초록 ▼

An arrangement for the supply of propellant for the propulsion systems of a satellite has a main fuel tank, a main oxidizer tank and an additional or auxiliary oxidizer tank. The auxiliary oxidizer tank becomes effective when the oxidizer in the main tank has been used up at the end of the useful li

An arrangement for the supply of propellant for the propulsion systems of a satellite has a main fuel tank, a main oxidizer tank and an additional or auxiliary oxidizer tank. The auxiliary oxidizer tank becomes effective when the oxidizer in the main tank has been used up at the end of the useful life of the satellite. At that time the additional oxidizer is used to bring the satellite into a retirement orbit out of the way, so to speak, to reduce the crowding in the range of desirable orbits. For this purpose, the emptiness of the main oxidizer tank is sensed by a sensor for providing a control signal which closes the main supply line, thereby switching on the auxiliary tank for propelling the satellite into the retirement orbit.

대표청구항 ▼

An apparatus for storing propellant for thruster means in a satellite, comprising a fuel tank (15a) having a capacity for holding fuel sufficient for all normal operations of said thruster means and for transporting said satellite to a retirement orbit when said normal operations are completed, firs

An apparatus for storing propellant for thruster means in a satellite, comprising a fuel tank (15a) having a capacity for holding fuel sufficient for all normal operations of said thruster means and for transporting said satellite to a retirement orbit when said normal operations are completed, first conduit means (15) connecting said fuel tank (15a) to said thruster means, a first oxidizer tank (1) having a capacity sufficient for said normal operations, second conduit means (3) connecting said first oxidizer tank to said thruster means, a second oxidizer tank (2) for holding an extra supply of oxidizer for transporting said satellite to said retirement orbit, third conduit means (4) including first and second conduit junctions connecting said second oxidizer tank in parallel to a portion of said second conduit means (3), whereby said first junction is upstream of said second oxidizer tank (2) and said second junction is downstream of said second oxidizer tank as viewed in an oxidizer flow direction from said first oxidizer tank (1) to said thruster means, controllable valve means (9) in said portion of said second conduit means (3), and gas bubble sensor means (7) in said second conduit means (3) between said first oxidizer tank (1) and said first junction for producing a control signal in response to said first oxidizer tank (1) being empty for closing said control valve means and for supplying oxidizer from said second oxidizer tank (2) to said thruster means to transport said satellite to said retirement orbit.