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A CSC of 4460 kg mass.
With apogee altitude equal to 400 km, the speed in perigee -- 7937 m/s.
The CSC speed in circular orbit -- 7849 m/s (after the braking pulse of 88 m/s).
Electric power of the membrane solar batteries (SB) -- 1.945 MW.
Electric power of the fuel cells (FC) -- 1.556 MW.
Electric power of electrorocket engines (ERE) -- 1.556 MW.
ERE efficiency -- 0.75
FC charging efficiency -- 0.8
ERE specific pulse -- 15700 m/s
SB mass -- 780 kg (0.4 kg/KW)
FC mass -- 780 kg (0.5 kg/KW)
ERE mass -- 780 kg (0.5 kg/KW)
Cargoes' catcher mass -- 500 kg.
The rest equipment mass -- 1620 kg.
Mass of the captured portion of cargo -- 50 kg.
Length of the track of the cargo substance -- 16000m.
Time of track capturing -- 2 s.
Acceleration of braking in course of cargo capturing -- 44 m/s2 (~4.5g).
Number of operations on cargo capturing for 1 year -- 2500.
Mass of the captured cargo for 1 year -- 125 tons.
Mass of the captured air for 1 year -- 125 tons.
Mass of the air used in ERE for 1 year -- 125 tons.
Mass of the cargo accumulated in the orbit for 1 year -- 125 tons.
The fleet of multiuse suborbital rockets for exploitation in course of 1 year -- 6-12 pieces (with 200-400 launches/rocket endurance).
In case of usage of ERE and FC with less specific power -- 0.75 kg/KW and 1 kg/KW correspondingly, the CSC mass gets doubled with keeping up the possibility to fulfill the aforementioned scheme of operation at the account of double circuits with half incrementation of speed on each of them by 22+22 m/s.

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