Our deployable wing fitted with triple-junction GaAs cells instead of silicon. One to five arrays on the same yoke and hinges as the Si-Core Wing, for missions that need more power per area or have to live with a harsher radiation environment.
Each array carries ES-30TJSC-80 or ES-30TJSC-30 CICs (coverglass, interconnectors, bypass diode) welded into serpentine series strings on the honeycomb sandwich panel. The panel is sized to the cell grid, the large cells are nested at their wafer chamfers, and string lengths are set so nothing runs into the hinge fittings. Arrays fold face-to-face into a flat launch stack on the yoke and deploy in sequence. Substrate, hinges, hold-down and release, yoke, harness and strings are delivered as one unit.
One array type, one yoke, one set of interfaces — configure one to five arrays per wing.
Triple-junction CICs at about 30 % BOL efficiency — roughly 1.7 × the power per area of silicon, and a radiation lifetime suited to GEO, MEO and long-duration LEO.
Aluminium honeycomb sandwich panels — flight-proven, from our structures partner.
Corner hinge fittings at every joint and two hold-down pads per array, aligned through the stack.
Cells welded into series strings on our qualified stringing line, each cell measured on the AM0 test bench, bypass diode per cell.
Shaker, thermal vacuum, deployment on the anti-gravity rig.
Radiation lifetime and efficiency per area over long missions.
Where silicon degradation would eat into the power margin.
More power from the same stowed volume and panel area.
Number of arrays, cell type and string layout, hinge and root interfaces, harness and connectors are defined together with you for your mission and bus. Our sales team walks you through the options and comes back with a proposal, budgetary pricing and lead time.
Your bus and envelope, the power budget per spacecraft, bus voltage, mission orbit and lifetime, and the number of spacecraft you are planning for.