LASS

The Douglas Company (DAC) proposed the "Lunar Application of a Spent S-IVB Stage (LASS)". The LASS concept required a landing gear on a S-IVB Stage. The mission was an unmanned, direct-flight, using an existing lunar beacon to obtain a precise landing location. The LASS required either a highly throttleable J-2 type engine (J-2X) or a moderately throttleable J-2S with RL-10 engines added to provide proper landing control.

DAC studied several configurations and recommended a vertical lander with a payload package on top. Landed payloads in the order of 11,000 kg were claimed by DAC with the 1965 Saturn V capability. This payload was based on a more optimistic delta-V budget than used in other studies. However, the landed payload would still be substantial (7200 - 8600 kg) using the more conservative values. The LASS was related to contemporary Douglas SASSTO studies on use of a modified S-IVB as a reusable, recoverable upper stage or as a single-stage-to-orbit launch vehicle.