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A CSC of 4250kg mass. SBs are not displayed. Possible to use nuclear electric generator instead of the SB.
With apolune altitude equal to 100 km, the speed in perilune -- 1695 m/s, with speed reduction by 20 m/s the CSC moves to the lower circular orbit (10 km altitude).
Speed incrementation by 21 m/s moves the CSC to the upper circular orbit (100 km altitude).
Electric power of the membrane solar batteries (SB) -- 0,156 MW.
Electric power of the fuel cells (FC) -- 0.07 MW.
Electric power of electrorocket engines (ERE) -- 0.07 MW.
ERE efficiency -- 0.6
FC charging efficiency -- 0.6
ERE specific pulse 6780 m/s
SB mass -- 80 kg (0.5 kg/KW)
FC mass -- 70 kg (1 kg/KW)
ERE mass -- 60 kg (0.75 kg/KW)
Cargoes' catcher mass -- 500 kg.
The rest equipment mass -- 3540 kg.
Mass of the captured portion of cargo -- 50 kg.
Length of the track of the cargo substance -- 1700m.
Time of track capturing -- 1 s.
Acceleration of braking in course of cargo capturing -- 20-21 m/s2 (~2 g).
Number of operations on cargo capturing for 1 year -- 3000.
Mass of the captured cargo for 1 year -- 150 tons.
Mass of the cargo used in ERE for 1 year -- 37.5 tons.
Mass of the cargo accumulated in the orbit for 1 year -- 112.5 tons.
The fleet of multiuse lunar suborbital rockets (rocket lifts) for exploitation in course of 1 year -- 2-4 pieces.

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