Non-Catalytic Hydrazine Thruster.
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
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The present invention concerns itself with a nominal 5 lbF thrust attitude control engine which derives its thrust from the non-catalytic decomposition of hydrazine. In essence, the thruster of this invention is composed of an elongated cylindrical, pressure chamber having an elongated cylindrical heating well positioned within the center of the chamber along its longitudinal axis. An electrical heater is positioned within the well. The chamber is operationally connected to a source of hydrazine which enters the chamber through an injection tube positioned tangential to the interior surface of the chamber. The configuration and position of the injector tube as well as the heating means are critical components of the thruster of this invention. These essential elements, with their unique placement and configuration, are responsible for providing the long life, high thrust and the means for maintaining the thruster at the temperature level necessary for successful pulsed as well as steady state operation. Accordingly, the primary object of this invention is to provide a monopropellant hydrazine thruster capable of operating at a 5 lbF nominal thrust level with a 3 to 1 blow-down range.
- Liquid Rocket Propellants