A concept for the Lunar Excursion Module, reported on in May of 1962. It seems to have originated with Maxime Faget (of Mercury capsule design fame) at the Manned Spacecraft Center in Houston. It is interesting not only for its conical shape, but also far is basic layout… as with the Soviet LK lander, this design features a single main propulsion system that fires through a “hollow” landing stage. The Soviet design packed all the propulsion tanks into the ascent stage; this NASA design had distributed tanks. This would make the ascent vehicle lighter, at the expense of plumbing complexity. Propellants were N2O4 oxidizer and either MMH or 50% N2H4 + 50% UDMH.
This vehicle would weigh 23,959 pounds at separation from the Command Module; 11,204 at landing. At liftoff – after leaving behind the landing stage – it would weight 7,068 pounds; at burnout, 3,568 pounds.
