©1998-2012 Griff Wason | All rights reserved. All trademarks and trade names acknowledged.

Comments:

A typical type product illustration. There are cutaways and sectioned versions, but these were kept back by the client, who has preferred to stay in the background. This set were completed in three days, although it took two months to get all the permissions to proceed with the work.

It’s fair to say that the client was delighted, and other project from this client are in the pipeline. Watch this space!

Description: Monopropellant Hydrazine Thrusters.

Thrusters for satellites, spacecraft, space probes and launch vehicle attitude control.

General:

This 120N hydrazine thruster uses storable monopropellant N2H4. Thrust is produced by the decomposition of hydrazine as it passes through a catalyst bed.

Thrusters are designed for operation in both steady state and pulse mode operation over a wide pressure range and are thus ideal for propulsion systems operating in blow-down mode.

The combustion chamber and nozzle is manufactured from either platinum alloy. The thruster structure is also designed to serve as a heat shield for protecting the propellant valve and spacecraft structure.

Thrusters are equipped with an internally redundant catalyst bed heater and thermal insulation to guarantee optimum reproducible start-up conditions. The thrusters is qualified for multiple cold starts.

The thruster valves are dual seat/dual coil solenoid type. Both solenoids are mechanically and electrically decoupled from each other.

Propulsion Module

This hydrazine propulsion systems are supplied as self contained 'plug-in' propulsion modules. The module, comprises the complete propulsion system together with all of the associated sensors, heaters, thermistors, pressure transducers and harness elements.

The 'plug-in' propulsion module provides just two interfaces to the spacecraft:

•  A structural interface to the spacecraft.
•  A single electrical interface via connectors.

Hydrazine Rocket Thruster