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. This assembly consists of a #4 Frangibolt® with custom fastener and housing specific to this design.
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.
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Hinge mechanisms are torsion-spring activated and contain dual-sliding surfaces plus redundant springs. The panels are populated with (2) strings of 7 cells. Each deployable panel rotates 180 degrees at hinges mounted on the 2U edge of the spacecraft. This deployable solar array subsystem consists of two (2) deployable solar array panels and one (1) center mount panel. In 2017, the HaWK achieved flight heritage, and a similar version of HaWK is flying on the interplanetary mission, MarCO. The HaWK solar array was developed under Air Force Research Laboratory (AFRL) funding. If the mission requires, the sun-tracking single-axis SADA is used to track the sun’s position and provide maximum orbital average power (OAP). Deployment of the flip-out panels and wings is accomplished using stored energy provided by springs. The complete array system is stowed for launch and released after power is applied to a melt rod release mechanism. The HaWK array wings are designed to interface in both a gimbal or a non-gimbaled configuration without interface/configuration changes. The system consists of two array wings (center panel with 2 flip-out panels per wing), launch restraint mechanism and single-axis pancake solar array drive assembly (SADA) for improved orbital average power (OAP). Our innovative HaWK solar array is a high-performance, 42-Watt solar array system for the CubeSat class spacecraft.
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