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It really depends on which part of the Apollo spacecraft you're talking about. Different sections used different propellants.

  • The first stage of the Saturn V, the S-1C section, burned RP-1 rocket fuel with LOX (liquid oxygen) as the oxidizer.
  • The Saturn V S-II and S-IVB sections (2nd and 3rd stages) burned LOX and liquid hydrogen.
  • The Apollo Command Module used unsymmetrical dimethylhydrazine (UDMH) fuel oxidized by dinitrogen tetroxide (N2O2) for RCS (reaction control system) thrusters
  • The Service Module used monomethylhydrazine (MMH) oxidized with N2O2 for its RCS attitude thrusters and (UDMH/N2H4) oxidized with N2O2 for the SPS (service propulsion system)
  • The Lunar Module used Aerozine 50 for fuel and N2O4 as oxidizer for the RCS, DPS (descent propulsion) and APS (ascent propulsion) systems
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11y ago

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