초록 ▼

The invention relates to a device for pressurizing a standardized two-liquid propulsion system of a geostationary satellite comprising a high pressure helium storage unit (10) having at least one helium storage tank, a regulating unit (11) and a pressurizing unit for propellant tanks (17, 18) interc

The invention relates to a device for pressurizing a standardized two-liquid propulsion system of a geostationary satellite comprising a high pressure helium storage unit (10) having at least one helium storage tank, a regulating unit (11) and a pressurizing unit for propellant tanks (17, 18) interconnected by a pressurizing circuit, wherein the regulating unit is an electronic regulating unit comprising at least one electrovalve (51), positioned at a location of the pressurizing circuit and controlled by a processing and control circuit (54), which receives informations from pressure sensors (43, 47, 48) associated with the different tanks, said processing and control circuit permitting a constant pressure pressurization of the propellant tanks (17, 18) by flow lines including a combination of pyrotechnic valves, filter elements and calibrated leak elements during the satellite transfer and placing in position phase and a measurement of the residual propellant quantity during the orbital life phase of the satellite so as to predict satellite End of Life to within 2 months out of a 15 year mission.

대표청구항 ▼

[ We claim:] [1.] Device for pressurizing a standardized two-liquid propulsion system of a geostationary satellite comprising a high pressure helium storage unit having at least one helium storage tank; a pressurizing unit including propellant tanks; an electronic regulating unit interconnected to t

[ We claim:] [1.] Device for pressurizing a standardized two-liquid propulsion system of a geostationary satellite comprising a high pressure helium storage unit having at least one helium storage tank; a pressurizing unit including propellant tanks; an electronic regulating unit interconnected to the propellant tanks by a pressurizing circuit and including at least one electrovalve coupled with a calibrated orifice, the regulating unit being positioned such that the electrovalve and calibrated orifice are between the high pressure unit and the propellant tanks; and a processing and control circuit controlling the electrovalve, the processing and control circuit receiving information from pressure sensors associated with the helium storage tank and the propellant tanks and providing a regulated pressure in the propellant tanks during a transfer orbit of the satellite and repressurization of the propellant tanks at any time during an orbit life of the satellite.