A thruster system (20) includes a tank (24) for holding liquid propellant, a catalyst bed (26) connected with the tank (24) and operable to decompose the liquid propellant and generate a gas, a plenum (28) connected with the catalyst bed (26) for receiving...

The present patent application relates to a method, which uses real pressure, temperature and mass data obtained from real telemetry, to control the mixture ratio based on the change of the temperature set in its tanks, where, for the purposes of the prese...

Die Erfindung betrifft einen Raketenantrieb umfassend einen ersten Tank und einen zweiten Tank, wobei der erste Tank mit einem Brennstoff und der zweite Tank mit einem Oxidator, wie flüssigem Wasserstoffperoxid, zum Speisen mindestens eines vorzugsweise w...

The system has a gas volume varying device for varying volume of gas in a propellant supplying circuit (4). The gas volume varying device comprises a hydraulic accumulator (8) having variable level of liquid. The accumulator includes a gas supply point and...

The low thrust cryotechnic propulsion module has a principal propulsion unit (10) and secondary propulsion unit (21,22) controlling altitude. There are two sets of reservoirs (31 to 34) of cryogenic feed, controlled by intermittent pressure controls (71,72...