MMA Part #27A-42BE
This deployable solar array subsystem consists of two (2) deployable solar array panels and one (1) center mount panel. Each deployable panel rotates 180 degrees at hinges mounted on the 2U edge of the spacecraft. The panels are populated with (2) strings of 7 cells. Hinge mechanisms are torsion-spring activated and contain dual-sliding surfaces plus redundant springs.
Solar array hold-down and panel release is accomplished through the use of a Frangibolt® assembly which restrains the panel during launch, however when activated, releases the panel upon command. This assembly consists of a #4 Frangibolt® with custom fastener and housing specific to this design. The housing is a fully-integrated assembly that enables the Frangibolt® to be completely removed from the spacecraft, reset and replaced without disassembly of any main spacecraft components. Upon release of the panel using this mechanism, all severed components (bolt head, remaining bolt) remain with the spacecraft through the use of a containment system.
A center-mounted solar array panel is populated and provided as part of the deployable system. The center panel is fabricated with either an aluminum or composite substrate and bonded using compliant silicone adhesive. Additionally, fasteners may be added to provide a secure mounting method.
- Blocking diodes
- Mass 992g
- ERM launch restraint
- 42W BOL@15.9V