NOVELTY - The strain isolation layer assembly (50) has a rigid solar layer (12), a strain isolation layer (30b) and an underlying substrate layer (52). A strain isolation layer is provided with discontinuous configuration, vertical rigidity and horizontal shear flexibility. The strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form the strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer and reduce the strains induced on the rigid solar layer.    USE - Strain isolation layer assembly mounted on spacecraft, satellite, space station, rotorcraft, watercraft, automobile, truck, bus, architectural structure and aircraft, and rigid solar layer such as solar panel, solar cell, solar panel array and solar panel laminated array (all claimed). Can also be used in aerospace vehicle, space launch vehicle, rocket, boat, train, commercial and residential building, transport vehicle, terrestrial and space-based structure, and unmanned aerial vehicle (UAV).    ADVANTAGE - Since the strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer, for isolating the rigid solar layer, the structural strain, thermal strain and mechanical strain induced on the rigid solar layer can be reduced. Manufacturing cost, complexity, overall weight can be reduced by mounting an isolation layer assembly.    DETAILED DESCRIPTION - INDEPENDENT CLAIMS are included for the following:    (1) an aircraft; and    (2) a method of reducing strains on a rigid solar layer.    DESCRIPTION OF DRAWING(S) - The drawing shows a front perspective view of the strain isolation layer assembly showing a pressure loading effect and deflections multiplied by one hundred and fifty.    Rigid solar layer (12)    Strain isolation layer (30b)    Strain isolation layer assembly (50)    Underlying substrate layer (52)    Spacing between vertical column support (180)    Pressure loading portion (186)