Rocket Engine using Hydrogen Peroxide
The 400N Liquid Rocket Motor (LRM) is a small rocket engine for apogee orbit injection of geo-stationery satellites and for trajectory and orbital manoeuvres on high orbital altitudes.
The Hydrogen Pereoxide/Ethanol-propellant engine – Apogee Orbital Manoeuvring Propulsion, AOMP - uses the storable ‘green’ propellant as fuel and oxidizer. It is designed for long term steady state operation. It operates in a wide pressure range at regulated pressure mode.
The combustion chamber and the nozzle are made of a Niobium alloy. That does not require surface coating, thereby allowing operational wall temperatures up to 1,800°C and thus maximum engine performance.
The uncoated surface is absolutely resistant against oxidization and thus invulnerable to mishandling, by application of sensors or by pulse cycles.
The main criterion for selecting the adequate model for a specific application is the available volume in the spacecraft for accommodating the engine.