A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.

A propellant tank can be used with a launch vehicle and can include at least one ring baffle having corrugated surfaces which are aligned circumferentially with respect to a longitudinal axis of the propellant tank. Folds of the corrugated surfaces may rise and fall in a first direction which is along the longitudinal axis. The ring baffle may be on an interior circumference of the propellant tank and the corrugated surfaces can extend in a second direction which is along a lateral axis of the propellant tank. Further, the ring baffle is of a predetermined width from the interior circumference of the propellant tank and can address slosh in a propellant used therein.

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.

The invention concerns a spacecraft propellant tank designed for storing and supplying fuel to the propulsion system, as well as its application method, which is related to space technology and particularly to the design of tanks for storing liquid propellants within rocket engines. The tank in question comprises a body featuring at least one convex edge that creates a corner capillary and an intake port positioned on one of these convex edges. Additionally, the tank's interior surface is treated to be hydrophilic. The objective of this invention is to develop a spacecraft propellant tank characterized by its lightweight and straightforward design. It facilitates the creation of various propellant tank shapes while minimizing the quantity of internal components that reduce useful volume. It also ensures consistent and reliable functionality of the propellant system with continuous supply of propellant to the intake port, even in the absence of gravity and during multiple activations of the propulsion system. The claimed invention achieves its objective by implementing technical results that include enhancing the efficiency of propellant supply within the tank to the intake port, improving reliability, augmenting the useful internal volume, and offering a variety of tank shapes. The stated objectives are met in particular through the hydrophilic properties of the propellant tank's inner surface, the design of the propellant tank shape featuring at least one convex edge that forms a corner capillary, and positioning of the intake port on one of the convex edges that forms the corner capillary. The application method for the spacecraft propellant tank involves initially filling the tank with liquid propellant and pressurizing gas through the intake port prior to spacecraft launch. Subsequently, once the spacecraft is in orbit, propellant is conveyed from the tank to the propulsion system through the intake port. The movement of liquid propellant towards the intake port is facilitated by the pressure of the pressurizing gas and a localized pressure reduction generated during propellant discharge. This reduction occurs in the corner capillary near the intake port relative to the pressure of the propellant in other sections of at least one corner capillary, thus establishing a flow of propellant through the corner capillaries towards the intake port area.

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 pressurization method for increasing a pressure within a propellant tank containing hydrogen peroxide H.sub.2O.sub.2. The pressurization method includes irradiating at least some of the hydrogen peroxide H.sub.2O.sub.2 with ultraviolet light emitted by at least one ultraviolet light source. With the UV light, a photolysis is actively provoked which causes the irradiated hydrogen peroxide H.sub.2O.sub.2 to at least partially decompose into water H.sub.2O and gaseous oxygen O.sub.2. Also a filling method for at least partially filling a receiving propellant tank with the pressurization method, a tank assembly, a filling system, and a spacecraft.

A diaphragm for use in a fluid storage tank in which the fluid storage tank comprises first and second shell portions defining an interior tank space, wherein the diaphragm is configured to be secured within the interior tank space between the first and second shell portions, to define a fluid storage reservoir between the diaphragm and one of the shell portions. The diaphragm comprises a body of deformable material having a part-spherical portion defining a central longitudinal axis. A thickness of the diaphragm varies between different regions of the diaphragm. The thickness of the diaphragm is asymmetric about the longitudinal axis. Also provided is a fluid storage tank including such a diaphragm.

A space electric propulsion system and a xenon filling method therefor are provided, suitable for a filling process of an electric propulsion system using high-purity xenon as a working medium. By reasonably designing a filling process, the precision of a xenon filling amount is ensured, and xenon filling can be performed without weighing the whole spacecraft. This method features a simple and efficient filling device, short preparation time, precise and controllable filling process, as well as safety and convenience, which can effectively meet the requirements for a high-purity xenon rapid filling task of a satellite.

A semi-ellipsoidal, semi-toroidal, or toroidal shell includes an annular sheet metal wall that is longitudinally segmented so as to include a plurality of annular wall segments. Each of the plurality of annular wall segments is joined to an adjacent wall segment by a respective latitudinal wall weld. Also disclosed is a tank including the shell, a vehicle including the shell, a multi-conic preform used to manufacture the shell, a method for assembling the preform, and a method for manufacturing the shell using the preform.

Provided is a liquid tank, including: a cylindrical seamless tank body having both end portions being reduced in diameter toward respective end sides; and a plurality of annular baffles provided inside the tank body and arranged at intervals in an axial direction of the tank body, in which at least one of the plurality of baffles is held on an inner peripheral surface of the tank body.