A hybrid softening strip for controlling stresses in a joint at low temperatures includes a layer of sacrificial material that can be tailored to fit the softening strip in the joint after the softening strip has been bonded to a structure.

A miniature satellite that uses a modified structural frame in order to store and disperse propulsion fuel efficiently. The modified structural frame includes a plurality of structural members. Each of the plurality of structural members includes a tubular body, a first endcap, a second endcap, an outlet port, and an inlet port. The first endcap and the second endcap are oppositely positioned within the tubular body. The first endcap and the second endcap are each perimetrically connected to the tubular body in order to delineate a fuel storage volume. The inlet port is positioned in between the first endcap and the second endcap and is mechanically integrated into the tubular body. The outlet port disperses propulsion fuel and is also mechanically integrated into the tubular body. The inlet port is in fluid communication with the outlet port through the tubular body. Additionally, the structural members are mounted amongst each other.

Systems and methods according to one or more embodiments are provided for providing a durable and thermally insulated duct network. A duct network may be provided by coupling two or more foam ducts to each other. In one example, a system includes a plurality of foam ducts and a plurality of foam bellows configured to couple the foam ducts to each other. The foam bellows include one or more bellow folds to allow an expansion and contraction of the foam ducts. A plurality of structural fastening systems couple the duct network to a structure of a vessel. The structural fastening systems allow for an axial movement of the duct network as the foam ducts expand and contract. Additional systems and methods are also provided.

A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion includes one or more recesses in a first surface of the peripheral portion.

An aerodynamic platform or spacecraft including a habitable 1G centripetal force rotating gravity producing interior corridor within an aerodynamic shell and an aerodynamic drone booster launch system with reentry and reuse capability.

The invention relates to a solid or liquid propellant (2) tank (1) for a thruster, the tank (1) comprising means for forming a gas (9) in the tank, the tank (1) having an opening (4) of surface area S for the extraction of a flow (20) of the propellant gas from the tank (1). According to the invention, the tank (1) comprises a propellant gas flow on-off control system comprising a grid (6) arranged opposite the opening (4) of the tank (1), a first thermal regulation system (11, 21) for heating the gas (9) in the tank and a second thermal regulation system (12, 22) for heating the grid (6), said grid (6) including holes of total surface area greater than the surface area S of the opening of the tank (1).

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.

This flexible thermal-control material (10A) is obtaining by stacking: a reflective layer (12) which reflects sunlight; and an infrared-ray emission layer (13) which emits infrared rays. The infrared-ray emission layer (13) is configured from a silicone material. Accordingly, a flexible thermal-control material is achieved which exhibits excellent optical characteristics such as solar absorption (?).

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

A system for controlling a distribution of propellant in a propellant tank assembly for a spacecraft comprises a body for containing the propellant, a plurality of thermal tomography elements, including a plurality of temperature-control elements and a plurality of temperature sensors, disposed around the body for detecting the distribution of the propellant inside the body; and a tomography element control module arranged to control the plurality of temperature-control elements to redistribute the propellant inside the propellant tank body by heating and/or cooling the propellant. In an embodiment, the propellant tank body includes a propellant management device inside the body and the tomography elements are disposed in proximity to the propellant management device. Tomography data can be obtained from the plurality of tomography elements, and a distribution of propellant within the propellant tank body can be determined based on the obtained tomography data.