Rocket Engine, Liquid Fuel, Gemini Reentry Control System (RCS)

Cylindrical, canted at about 30 degrees at one end for internal nozzle exit; plumbing at other end consisting of two parallel vertical rods serving as propellant inlet lines, and other, smaller diameter pipes projecting from their sides with downward, goose neck ends. Canted nozzle end with matching angled mounting flange around opening; six holes drilled into flange at lower side for fitting onto spacecraft side; with six-sided red plastic nozzle protective cover, secured by six equidistant screws; rubber gasket under cover; clear plastic, six-sided desiccant container on protective cover, with nearby sticker adhered onto cover, with desicant installation date of 2/26/65; two yellow plastic protective caps over two small pipes and two black plastic wrappings over ends of two other small pipes; with mounting bracket. Overall, stainless steel, with brown phenolic nozzle protruding from nozzle flange, but covered with protective cover. Small rectangular black and white metal manufacturer's plate mounted around top of cylinder, or thrust chamber.