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.

Example aspects of a deployed electromagnetic radiation deflector shield assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The deployed electromagnetic radiation deflector shield assembly can comprise a base station on a ground surface; a deployed electromagnetic radiation deflector shield comprising an electromagnet configured to generate a magnetic field configured to deflect radiation from a radiation source; and an upright supporting the deployed electromagnetic radiation deflector shield at a distance away from the base station, and wherein the distance is configured to prevent the magnetic field from interfering with the base station.

[Object] To provide a tether that is automatically deformed from a deployment state in case of cutting or the like.

[Solving Means] A tether 10 is a net that kinks and is automatically deformed upon tension release. The tether 10 has a length of several kilometers to several tens of kilometers upon deployment and is capable of shrinking to have a length of approximately several tens of meters to several hundreds of meters by kinking and automatically being deformed when the tension is released because of cutting or the like.

Example aspects of an assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The assembly can comprise a deployable deployed electromagnetic radiation deflector shield comprising: a power supply; and an electromagnet configured to generate a magnetic field to deflect radiation; and a spacecraft, wherein the deployed electromagnetic radiation deflector shield is unattached to the spacecraft when deployed from the spacecraft, wherein the deployed electromagnetic radiation deflector shield is deployed at a distance away from the spacecraft, and wherein the distance is configured to prevent the magnetic field generated by the electromagnet from interfering with the spacecraft.

A system for imparting linear momentum transfer may include a catching mechanism of a target space vehicle and a tether that is configured to impart a linear momentum transfer from the tether to the target space vehicle. The tether may be fixedly or detachably connected to a Kinetic Energy Storage and Transfer (KEST) vehicle that maneuvers and potentially retrieves the tether. Alternatively, the tether may be separate from the KEST vehicle and may be retrieved by a suitable retrieving mechanism, such as a robotic arm.

A vehicle, such as a satellite or other spacecraft, includes an electrodynamic tether connected thereto. A processor, contained within the vehicle and connected to the electrodynamic tether, is configured to cause a current to be directed to the electrodynamic tether to cause a change in motion of the vehicle. Sensors, such as an attitude sensor, a position sensor, a magnetometer, and an ionosphere sensor, are contained within the vehicle and are connected to the processor. The processor is configured to direct current to the electrodynamic tether based upon input received from the sensors to maintain the vehicle within a specified orbit, such as a highly-inclined eccentric orbit over the polar or other high-latitude region, or to change the vehicle's orbit. The processor may be configured in a closed-loop configuration to account for measured errors by the sensors position, attitude, ionospheric charge density, and/or the Earth's magnetic field.

Example aspects of a deployed electromagnetic radiation deflector shield assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The deployed electromagnetic radiation deflector shield assembly can comprise a base station on a ground surface; a deployed electromagnetic radiation deflector shield comprising an electromagnet configured to generate a magnetic field configured to deflect radiation from a radiation source; and an upright supporting the deployed electromagnetic radiation deflector shield at a distance away from the base station, and wherein the distance is configured to prevent the magnetic field from interfering with the base station.

A craft having a source of deuterium-containing micro-fusion fuel particles is operable above a planetary, lunar or asteroid surface in the presence of ambient cosmic rays. The fuel particles are dispersible from a set of ports, where at least some of the ports are in an underside of the craft body and others are in lateral sides of the craft body. Dispersed fuel particles interact with ambient cosmic rays and muons to generate energetic reaction products, at least some which are then received by the underside of the craft to generate lift and also selected lateral sides of the craft to generate propulsive thrust in a desired lateral direction. The craft can carry tethers and winches to carry a payload above the surface from location to another. In another embodiment, a balloon-based design, such as a dirigible, provides primary buoyant lift, while the micro-fusion particles provide at least lateral thrust, and supplemental lift where needed.

To reduce space debris and decrease risks for future space flights and currently operating satellites, NASA requires all satellites to have an end of life deorbiting plan to prevent satellites from having long and indefinite orbit lifespan. Accordingly, disclosed herein are systems and methods for deploying a deorbiting drag device to dramatically decrease the orbit lifespan of satellites. One of the methods comprises: providing power, using a photovoltaic panel, to a central processing unit (CPU) of the satellite; determining, using a health sensor, a health status of the satellite by monitoring activities of the CPU; and releasing a deorbiting drag device based on the health status by diverting power from the photovoltaic panel to a release actuator.

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.