Cell-based space systems with nested-ring structures that interlock and can change configuration to support a mission are provided. The cells may self-assemble into a larger structure to carry out a mission. Multiple rotatable rings may be included in a cell, with a payload/control section in the center. The rings may provide power and/or data to trams that move about the rails. Trams may interlock with other cells, carry sensors or other devices, etc. Cells may be stowed in a cell stack that is deployable. Such cell-based systems may have various applications in space, on Earth, other celestial bodies, and underwater.

A fuel tank for use with a spacecraft, the fuel tank being configured to store therein fuel for driving the spacecraft, includes a carbon fiber reinforced plastic layer and a metallic plating layer, the carbon fiber reinforced plastic layer has a polished surface having been subjected to polishing processing, the polished surface being on an inner side of the fuel tank, and the metallic plating layer is provided on the polished surface.

A formation assembly for use in manufacturing a reinforced insulation panel including a foam material and a reinforcing structure includes a back plate including a first surface configured to receive the foam material, and a first support sheet spaced from the first surface to form a gap therebetween, wherein the first support sheet supports the reinforcing structure. The formation assembly also includes a second support sheet spaced from the first support sheet, wherein the second support sheet defines an upper boundary of the reinforced insulation panel. A rigid structure is coupled to the second support sheet, wherein the rigid structure restricts movement of the reinforced insulation panel.

A composite wall assembly edge joint including a first composite buildup pad having a first tapered section is secured to and extends along a first composite face sheet. A second composite buildup pad having a second tapered section is secured to and extends along a second composite face sheet, wherein the first and second composite buildup pads are positioned between spaced apart first and second composite face sheets. A composite flute core member includes a tapered first portion positioned between and secured to the first tapered section and to the second tapered section. A second portion of the composite flute core member extends in a direction away from the tapered first portion of the composite flute core member and is positioned between, extends along and is secured to the first and second composite face sheets.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes means to use an electric propulsion system coupled to a frame of a spacecraft, the electric propulsion system including at least a first thruster and a second thruster, the first thruster adjacent a first side of the frame, the second thruster adjacent a second side of the frame, and means to allow at least one of the first thruster or the second thruster to control the spacecraft without using a chemical propulsion system.

A system for managing propellant and pressurant for in-space propulsion of a spacecraft is provided. The system includes a conformal fuel tank having an ullage operatively connected for pressurization and a propellant management device (PMD) to wick propellant to a liquid port of the conformal fuel tank. The system further includes a pneumatic circuit including a tank pressurant vent valve for adjustment of operating pressure prior to refueling operations; a vent to release excess pressurant; a pressurant metering vent valve to provide control and safety relief for the pressurant; a check valve to prevent backflow; a pressurant cat bed for decomposing propellant into pressurant; a repressurizing valve to release pressurant once cooled; a burst disk to provide overpressure safety relief; a series of propellant extraction valves to intake a predetermined quantity of propellant for decomposition; and a pressure regulator that delivers proper pressure to a series of thrusters.

A composite tank for a reusable launch vehicle comprises a composite wall, having a first coefficient of thermal expansion. The composite wall comprises a first end, a second end, a central axis, which passes through the first end and through the second end, and a cylindrical interior surface. The composite tank also comprises slosh baffles, formed from a second material, having a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. Each of the slosh baffles is attached to the cylindrical interior surface of the composite wall. Each of the slosh baffles is annular and is separated from the cylindrical interior surface of the composite wall by a radial gap, selected, in part, based on a difference between the first coefficient of thermal expansion and the second coefficient of thermal expansion. The radial gap is configured to change responsive to changes in temperature of the composite tank.

A system for fluid management in low or micro gravity environment, the system including: a two-phase gas-liquid tank suitable for storage of a two-phase gas-liquid, the two-phase gas-liquid tank including an outer surface, an inner cavity, and an outlet between the inner cavity and the outer surface. The system further includes a thermal or electromagnetic device disposed on or proximal to the two-phase gas-liquid tank. The system further includes a controller operatively coupled to the thermal or electromagnetic device, the controller being configured to energize the thermal or electromagnetic device in a controlled manner (i) to generate a thermal or electromagnetic gradient heat in the two-phase gas-liquid and (ii) urge a portion of the two-phase gas-liquid to the outlet of the two-phase gas-liquid tank.

Provided is a composite inner frame multi-bonded barrel, a shell-integrated projectile propellant tank including the same, and a method for manufacturing the barrel and the tank. The shell-integrated projectile propellant tank may include the composite inner frame multi-bonded barrel including a cylinder portion including a plurality of inner frames bonded together; a dome portion including an upper dome frame and a lower dome frame bonded to an upper end and a lower end of the cylinder portion, respectively; a cylindrical shell coated on an outside of the composite inner frame multi-bonded barrel; and at least one manhole cover sealing a manhole cover coupling hole formed in a center of the upper dome frame or the lower door frame, and the at least one manhole cover has a fluid injection port formed on one side thereof.

A metallic positive expulsion fuel tank with stress free weld seams may include a first hemispherical shell with a first edge; a pressurized gas inlet attached to the first hemispherical shell; and a metallic cylinder with first and second edges attached to the first hemispherical shell along matching first edges by a first weld seam. The tank may also include a second hemispherical shell with a first edge attached to a fuel outlet fixture. An elastomeric diaphragm may be attached to the fuel outlet fixture on the second hemispherical shell. The second hemispherical shell may be attached to the second edge of the metallic cylinder along matching edges by a second weld seam thereby forming a positive expulsion fuel tank with two interior chambers separated by the elastomeric diaphragm. The first and second weld seams may be subjected to a localized post-weld stress relief heat treatment in which heating of the tank is confined to a distance of 2 inches (5.08 cm) of the first weld seam and a distance of 2 inches (5.08 cm) of the second weld seam such that the stresses in the first and second weld seams are relieved and the elastomeric diaphragm is unaffected by the heat treatment.