Systems and methods for a multimode propulsion system (MMPS) are presented. The MMPS includes a chemical thruster, an electric thruster, and a shared propellant tank. The MMPS further includes a propellant decomposition chamber that transforms, via a catalytic and/or electrolytic process, the propellant from the tank into vapor form for use as gas propellant by the electric thruster. The electric thruster can be configured for targeted ionization of one or more constituent species present in the vapor form of the propellant. Flow activation/control from the tank to the chemical and electric thrusters is provided by a fluidic feed system. The branches include a check valve and a pressure regulator in series connection. A normally closed squib valve prevents propellant flows/leaks from the tank to either the chemical or the electric thrusters when the MMPS is not in operation.

A device for thermally insulating a piece of equipment, the device including a block of thermal insulation having at least a first hole; a deformable cover made of a gastight material and surrounding the block of insulation so that the wall of the first hole is covered by the gastight cover while leaving open the ends of first hole, the cover defining, at the second end, a first opening that communicates with the first hole and a second opening that communicates with the space situated between the insulating block and the cover; and the first and second openings of the cover being closed in gastight manner with the inside of the cover under a partial vacuum.

The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one first heat exchanger (18) suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.

This disclosure includes a hybrid magneto-active membrane, which can be used as part of a Magneto-active Propellant Management Device (MAPMD), to actively control free surface effects of liquid materials, such as fuels, and to reduce fuel slosh. The disclosed MAPMD merges aspects of a diaphragm membrane with a magneto-active inlay to control the membrane during in-flight conditions.

This disclosure provides a system for damping slosh of a liquid within a tank, a baffle for use in the system, and a method of damping slosh using the system. The system includes a plurality of baffles. Each baffle has a body configured to substantially float upon the liquid. Each baffle also has an activation material received along at least a portion of the body. The activation material is magnetically reactive provided in a quantity sufficient to enable the body to be manipulated in the presence of a magnetic field (M). The system further includes an actuator configured to provide the magnetic field (M).

A system and method for shedding redundant launcher tank mass, comprising progressing means, and cutting means configured to cut redundant propellant tank wall, the system configured to progress inside the tank, along the tank wall in an initially predetermined rate.

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.

An antivortex device for use in suppressing formation of a vortex created by fluid flowing through multiple outlet ports defined in a sump is provided. The antivortex device includes a plurality of center plates extending through a central axis of the sump, an extension plate substantially aligned with one of the plurality of center plates and extending substantially radially outward from the central axis, and a top plate coupled to the plurality of center plates.

The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.

To provide a propellant tank such as a fuel tank and an oxidant tank for a spacecraft, the propellant tank discharging propellant such as liquid hydrogen and liquid oxygen accumulated therein toward a rocket engine by pressurizing an inside thereof by operating gas. The propellant tank includes a tank body that accumulates therein the propellant in a liquid state, and a holding container that is provided inside the tank body and disposed with a predetermined gap from an inner wall of the tank body, so that the propellant in a liquid state can be held therein, when the inside of the tank body is in a microgravity state or a zero-gravity state.