A feed assembly supplies polysilicon to a growth chamber for growing a crystal ingot from a melt. An example system includes a housing having support rails for receiving one of a granular tray and a chunk tray and a feed material reservoir positioned above the support rails to selectively feed one of either the granular tray or the chunk tray. A valve mechanism and pulse vibrator are also disclosed.

Example aspects of a deployed electromagnetic radiation deflector shield and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The deployed electromagnetic radiation deflector shield can comprise a power supply; and an electromagnet configured to generate a magnetic field to deflect radiation; wherein the deployed electromagnetic radiation deflector shield is deployed at a distance away from one of a spacecraft and a base station to minimize an effect of the magnetic field on the one of the spacecraft and base station.

An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.

A feed assembly supplies polysilicon to a growth chamber for growing a crystal ingot from a melt. An example system includes a housing having support rails for receiving one of a granular tray and a chunk tray and a feed material reservoir positioned above the support rails to selectively feed one of either the granular tray or the chunk tray. A valve mechanism and pulse vibrator are also disclosed.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

A tether for joining objects in space by centripetal force has a modular architecture. The modular architecture facilitates the deployment of the tether by facilitating its transport into space as unassembled modular components and its assembly in situ, after the components have been transported. The modular architecture also facilitates it repair, modification, and disassembly in situ. More particularly, the modular tether has design features that enable its assembly, repair, modification, and/or disassembly in situ while the modular tether remains under tension, i.e., while the modular tether continues to perform its function of joining two or more objects by the application of centripetal force. The modular architecture also enables new tether modalities, e.g., a tensile strength modality, a winch modality, a tension monitoring modality, a repair state modality, a situational awareness modality, and a temperature control modality.

A global warming or cooling mitigation and solar energy system, comprising tethered pairs of reflecting mirror systems of similar or identical size, situated at approximately Lagrange Point One between the Earth and the Sun; a first, Sun facing mirror system reflects radiation to a second, Earth or near Earth facing mirror system, the second mirror system targets the radiation to solar panels, other targets for purposes such as weather management, or to a third mirror system in a geosynchronous orbit, which in turn can target solar panels on Earth during night time. Because only one of the two tethered mirror systems is sending radiation to Earth, the result is typically a 50% reduction of total energy reaching the Earth from, as measured by the surface area of the two mirrors; this causes global cooling. Because electrical energy can be generated from the invention, it is anticipated the invention can be practiced on a for profit basis, with global warming mitigation an automatic public benefit. The invention further comprises non-reflective, global cooling elements, which serve only to block radiation from the Sun. The tethered pairs of mirrors have ion engines for maneuvering and positioning, such that they can be positioned with minimal energy required on the approximate orbital path of Lagrange Point one, but far enough off to the side to intercept solar radiation that would have otherwise missed the Earth, thus they can be used to either increase or decrease global warming; in effect the invention can function as a giant Earth thermostat. Further applications, variations and anticipated benefits are detailed.

Circular mass accelerators for off-world applications are disclosed herein. An example system includes a base assembly that is configured to interface with a supporting surface, a vertical support assembly extending from the base assembly, a first drive positioned, a shaft connected to the first drive, a hub assembly having a spool, the hub assembly being coupled to a second drive that is located on a terminal end of the shaft, a first tether and a second tether that can be spooled onto and unspooled from the spool by the second drive, and payloads positioned each of the tethers, the payloads being releasably coupled to tethers in such a way that the payloads can be released upon the payloads being rotated to a target launch velocity.

A space-debris capturing device includes a harpoon driven into target debris as space debris to be removed. The harpoon includes a first harpoon part having a large diameter, and a second harpoon part having a diameter smaller than the diameter of the first harpoon part and protruding from a leading surface in the direction of the drive of the first harpoon part into the target debris.

A debris removal device includes: an end mass adapted to approach debris to be removed; a debris capture device separably-mounted on the end mass; and a tether connecting the debris capture device and the end mass to each other. The debris capture device includes a harpoon adapted to penetrate into the debris, a shooting device adapted to shoot the harpoon, a guide member positioned to come into contact with the surface of the debris to adjust the shooting angle of the harpoon with respect to the surface of the debris, and a switch that sends the shooting signal to the shooting device. When the harpoon is penetrated into the debris, the end mass is separated from the debris capture device, and the tether is released into outer space.