S.P.Korolev RSC Energia


LUNAR ORBITER

Principal characteristics of Lunar Orbiter

Crew, members
Maximum flight time, days
Orbiter mass in the artificial Moon satellite orbit, kg
Orbiter return mass, kg
Descent module mass, kg
Stage Ibooster (two-chamber):

thrust, kgf
thrust specific impulse, kgf s/kg

Rendezvous-correction engine:

thrust, kgf
thrust specific impulse, kgf s/kg

Propellant stock, kg

AT (oxidizer)
NSDH (fuel)

Overall dimensions, mm

length
maximum diameter of shell

2
13
9850
7530
2804

3388
314

417
296

2032
1120

10060
2930

The Lunar Orbiter was designed of a descent module, a habitable module containing a dedicated compartment accommodating an attitude control and berthing engines and a docking system mechanism, instrumentation and propulsion and power compartments where rocket stage I and power system equipment working on oxygen-hydrogen propellants were accommodated. The habitable compartment was simultaneously serving as an airlock for cosmonauts to move to the lunar vehicle through open space (in space suit Krechet).

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1. Descent module
2. Habitable compartment
3. Docking mechanism
4. Attitude control and berthing engines compartment
5. Berthing engines
6. Propulsion compartment
7. Power compartment
8. Attitude control engines
9. Rocket stage I
10. Instrumentation compartment

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