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A CSC of 4250 kg mass, an SB block of 70 kg mass and a depot-block (a tanker) of 1000 kg mass for storage of liquid and solid cargoes of up to 10 tons mass. The SB block is connected by an electric cable of invariable length with the depot-block which in its turn is connected with the CSC by an electric cable of variable length (at the account of usage of a reel-to-reel mechanism of the cable unwinding and winding). Correspondingly fuel cells are not used for the ERE energy supply.
With apolune altitude equal to 100 km, the speed in perilune -- 1695 m/s (10 km altitude), with speed alterations by a value of around ± 10 m/s (around 20 m/s in total).
Electric power of the membrane solar batteries (SB) -- 0.133 MW
Electric power of electrorocket engines (ERE) -- 0.133 MW.
ERE specific pulse 6780 m/s
SB mass -- 70 kg (0.5 kg/KW)
ERE mass -- 100 kg (0.75 kg/KW)
Cargoes' catcher mass -- 500 kg.
The rest equipment mass -- 3511 kg.
Mass of the captured portion of cargo -- 50 kg.
Maximal length of the CSC electric cable -- 9000 m.
Length of the track of the cargo substance -- 1700m.
Time of track capturing -- 1 s.
Acceleration of braking in course of cargo capturing -- 9.97 m/s2 (~1 g).
Number of operations on cargo capturing for 1 year -- 4000.
Mass of the captured cargo for 1 year -- 200 tons.
Mass of the cargo used in ERE for 1 year -- 50 tons.
Mass of the cargo accumulated in the orbit for 1 year -- 150 tons.
The fleet of multiuse lunar suborbital rockets (rocket lifts) for exploitation in course of 1 year -- 2-4 pieces.

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