Solar array spring elements for stacking spacecraft

A method, comprising:

• placing at least a first spacecraft in a launch vehicle;
• stacking a second spacecraft with the first spacecraft in the launch vehicle such that a solar array of the first spacecraft extends between the first spacecraft and the second spacecraft, the solar array is in physical contact with the second spacecraft and a spring element that forms one or more of a spring-loaded hinge of the solar array or a frame structure element of the solar array is spring-loaded to apply a force between the first spacecraft and the second spacecraft;
• subsequently, deploying the second spacecraft using the force of the spring element between the first spacecraft and the second spacecraft to separate the second spacecraft from the first spacecraft;
• and
• using the force of the spring element to deploy the solar array from a folded configuration to an unfolded configuration.

A stack of spacecraft, each spacecraft in the stack comprising:

• a spacecraft body;
• a solar array attached to the spacecraft body, the solar array including a frame structure made of a plurality of tubes connected by nodes;
• and
• a solar array spring element that forms one or more of a first spring-loaded hinge of the solar array or a tube of the solar array, the solar array spring element configured to provide a force between the solar array and one or more components of a neighboring spacecraft in the stack of spacecraft.