A system includes a satellite assembly. The assembly includes a plurality of satellite devices, where each satellite device includes a processor device, an impulse actuator, and a memory storing instructions. The instructions are executable by the processor device to access a sequence of waypoints. The sequence of waypoints identifies a first waypoint and is associated with formation of a distributed structure including the plurality of satellite devices. The instructions are further executable by the processor device to initiate movement of the satellite device toward the first waypoint at least by initiating activation of the impulse actuator.

A payload interposer (PIP) board provides an interface for hosting payloads on a space vehicle platform. Payload development may be performed via the PIP board in a manner that “abstracts” the hardware of the space vehicle from the payload developer. The PIP board may include a host side payload interface connector that connects to a space vehicle and a payload side payload interface connector that connects to a payload. Power, CDH, and other space vehicle functionality may thus be provided to the payload from the space vehicle via the PIP board.

A control system for a spacecraft for determining a resultant torque that is exerted upon a spacecraft by one or more magnetic torque rods is disclosed. The spacecraft is configured to revolve around a celestial body in an orbit. A magnetic field of the celestial body is predictable, and a direction of the magnetic field located around the orbit is fixed. The control system includes the one or more magnetic torque rods, one or more processors in electronic communication with the one or more magnetic torque rods, 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 instruct the one or more magnetic torque rods to exert the resultant torque upon the spacecraft.

A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Power transmitters can be coordinated as a phased array and the power generated by the phased array is transmitted to one or more power receivers to achieve remote wireless power generation and delivery. In many embodiments, a reference signal is distributed within the space-based solar power station to coordinate the phased array. In several embodiments, determinations of the relative locations of the antennas in the array are utilized to evaluate the phase shift and/or amplitude modulation to apply the reference signal at each power transmitter.

A power controller includes: a plurality of switching elements provided in one-to-one correspondence with a plurality of power supplies, and each of which switches on or off to switch between supplying and stopping supplying a load with electric power from a corresponding one of the plurality of power supplies; a processing unit which computes an operation amount for adjusting an amount of the electric power supplied to the load; and a signal generator which determines, for each control, a switching-element count indicating a total number of switching elements to be turned on among the plurality of switching elements, and a duty ratio of the switching-element count, based on the operation amount, and generates a drive signal for driving the plurality of switching elements successively, based on the switching-element count and the duty ratio.

A rotation-stabilized beamed-energy receiver, and associated systems and methods, including an aircraft carrying a rotating electromagnetic energy receiver that, when rotated, is supported by centripetal force in a selected shape and/or orientation. Accordingly, the receiver can be made from very thin and/or otherwise lightweight/flexible materials, while performing an energy-receiving function.

An antenna assembly has a solar layer having one or more solar cells generating solar power, an antenna layer connected to the solar layer and having electronic components utilizing the solar power generated by the solar layer, and a thermal dissipation device dissipating heat locally at the antenna assembly. A large number of antenna assemblies are connected to form an antenna array in which heat is generated locally at each antenna assembly and dissipated locally at each antenna assembly.

A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.

A power distribution device includes an input, an output, a power switch controller, and a voltage isolation device. The power distribution device includes, and is designed to provide power to, for example, non-radiation-tolerant or non-radiation hardened components for use in low Earth orbit (LEO) missions. The input is configured to receive power from a power source. The output is configured to provide the power to an electrical load. The power switch controller is configured to selectively operate the power distribution device in a first mode responsive to a first event, and to selectively operate the power distribution device in a second mode responsive to a second event. The voltage isolation device includes a plurality of switches configured, in the first mode, to pass the power between the input and the output, and, in the second mode, to interrupt the passage of the power between the input and the output.

A spacecraft propulsion system comprises two thrusters, each operating in accordance to a corresponding propulsion technique. A controller is configured to direct collected solar energy to heat a propellant for consumption in one of the two thrusters, or to generate electric energy for the other one of the two thrusters.