other side coupled to the cylinder module and moving up and down the solar module by operation of the cylinder module, in which the rotary supply plate includes a first hinge and a second hinge spaced apart from each other on the other side, the cylinder module includes a first cylinder unit and a second cylinder unit of which the upper ends are coupled to the first hinge and the second hinge by shafts, respectively, and at least one of the height and the inclination of the rotary supply plate is adjusted by contracting or stretching of the first cylinder unit and the second cylinder unit.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

One embodiment can provide a photovoltaic roof tile. The photovoltaic roof tile can include a front glass cover, a back glass cover, a plurality of photovoltaic structures positioned between the front and back glass covers, and a single encapsulant layer positioned between the front glass cover and the photovoltaic structures. A surface of the photovoltaic structures is in direct contact with the back glass cover.

One embodiment can provide a photovoltaic roof tile. The photovoltaic roof tile can include a front glass cover, a back glass cover, a plurality of photovoltaic structures positioned between the front and back glass covers, and a single encapsulant layer positioned between the front glass cover and the photovoltaic structures. A surface of the photovoltaic structures is in direct contact with the back glass cover.

A deflection pad may include a body including two peaks, and a recess in the body between the two peaks, the recess may be sized to accommodate a fastener such that when deployed, the fastener is below a height of the two peaks within the recess. The deflection pad may include arms projecting in a direction generally opposite the two peaks, the arms biased inward towards the recess. The deflection pad may be included in a system that includes a torsion beam and one or more support racks to which multiple PV modules may be attached, where the support are racks attached to the torsion beam. One or more deflection pads may be positioned on the support racks to be below the PV modules.

A deflection pad may include a body including two peaks, and a recess in the body between the two peaks, the recess may be sized to accommodate a fastener such that when deployed, the fastener is below a height of the two peaks within the recess. The deflection pad may include arms projecting in a direction generally opposite the two peaks, the arms biased inward towards the recess. The deflection pad may be included in a system that includes a torsion beam and one or more support racks to which multiple PV modules may be attached, where the support are racks attached to the torsion beam. One or more deflection pads may be positioned on the support racks to be below the PV modules.