Test-fired Rocketdyne SE-8 rocket engine for an Apollo Command Module Reaction Control System (RCS) bi-propellant thrust chamber assembly manufactured in 1964, weighing 9.9 lbs, measuring 11.25″ in height and 5″ in diameter, with dual wiring extending to approximately 36″ in length. The Rocketdyne label reads, in part: “Propulsion System Component, Rocket Engine Assy, Part No. 99-106003, Contract No. IDWA 6502, Date of Mfg. 9-8-64…Model No. SE8-2…Serial No. 4054401.” The unit bears numerous inspection stamps markings, with examples as follows: "Engine Ring Development," "Ground Test Use Only," "600 n 5 V 24164," and "Customer S/No. 063600842101, Manufacturer's S/No. NA842101." The fuel and oxidizer valve assemblies remain present to the upper portion. In very good condition, with expected wear from testing.
Twelve of these engines were installed on the Apollo Command Module (CM), with each utilizing the propellants Nitrogen Tetroxide (N2O4) and Monomethylydrazine (MMH) as fuel. SE-8s were integrated on the CM in two systems of six engines and provided it with rotation control, rate damping, and attitude control after its separation from the Service Module and during reentry. Sale of this item is limited to US Citizens and Organizations (only) to comply with US technology transfer restrictions.
Terms and abbreviations used in our descriptions.