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SpaceNut

Administrator

From: New Hampshire

Registered: 2004-07-22

Posts: 28,946

Re: SLS Rocket + Orion + Apollo LEM

Continuing here from the new Russian moon mission....
With all the details to make use of to build from Why should a company not want to buid one for NASA to purchase under a COT's developement....

https://en.wikipedia.org/wiki/Apollo_Lunar_Module

Materials
Aluminum, titanium, aluminized Mylar and aluminized Kapton blankets

The return payload included the lunar rock and soil samples collected by the crew (as much as 238 pounds (108 kg) on Apollo 17), plus their exposed photographic film.

Crew: 2
Crew cabin volume: 235 cu ft (6.7 m3)
Habitable volume: 160 cu ft (4.5 m3)
Crew compartment height: 7.667 ft (2.337 m)
Crew compartment depth: 3.50 ft (1.07 m)
Height: 12.33 ft (3.76 m)
Width: 14.08 ft (4.29 m)
Depth: 13.25 ft (4.04 m)
Mass, dry: 4,740 lb (2,150 kg)
Mass, gross: 10,300 lb (4,700 kg)
Atmosphere: 100% oxygen at 4.8 psi (33 kPa)
Water: two 42.5 lb (19.3 kg) storage tanks
Coolant: 25 pounds (11 kg) of ethylene glycol / water solution
Thermal Control: one active water-ice sublimator
RCS propellant mass: 633 lb (287 kg)
RCS thrusters: sixteen x 100 lbf (440 N) in four quads
RCS propellants: Aerozine 50 fuel / nitrogen tetroxide (N2O4) oxidizer
RCS specific impulse: 290 s (2,840 N·s/kg)
APS propellant mass: 5,187 lb (2,353 kg)
APS engine: Bell Aerospace LM Ascent Engine (LMAE) & Rocketdyne LMAE Injectors
APS thrust: 3,500 lbf (16,000 N)
APS propellants: Aerozine 50 fuel / nitrogen tetroxide oxidizer
APS pressurant: two 6.4 lb (2.9 kg) helium tanks at 3,000 pounds per square inch (21 MPa)
APS specific impulse: 311 s (3,050 N·s/kg)
APS delta-V: 7,280 ft/s (2,220 m/s)
Thrust-to-weight ratio at liftoff: 2.124 (in lunar gravity)
Batteries: two 28–32 volt, 296 ampere-hour silver-zinc batteries; 125 lb (57 kg) each
Power: 28 V DC, 115 V 400 Hz AC

Height minus landing probes: 8.59 ft (2.62 m)
Width/depth minus landing gear: 12.83 ft (3.91 m)
Width/depth including landing gear: 31.0 ft (9.4 m)
Mass including fuel: 22,783 lb (10,334 kg)
Water: one 151 kg (333 lb) storage tank
DPS propellant mass: 18,000 lb (8,200 kg)
DPS engine: TRW LM Descent Engine (LMDE), TRW TR-201[13]
DPS thrust: 10,125 lbf (45,040 N), throttleable between 10% and 60% of full thrust
DPS propellants: Aerozine 50 fuel / nitrogen tetroxide oxidizer
DPS pressurant: one 49-pound (22 kg) supercritical helium tank at 1,555 psi (10.72 MPa)
DPS specific impulse: 311 s (3,050 N·s/kg)
DPS delta-V: 8,100 ft/s (2,500 m/s)
Batteries: four (Apollo 9-14) or five (Apollo 15-17) 28–32 V, 415 A·h silver-zinc batteries; 135 lb (61 kg) each

Apollo Lunar Module Documentation

Mars_B4_Moon

Member

Registered: 2006-03-23

Posts: 9,281

Re: SLS Rocket + Orion + Apollo LEM

Nasa’s new rocket is the last hurrah for US space agency’s old ways

https://www.ft.com/content/4ef1a4c0-ce0 … 28e0049c69