Deployable solar array assembly

A solar cell array system for deployment from a spacecraft, the solar cell array system having a first and a second solar cell panel assembly, each solar cell panel assembly comprising:

• a flexible solar panel;
• a rotational member connected to said flexible solar panel, said rotational member having a first end and a second end;
• a hinge assembly disposed proximate to at least one of said first end and said second end of said rotational member, wherein said hinge assembly of the first solar cell panel assembly is connected to said hinge assembly of the second solar cell panel assembly;
• and
• a locking device disposed proximate to at least one of said first end and said second end of said rotational member, wherein said locking assembly of the first solar cell panel assembly is configured to lock with said locking assembly of the second solar cell panel assembly.

A solar cell array system for deployment from a spacecraft, the solar cell array system comprising:

• a solar cell panel assembly comprising:
• a flexible solar panel having a first end, a second end, and a first longitudinal axis;
• a rotating member coupled to said first end of said flexible solar panel, said rotating member having a second longitudinal axis and a first and a second end, wherein, when said solar cell panel assembly is in a stored mode, said flexible solar panel is wound about said rotating member and, when said solar cell panel is being deployed, said rotating member is configured to rotate about said second longitudinal axis so that said flexible solar panel may be unwound from said rotating member;
• a first and second longitudinal stabilizing means for stabilizing said flexible solar panel along said first longitudinal axis, said first longitudinal stabilizing means coupled to said first end of said rotating member and said second longitudinal means coupled to said second end of said rotating member;
• a first tether means for applying a compressive force to an end of said first longitudinal stabilizing means;
• and
• a second tether means for applying a compressive force to an end of said second longitudinal stabilizing means;
• and
• a deployment means for deploying said solar cell panel assembly from said spacecraft.

A method for deploying a stowable solar cell array from a spacecraft, the method comprising the steps of:

• configuring the array as a plurality of flexible solar cell panels, wherein each flexible solar cell panel is wound about a rotating member, the rotating members coupled in series;
• orienting said rotating members along an imaginary substantially straight line that is substantially perpendicular to a surface of the spacecraft;
• rotating said rotating members, causing each of said plurality of flexible solar cell panels to unwind from said rotating members;
• extending at least two support members along each of said plurality of flexible solar cell panels;
• and
• applying a compressive force to each of said at least two support members.