Maxar Space LLC

Giovanni Lenguito

Jason Esquivias

Ashton Murphy

A satellite propellant tank includes a tank body and a dome attached to the tank body to enclose an interior volume for propellant storage. One or more cavities are formed in the dome. One or more propellant control components are located in the one or more cavities formed in the dome.

Satellite propellant tank with integrated regulation

An example of an apparatus includes an inlet to connect to a propellant source a pressure regulator connected to the inlet to reduce propellant pressure from a first pressure at the inlet to a second pressure. The apparatus includes a manifold connected to the pressure regulator to receive propellant from the pressure regulator at the second pressure and includes a plurality of manifold outlets. The apparatus further includes a plurality of gas lines, each gas line extending from a corresponding manifold outlet for connection to a corresponding satellite propellant tank.

Spacecraft propellant loading system

Described herein is a power processing unit (PPU) for use with a Hall Effect Thruster (HET) and a Propellant Management Assembly (PMA) of a spacecraft. The PPU comprises an anode and ignitor supply subsystem that provides anode and ignitor signals to an anode and an ignitor circuit of the HET. The PPU also comprises a valve control subsystem that provides valve control signal(s) to valve(s) of the PMA. The anode and ignitor supply subsystem and the valve control subsystem are each coupled to a low voltage (LV) bus of an electrical power subsystem of the spacecraft. The anode and ignitor supply subsystem includes a step-up DC-DC converter having a transformer that steps-up a voltage of the LV bus to a higher voltage used to produce the anode and ignitor signals. The valve control subsystem is devoid of a transformer. An Electric Propulsion System (EPS) includes the PPU, HET and PMA.

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New York, NY, United States of America

Giovanni Lenguito