Rocket Engine, Liquid Fuel, Orbital Attitude Maneuvering System (OAMS), Gemini

Cylindrical, metallic, tapering down to wider diameter circular nozzle at end, at slight angle to the vertical. Designed with this shaped nozzle to fit the contours of the Gemini spacecraft. Two parallel propellant feed-in pipes jutting out from top of cylinder, with one each, smaller diameter curved pipe welded on to side of each outlet; two other smaller diameter pipes, from top of each outlet; two clear plastic wrappings over propellant inlet pipe ends, but no usual protective caps over adjoining curved pipes. Nozzle, phenolic; internally, ceramic liner around combustion chamber; red plastic nozzle protective cover removed from nozzle and comes separate with motor, showing there is a black rubber gasket undeneath protective cover; protective cover also with five sided clear plastic dessicant container with adjacent white adhesive sticker with last dessicant filling date of 7/9/64; actual nozzle covered only with adhesive tape. Two thick red stripes painted around top of cylinder and letters, also in red, painted between stripes, CTU; red lines indicate this motor was not suitable for flight testing. With black rectangular plastic temperature sensor box on one side of oxidizer outlet, with electrical wire, with white insulated plastic, protruding from bottom of sensor box and ending with four individual blue plastic insulated wire strands. With black and white metallic manufacturer's plate around top of cylinder.