Certain embodiments of the inventive technology may be described as apparatus for melting and reshaping metal from a first shape into a second shape in a microgravity or zero gravity environment, such as a space foundry, where such apparatus includes feedstock input componentry (5) configured to accept conductive metal feedstock (7) having the first shape, a furnace and a furnace pre-stage (22) established upflow of the furnace, a plurality of electromagnetic field generators (10), each of which is configured to generate an electromagnetic field, to, e.g., steer, melt and/or move the metal, whether melt or otherwise, and casting componentry (15) configured to reshape molten metal to the second shape. Certain embodiments may achieve a high degree of control over electromagnetic fields by offering individual adjustment of one or more electrical parameters of the electromagnetic field generators (10).

An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.

An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.

An object is to notify an appropriate intrusion alert by determining whether debris will intrude into an orbit area of a satellite constellation. A passage determination unit (110) determines whether debris will pass through a satellite orbit area, based on satellite orbit forecast information in which a forecast value of an orbit of a satellite is set and debris orbit forecast information in which a forecast value of an orbit of debris is set. When it is determined that debris will pass through the satellite orbit area, an alert generation unit (120) generates an intrusion alert (111) including a predicted time, predicted location coordinates, and predicted velocity vector information that relate to passage of the debris. An alert notification unit (130) notifies the intrusion alert (111) to a management business device (40) used by a management business operator that manages a satellite that flies in the satellite orbit area.

Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

A spectrographic system includes a space-borne spectrometer in communication with a ground-based processor. The space-borne spectrometer may include an interferometer, a detector array downstream from the interferometer, and a spectrometer controller configured to cooperate with the detector array to collect Fourier Transform Spectral (FTS) data, generate Principle Component Analysis (PCA) scores from the collected FTS data, generate an approximate interferogram based upon the PCA scores and the collected FTS data, generate residuals based upon the approximate interferogram, and generate compressed FTS data based upon the PCA scores and residuals to be sent to the ground-based processor.

A tethered uni-rotor network of satellite vehicles, is made up of a central hub with multiple tethers radiating outward in a hub-and-spoke arrangement. Each tether attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a persistent state of rotation, driven by the propulsion units on each satellite vehicle, so the airfoils generate lift which supports each satellite vehicle and a distributed portion of the weight of the central hub. As the system rotates, centrifugal forces pull each satellite vehicle outwards, which keeps each tether taught and applies tension across each of the lifting surfaces, thereby alleviating the bending moment common to fixed-wing aircraft. This approach reduces the weight within the structural members, utilizes higher aspect ratio wings to reduce induced drag, and employs thin-thickness high-camber airfoil profiles which achieve higher lift-to-drag ratios than standard practice.

A tethered uni-rotor network of satellite vehicles, is made up of a central hub with multiple tethers radiating outward in a hub-and-spoke arrangement. Each tether attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a persistent state of rotation, driven by the propulsion units on each satellite vehicle, so the airfoils generate lift which supports each satellite vehicle and a distributed portion of the weight of the central hub. As the system rotates, centrifugal forces pull each satellite vehicle outwards, which keeps each tether taught and applies tension across each of the lifting surfaces, thereby alleviating the bending moment common to fixed-wing aircraft. This approach reduces the weight within the structural members, utilizes higher aspect ratio wings to reduce induced drag, and employs thin-thickness high-camber airfoil profiles which achieve higher lift-to-drag ratios than standard practice.

ThermaSat™ propulsion system uses water as a safe and non-explosive propellant, and which is unpressurized at liftoff. Utilizing solar thermal propulsion, the compact and efficient capacitor heats water to steam to produce high thrust and total impulse. The advanced optical system allows for the thermal capacitor to charge through solar power alone with no protruding concentrators or power draw from the main bus. Additional solar panels, body mounted to the ThermaSat, provide auxiliary heating of the thermal capacitor when not directly incident to sunlight to promote non-sun pointing operations.