posted on Mar, 3 2015 @ 02:03 PM
Here is some revisited calculation and hypothesis.
Applicable to a naval laser system that was described some time ago here on ATS. A CW 30kW ~1um unit.
Angular resolution for excellent atmospheric seeing condition = 2uRad, giving 1.6m at 800km distance.
Apperture equivalent for 2uRad = 0.6meter.
Circle of 1.6m area = 2m^2
30kW on 2m^2 give an irradiance of 15kW/m^2
That's 10x the Sun irradiance in space. Aimed at thermal radiator and sustained, it may be possible to overheat the satellite and (maybe) cause a
thermal runaway in a battery or semething else.
The question that remain: Does a Sun-synchronous orbit sat present it's thermal radiator with an angle sufficient for an efficient transfert of power
edit on 2015-3-3 by PeterMcFly because: (no reason given)