1N Monopropellant Hydrazine Thruster
Description
The Rafael 1N Monopropellant Hydrazine Thruster generates the required thrust for maneuvering satellites by means of a hot gas jet created by hydrazine decomposition and expansion through the exit nozzle. The thruster was originally designed and qualified for the Israeli OFEQ program and subsequently selected for numerous commercial and scientific satellite programs.
The thruster is governed by a solenoid-operated, dual-coil, dual-seat normally-closed Flow Control Valve (FCV) with an integral 15-micron absolute filter at the valve inlet. The all-welded FCV and Thrust Chamber Assembly (TCA) are joined through a Haynes-alloy thermal barrier element. The TCA incorporates a bell-shaped nozzle with an expansion ratio of 130:1.
The thruster includes an electric catalyst bed heater (CBH) with two resistance coils, providing the initial thermal condition for long-duration and repeatable operation. Inlet connection is through an MS 33656-4 threaded connector or optional 1/4" or 3/8" welded tube. Completely ITAR-free.