Apollo SMLL

North American Aviation (NAA) proposed use of the SM as a lunar logistics vehicle (LLV) in 1966. The configuration, simply stated, put a landing gear on the SM. It was proposed for use in an unmanned, direct landing mode. The system required the addition of remote guidance and control and a suitable throttling engine.

So-called "conversions" of the present SM engine really inferred a new engine development, probably of the same magnitude as that required for the LM descent engine. It was considered wiser by NASA's Bellcomm consultants to develop a new pump-fed engine or use a converted Agena engine and take advantage of the superior performance available.

Advantages of the SM Lander were said to be simple mission configuration; straightforward development; and substantial payload capacity at an early operational date (5,000 kg with an Apollo Block 1 SM; 7500 kg with a service module extended in length by 107 cm). Technical challenges included designing the landing gear and throttling engine provisions, and remote guidance and control for lunar landing.

• Bendersky, C, Manned Lunar Program Options - Mission Equipment - Case 230, Bellcomm memo for file, Sept. 29, 1967.