CUBICS

Responsible: @Abegail Gagelonia
Accountable: @Ben Harbarenko
Consulted: @Ben Harbarenko, @Ethan Ledig , @Katrina Hamdon , @Alice Nguyen , @Sarah Keats
Informed: Mechanical Team

What: Generate a Hinge assembly concept in CAD. Hinge should fit within the limited volume and interface the satellite with the deployable solar panels. The envelope available to contain the hinges and the solar panels is shown in this image:

Note the 9mm x 84mm protrusions. With the inclusion of surface mount solar panels the available depth is actually closer to 7mm. This is the volume that the hinges must function within. Your concept must be spring loaded to deploy should the solar panels be unconstrained. Cost of manufacture for both in house, and outsourced will be considered in a future trade study. Deliver presentation of CAD design at MecE meeting.

Consider reviewing Ex2 CAD for hyperion hinge for reference on past design. The full satelite CAD may be found here: https://drive.google.com/drive/u/0/folders/1zw0Y4LhD7IkPOgsIkOr8FfsBMZjpWSua

This is a detailed design document for the past design:
https://docs.google.com/document/d/1CXjtnlCOI9ZgDuHZ-j_Es-M7oV87Fg4Ec86F1mfKNsQ/edit

Why: It is crucial that a traditional hinge design is prepared for integration of the satellite as it is currently assumed that this will be the design that flies.