NOVELTY - The method involves providing a string (320) of solar cells (310) for a solar array. A portion of one of the strings of solar cells of solar array is deactivated when the power produced by solar array reaches a maximum power allowance threshold. A portion of one of the strings of solar cells in solar array is activated when power produced by solar array reaches a minimum power allowance threshold. The deactivation of portion of one of strings of solar cells is performed by connecting a shunting plug (370) to the portion of one of strings of solar cells to be deactivated.    USE - Method for reconfiguring solar array used on vehicles such as satellites such as low earth orbiting (LEO) satellite, medium earth orbiting (MEO) satellite, or geosynchronous earth orbiting (GEO) satellite (claimed), space stations such as international space station (ISS), and unmanned vehicle such as deep-space vehicle and on building.    ADVANTAGE - Since a portion of one of the strings of solar cells of solar array is deactivated or activated when the power produced by solar array reaches a maximum or minimum power allowance threshold respectively, the shunting plug the shunting plugs are removed when solar array power production declines and the additional panel area is allowed to be brought on-line so as to provide a pseudo-constant solar array power source to downstream loads so that the shunting portions allows the solar array to effectively act as a large radiator and dissipate heat. Thus, the lifetime of solar array is extended while eliminating the hazards of direct-pointing of the solar array towards the sun, and/or having an ineffective solar array shading system.    DETAILED DESCRIPTION - An INDEPENDENT CLAIM is included for a reconfigurable solar array apparatus.    DESCRIPTION OF DRAWING(S) - The drawing shows a circuit diagram of the reconfigurable solar array system employed by the international space station.    Solar cells (310)    String of solar cells (320)    Diode (330)    Cap (360)    Shunting plug (370)