Architectural Design Criteria For Spacecraft

Architectural Design Criteria for Spacecraft Solar Arrays

Architectural Design Criteria for Spacecraft Solar Arrays 165 With E g0 = 1.41 eV,  e=-6.6×10-4 eV/°K, and à e=552 °K. The current iL due to illumination is given instead by i T KT T JL t K ot (mA/cm 2) (4) Where J tot is light intensity (W/ m 2), È (T) is the efficiency of the cell, K(T) is a coefficient to be determined as function of the temperature.

  Design, Criteria, Architectural, Spacecraft, Architectural design criteria for spacecraft