A space vehicle electromechanical system may employ an architecture that enables convenient and practical testing, reset, and retesting of solar panel and antenna deployment on the ground. A helical antenna winding fixture may facilitate winding and binding of the helical antenna.

A method for generating a fissile material is described. The method includes positioning a fertile, non-fissile material within outer space, the position within an area of proton or other high energy particle radiation, rather naturally or artificially occurring, allowing the high energy particle radiation to impinge the fertile but non-fissile material over a time, the time based on amount of high energy particle radiation at the position, such that the non-fissile material gradually transmutes into a fissile material due to the impingement, and deploying the fissile material within a spacecraft.

A control assembly for a spacecraft includes a propellant management assembly configured to adjust a supply of propellant from a storage unit to a thrust generator. The control assembly further includes a controller having a processor configured to receive an input from the spacecraft, and receive at least one input from the propellant management assembly or from the thrust generator. The processor is further configured to, based on the inputs, determine a desired operating mode of the thrust generator, and based on the determination, either 1) send an output to the propellant management assembly to operate in a first mode in which the thrust generator uses propellant to electrostatically generate thrust or 2) send an output to the propellant management assembly to operate in a second mode in which the thrust generator uses propellant to gas-dynamically generate thrust.

A method and system for satellite control in space using an IP-based satellite bus and all-IP compliant subsystems and payload(s) and a corresponding T&C system. Specifically, the present method/system includes a satellite-based IP Bus (connected as a network) that relies on Ethernet, USB, WIFI, or Bluetooth to connect various satellite components, satellite components configured to communicate on the IP bus, and a T&C system that understands the IP bus and can read its telemetry and commands. The system permits operations control on-orbit, in near real time within a secure system environment, with a dramatic increase in mission efficiency, an expansion of how much and what can be done on-orbit, and cost savings on future missions using IP-compliant spacecraft and payloads.

An array of antenna assemblies each generate solar power and utilize the generated solar power at that antenna assembly, which enables large amounts of power to be generated. An antenna assembly having a flat antenna layer forming a first outer surface of said antenna assembly, a flat solar layer forming a second outer surface of said antenna assembly, and a flat structural layer having a flat support structure sandwiched between the antenna layer and the solar layer. The antenna layer has a flat antenna plate with one or more antennas at the first outer surface of the antenna assembly to communicate with Earth. The solar layer has a flat solar plate with one or more solar cells at the second outer surface of the antenna assembly to receive solar energy and generate power.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

A system and method for protecting an electronics module on a spacecraft in space are described. The system includes a non-radiation hardened electronics module electrically connected to a power supply, with a switch connected between the power supply and the electronics module. The switch can disconnect the electronics module from the power supply in response to an event signal. A sensor which is capable of detecting a solar proton event is connected to the switch. The sensor emits the event signal upon detection of the solar proton event.

Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters.

Provided herein are various improvements to launch vehicle payload systems, such as employed to launch and deploy secondary payloads into orbit. In one example, a system includes a fairing configured to encase a payload within an envelope of a primary fairing of a launch vehicle, and a mount system configured to adapt a mounting port for the payload to a mounting port associated with the launch vehicle. The system also includes a fairing door configured to be commanded open for deployment of the payload after the primary fairing has open.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.