Efficient solar panel wing-stowage on a space launch vehicle

A launch vehicle having a longitudinal axis, the launch vehicle comprising:

• a payload;
• an upper stage;
• and
• an adapter assembly positioned between the payload and the upper stage and structurally interconnecting the payload and the upper stage, the adapter assembly comprising a frame having a longitudinal axis, a solar panel having a stowed state and a deployed state and a perimeter wall having a height extending parallel to the longitudinal axis and an interior surface and exterior surface, wherein the frame defines an interior space, and wherein in a stowed state the solar panel is positioned within the interior space of the frame in a plane substantially perpendicular to the longitudinal axis of the frame, and wherein the perimeter wall further comprises at least one port extending from the interior surface to the exterior surface and adapted to receive a payload module.

A method of assembling a launch vehicle having a longitudinal axis, the method comprising:

• obtaining a plurality of solar panels, a frame having a longitudinal axis, a forward end and an aft end and defining an interior space, a first separation ring, a second separation ring, and two separable components of the launch vehicle;
• interconnecting the first separation ring to the forward end of the frame and the second separation ring to the aft end of the frame;
• interconnecting a first and a second array of solar panels to the frame;
• stowing the first array of solar panels at least partially within the interior space of the frame defined by the first separation ring and in a plane substantially perpendicular to the longitudinal axis of the frame;
• stowing the second array of solar panels at least partially within the interior space of the frame defined by the second separation ring and in a plane substantially perpendicular to the longitudinal axis of the frame;
• positioning the frame between the separable components along the longitudinal axis of the launch vehicle;
• and
• interconnecting the frame to the separable components.

A system for stowing one or more solar panels on a space vehicle comprising:

• a space vehicle having a longitudinal axis, and a first component and a second component, where at least one of the first and second components are separable from the space vehicle;
• a frame positioned between the first and second components and structurally interconnecting the first and second components, the frame and the first and second components aligned along the longitudinal axis of the space vehicle, the frame defining an interior space and having a longitudinal axis;
• the frame further comprising an adapter having a forward end and an aft end, a first separation ring interconnected to the forward end of the adapter, and a second separation ring interconnected to the aft end of the adapter;
• and
• a first array and a second array of solar panels having a stowed state and a deployed state, wherein in a stowed state the first array is positioned in a plane substantially perpendicular to the longitudinal axis of the frame and at least partially within an interior space defined by the first separation connector and the second array is positioned in a plane substantially perpendicular to the longitudinal axis of the frame and at least partially within an interior space defined by the second separation connector.