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The version 1 (top) and the version 2 (bottom) of the Instrument Unit. Saturn I Block I vehicles (SA-1 to SA-4) were guided by instruments carried in canisters on top of the S-I first stage, and included the ST-90 stabilized platform, made by Ford Instrument Company and used in the Redstone missile. [11]
The Saturn family used liquid hydrogen as fuel in the upper stages. Originally proposed as a military satellite launcher, they were adopted as the launch vehicles for the Apollo Moon program . Three versions were built and flown: the medium-lift Saturn I , the heavy-lift Saturn IB , and the super heavy-lift Saturn V .
The Saturn IB launched two uncrewed CSM suborbital flights to a height of 162 km, one uncrewed LM orbital flight, and the first crewed CSM orbital mission (first planned as Apollo 1, later flown as Apollo 7). It also launched one orbital mission, AS-203, without a payload so the S-IVB would have residual liquid hydrogen fuel.
The fuel pump delivered 15,471 US gallons (58,560 litres) of RP-1 per minute while the oxidizer pump delivered 24,811 US gal (93,920 L) of liquid oxygen per minute. Environmentally, the turbopump was required to withstand temperatures ranging from input gas at 1,500 °F (820 °C) to liquid oxygen at −300 °F (−184 °C).
The Saturn I booster was a huge increase in size and power over anything previously launched. It was three times taller, required six times more fuel and produced ten times more thrust than the Juno I rocket that had launched the first American satellite, Explorer 1, into orbit in 1958. [2]
Eight H-1 engines in a Saturn I. Like all of Rocketdyne's early engines, the H-1 used a waterfall injector fed by turbopumps and regeneratively cooled the engine using the engine's fuel. The combustion chamber was made of 292 stainless steel tubes brazed in a furnace. [12] Unlike the J-2 engine used on the S-IVB stage, the H-1 was a single ...