There are many different designs, none of which have yet flown.
Depending on many details such as orbit and the wavelength used for
wireless power transmission, even a relatively small satellite (10's of
MW say) might be reasonable.

Given the power level (10 MW to 10 GW) you can then figure out roughly
the area and mass requirements. Incoming solar energy is about 1.3
kW/square meter at Earth's orbit, and conversion efficiencies are likely
to be 35% or less, so 10 MW at the satellite would require at least
20,000 sq meters area. 10 GW would require 20 million sq meters, or 20
sq km. Mass requirements depend on a lot of design issues as well, but
at a minimum you have to account for the mass of the solar cells - the
best available that I am aware of (Unisolar Ovonic sells thin film cells
with this claimed performance) are about 1 kg per kW. So for 10 MW at
the satellite, that's 10,000 kg, or 10 metric tons. For the 10 GW
satellite it would be 10,000 metric tons. On that you have to add the
mass needed for structural integrity, power transmission, and propulsion.

A good reference is the 2001 NRC report:

http://www.nap.edu/books/0309075971/html/

which has citations of many relevant papers in the field.

Arthur

hoseung1 wrote:

>I want to know the weight and area of solar power satellite.
>An also I want to know the paper describing the weight and area of
>SPS.
>Thanks.
>
>
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