A device for mounting and supporting a generally cylindrical or tapered tank, having a main axis X, that includes a pair of first retaining rods for retaining the tank along a vertical axis Z on each of a first and second end of the tank, a second retaining rod for retaining the tank along a horizontal axis Y, perpendicular to the main axis, on the first end of the tank, and a third retaining rod for retaining in a ball-and-socket joint, the means being located around the vertical axis and connected to the second end of the tank.

Apparatus, computer-readable medium, and method for calculating a mass of propellant in a propellant storage volume. A density of the propellant is calculated based on a detected pressure and temperature of the propellant and actual thermodynamic properties of the propellant. A volume of the propellant storage volume is calculated based on a measured nominal volume and changes to the nominal volume based on pressure. The mass of the propellant is calculated by multiplying the calculated volume of the propellant storage volume by the calculated density of the propellant in the propellant storage volume.

A roll control thruster controls the attitude of a launch vehicle by using the oxidizer filled in an oxidizer tank, and includes: a thruster tank that is charged using a portion of the oxidizer stored in the oxidizer tank; a thruster line that is branched from the thruster tank and forms a supply path of the oxidizer stored in the thruster tank; a thruster valve that is provided in the thruster line and opens and closes the thruster line or adjusts the opening degree of the thruster line; a thruster module that is connected to the thruster line and injects the oxidizer, supplied via the thruster line, in order to control the attitude of the launch vehicle; and a thruster control module that controls the operation of the thruster valve and the supply of oxidizer to the thruster module.

Aerospace systems, and systems and methods for assembling an aerospace system or another system or structure, are disclosed. A representative system can include a propellant tank with a dome-shaped head; attachment features on the dome-shaped head; and a thrust structure with legs attached to the attachment features. A representative method can include forming shims to be positioned between the legs and the attachment features. The shims can be formed based on digital characterizations of mounting faces on the attachment features within a reference coordinate system. The method can include positioning a drill jig within the reference coordinate system and using the drill jig to make holes in the shims and/or the attachment features for fastening the legs to the attachment features. A drill jig can include plates that are movable relative to each other. At least one of the plates can include a mounting hole pattern.

A fuel depot in space is provided. The fuel depot has a collapsible housing with a guidance, navigation, and control (GNC) system, a power management system, and a reaction control system (RNC). Connected to the housing are a plurality of fuel tanks that are connected via collapsible rods. The fuel tanks have pipe systems that are in communication with a plurality of pumps to transfer fuel from the tanks through a refueling arm and into a spacecraft during refueling.

Apparatus, computer-readable medium, and method for calculating a mass of propellant in a propellant storage volume. A density of the propellant is calculated based on a detected pressure and temperature of the propellant and actual thermodynamic properties of the propellant. A volume of the propellant storage volume is calculated based on a measured nominal volume and changes to the nominal volume based on pressure. The mass of the propellant is calculated by multiplying the calculated volume of the propellant storage volume by the calculated density of the propellant in the propellant storage volume.

A three-point propulsion system of an orbital deployment space module for at least one satellite including: chassis including exactly three first housings shaped to each receive a propulsion unit and at least one second housing shaped to receive a tank, at least one liquid fuel tank disposed in a second housing, and exactly three propulsion units, each propulsion unit being disposed in one of the first housings, and each propulsion unit including at least one thruster.

A three-point propulsion system of an orbital deployment space module for at least one satellite including: chassis including exactly three first housings shaped to each receive a propulsion unit and at least one second housing shaped to receive a tank, at least one liquid fuel tank disposed in a second housing, and exactly three propulsion units, each propulsion unit being disposed in one of the first housings, and each propulsion unit including at least one thruster.

Aerospace systems, and systems and methods for assembling an aerospace system or another system or structure, are disclosed. A representative system can include a propellant tank with a dome-shaped head; attachment features on the dome-shaped head; and a thrust structure with legs attached to the attachment features. A representative method can include forming shims to be positioned between the legs and the attachment features. The shims can be formed based on digital characterizations of mounting faces on the attachment features within a reference coordinate system. The method can include positioning a drill jig within the reference coordinate system and using the drill jig to make holes in the shims and/or the attachment features for fastening the legs to the attachment features. A drill jig can include plates that are movable relative to each other. At least one of the plates can include a mounting hole pattern.

A reservoir assembly for a rocket engine of a spacecraft includes a first reservoir defining a first inner volume, a second reservoir having walls defining a second inner volume and comprising first walls fixed to the first reservoir, and an elastic membrane delimiting the second inner volume from the first inner volume, wherein the second reservoir comprises an outlet to allow a liquid propellant to flow out toward a propulsion apparatus of the rocket engine, characterized in that it further comprises a connecting means coupled to the first and second reservoirs and adapted to connect the first and second reservoirs.