Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

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 deployable electromagnetic radiation deflector shield (DERDS) is disclosed. It is used in protecting manned spacecraft or robotic spacecraft flying outside of the Earth's protective magnetic field as well as manned extra-planetary base stations. This DERDS is deployed from the spacecraft during flight and positioned to be between the Sun and the protected spacecraft (or in the case of Jupiter/Saturn missions, transitioning to be between that planet and the spacecraft). It remains in the proper position from the spacecraft by its own sensors and computer controlled gaseous or ion thrusters. It is deployed away from the spacecraft to better deflect incoming solar radiation (or Jovian radiation and the like), and not have its magnetic field affect the protected spacecraft or extra-planetary base station's equipment and astronauts (as in prior art). Its deployment will also prevent any captured radiation in its generated magnetic torus (like Earth's Van Allen radiation belts) from affecting the protected spacecraft or extra-planetary base station. The DERDS has a self-contained superconducting electromagnet that creates a magnetic field to deflect incoming solar radiation, including CMEs (coronal mass ejections) and repositioned for x-ray and gamma ray bursts from distant supernovae. It utilizes a tethered umbilical cord to transmit electrical power and back up commands from the spacecraft or satellite. Another variant or embodiment would be to mount the DERDS on a telescopic/extendable solid mount and remove the need for thrusters within the DERDS as it would move as an attachment to the spacecraft. The source of electrical power in this embodiment is the protected spacecraft's solar arrays, RTG (radioisotope thermal generator), fuel cells, and or batteries. In addition, it can be constructed with these power supplies mounted within the DERDS, as in a self-contained deployed spacecraft/satellite. Another embodiment of the DERDS would be mounted on an ecliptic track wherein the DERDS moves along the track to protect the manned base station.

A system and method for assisted EVA self-return is provided herein. The system estimates a crewmember's navigation state relative to a fixed location, for example on an accompanying orbiting spacecraft, and computes a guidance trajectory for returning the crewmember to that fixed location. The system may account for safety and clearance requirements while computing the guidance trajectory. According to at least one embodiment, the system actuates the crewmember's safety jetpack to follow the prescribed trajectory to the fixed location.

A system and method for assisted EVA self-return is provided herein. The system estimates a crewmember's navigation state relative to a fixed location, for example on an accompanying orbiting spacecraft, and computes a guidance trajectory for returning the crewmember to that fixed location. The system may account for safety and clearance requirements while computing the guidance trajectory. According to at least one embodiment, the system provides a directional cue (e.g., a visual, auditory, or tactile cue) to a crewmember corresponding to the prescribed trajectory back to the fixed location. The system may be activated by the crewmember or remotely by another crewmember and/or system.

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 radar satellite of the present invention comprises a radar unit including a plurality of radar panels coupled to each other in a single flat plate shape, each of the plurality of radar panels including a plurality of antennas which transmit and receive radar waves, and a solar cell; and a communication/control unit which performs communications with a spot on an earth or a spacecraft. The radar unit includes: a radar panel array which is a plate-shaped structure including the plurality of radar panels; and a deployable truss structure including a plurality of side frame members supporting the plurality of radar panels, respectively, and coupled to each other in such a manner that the side frame members are foldable and deployable.

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.

A system and method for assisted EVA self-return is provided herein. The system estimates a crewmember's navigation state relative to a fixed location, for example on an accompanying orbiting spacecraft, and computes a guidance trajectory for returning the crewmember to that fixed location. The system may account for safety and clearance requirements while computing the guidance trajectory. According to at least one embodiment, the system actuates the crewmember's safety jetpack to follow the prescribed trajectory to the fixed location. In another embodiment, the system provides the crewmember with a directional cue (e.g., a visual, auditory, or tactile cue) corresponding to the prescribed trajectory back to the fixed location. The system may be activated by the crewmember or remotely by another crewmember and/or system.

Systems, devices, and methods for precision boom deployment are provided in accordance with various embodiments. The tools and techniques provided may have space and/or terrestrial applications. Some embodiments include a boom deployment system that may include a furlable boom. Some embodiments include: boom reinforcement devices, end fitting devices, contoured support devices, edge support devices, spiral harness devices, latch devices, combined boom spool and tension drive devices, and/or rotary encoder devices. Some embodiments may utilize a composite slit-tube boom. Some embodiments utilize a furlable boom that may be fabricated with curvature along its length.