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.

Systems, methods, and apparatus for magnetic maneuvering for satellites are disclosed. In one or more embodiments, a method for maneuvering satellites comprises applying, by a current source in a first satellite, current to an electromagnet in the first satellite. The method further comprises generating, by the electromagnet in the first satellite in response to the current, a magnetic field. Further, the method comprises maneuvering, by the first satellite, a second satellite via the magnetic field. In one or more embodiments, the electromagnet comprises a torque rod, an electric motor coil, and/or a solar array. In one or more embodiments, the second satellite comprises a ferromagnetic or ferrimagnetic material, a conductive material, or a combination thereof. In some embodiments, the second satellite comprises an electromagnet.

In a satellite constellation forming system, each satellite in an orbit satellite group includes a propulsion device to change velocity of each satellite in the orbit satellite group. A satellite constellation forming unit causes propulsion devices of satellites in the orbit satellite group to operate in synchronization, for each orbital plane of the plurality of orbital planes. The satellite constellation forming unit causes each satellite in an orbit satellite group in a first orbital plane of the plurality of orbital planes to perform an acceleration and deceleration process of repeating operation of accelerating for a first time period and then decelerating for the first time period. The satellite constellation forming unit causes each satellite in an orbit satellite group in an orbital plane adjacent to the first orbital plane to start the acceleration and deceleration process after a delay of a second time period.

A satellite constellation forming system forms a satellite constellation (20) including two orbital planes each having a different normal direction and in each of which the same number of satellites fly. A satellite constellation forming unit gradually changes an orbital altitude of at least one orbital plane of the two orbital planes from a state in which satellite passage timings of satellites flying in the two orbital planes do not coincide with each other at an intersection neighborhood point (Pc) between the two orbital planes in each of the two orbital planes, while maintaining the state in which the satellite passage timings do not coincide with each other.

An example system for controlling a target satellite includes: a satellite-control spacecraft including: a propulsion subsystem configured to propel and navigate the spacecraft proximate the target satellite; and a satellite-capture subsystem configured to: capture the target satellite; apply a control medium to the target satellite, the control medium including an electrically conducting and/or magnetic material; and release the target satellite; and an energization assembly configured to energize the control medium to release energy for controlling, propelling and navigating the target satellite.

A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite. In-orbit space situational awareness systems, comprising one or more in-orbit host satellites having one or more enhancement modules attached thereto, the enhancement modules comprising sensors such as satellite spatial location/position sensors, range sensors, navigation sensors, and/or proximity sensors for detecting other objects in-orbit, their location, speed, acceleration, orbital trajectory or the like, wherein the enhancement modules communicate to create a mesh network between the satellites.

A spacecraft is provided, which includes one or more of a centrally-oriented core, which includes a computing device. The computing device includes a processor and a memory, coupled to the processor, including computer instructions to control the spacecraft. The spacecraft may also include a power source, coupled to the core, a plurality of struts, each including a root end coupled the core and a distal end, the plurality of struts extending radially from the core. The spacecraft may also include a plurality of blade deployers, coupled to distal ends of the plurality of struts and a plurality of blades, coupled to the plurality of blade deployers and extending radially away from the core and in a common plane with the plurality of struts. The plurality of blades includes material configured to be deflected by solar pressure. Each of the struts is configured to provide damping to a corresponding blade.

A control system configured to execute a safing mode sequence for a spacecraft is disclosed. The control system includes one or more star trackers that each include a field of view to capture light from a plurality of space objects surrounding the celestial body. The control system also includes one or more actuators, one or more processors in electronic communication with the one or more actuators, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to determine a current attitude of the spacecraft, and re-orient the spacecraft from a current attitude into a momentum neutral attitude.

An energy conversion method transfers energy from celestial bodies, including the Earth, to a vehicle apparatus by way of a gravity assist, a descent towards the surface of the celestial body, or both. The energy transferred to the vehicle apparatus may be utilized by: a kinetic energy converter apparatus converting the kinetic energy to any form of kinetic energy, potential energy, or both; doing work on any end use process or power plant apparatus immediately, later, or both; storing the kinetic energy, the potential energy, or both on an accumulator apparatus to be utilized on site, at another location, or both.