A CubeSat satellite has a solar cell and an arc propulsion system. The arc propulsion system includes a power source, a first lead coupled to the power source and to a cathode, and a second lead coupled to the power source and to an anode. The solar cell is used as the cathode of the propulsion system.

Systems and methods for powering an electrical thruster (112) of a vehicle (100). The methods comprise providing an unregulated high voltage output current of a high voltage solar array (122) directly to an electric propulsion system (104) of the vehicle. The electric propulsion system generates a converted high voltage current by converting a voltage level of the unregulated high voltage output current. The converted high voltage current is supplied directly to an anode of the electrical thruster. A regulated low voltage current is also generated by regulating a low voltage output of a low voltage solar array (124). The regulated low voltage current is used to supply power to at least one electronic component of the electrical thruster.

A modular device for a spacecraft includes a propulsion system having a tank, a plenum, and a manifold, wherein the propulsion system is integrally formed with a structural frame of the spacecraft. A method of manufacturing the modular device is also discussed, the method including utilizing an additive manufacturing process to construct the propulsion system.

Systems (100) and methods (300, 500) for controlling an electromechanical valve element (116). The methods involve: building up a magnetic flux through a valve (206) of the electromechanical valve element by supplying a PWM signal to an electromechanically inductive coil (202) of the electromechanical valve element at a power level lower than a power level needed to actuate the valve. When the valve needs to be opened, an amplitude of the PWM signal is increased such that the power provided to the electromechanically inductive coil rises to a power level sufficient to actuate the valve. Notably, the valve opens when a power cycling time of the PWM signal increases beyond a minimum power required to open the valve.

Integrated power module device, systems, and methods are provided in accordance with various embodiments. For example, some embodiments include a system that may include one or more integrated power modules. Each integrated power module may include: one or more solar cells; one or more rechargeable energy storage cells; and/or one or more circuits coupling the one or more solar cells with the one or more rechargeable energy storage cells. In some embodiments, each integrated power module is configured such that the one or more rechargeable energy storage cells of the respective integrated power module are coupled with one or more back sides of the one or more solar cells. In some embodiments, at least two of the one or more integrated power modules are coupled with each other at least in parallel or in series.

Embodiments of the present disclosure are directed to techniques for autonomously transitioning a spacecraft from a power-saving state to a power-consuming state at a time after launch of the spacecraft on a launch vehicle. Because the spacecraft can autonomously detect conditions for transitioning to the power-consuming state, commands received via an umbilical connection to the launch vehicle, or detecting the presence or absence of such a connection, is unnecessary, thereby removing several technical barriers to eliminating such umbilical connections altogether. In some embodiments, low-cost vacuum detection devices that use very small amounts of power may be used by the spacecraft to detect when the spacecraft has reached an altitude suitable for transitioning to the power-consuming state.

A reusable staging system comprising: a processor-based device configured to monitor one or more rocket stages of a launch vehicle having a payload, wherein the processor-based device has at least one interface communicating with the one or more rocket stages of the launch vehicle; and a memory device for storing data and executing software routines, and wherein the reusable staging system is disposed within the payload of the launch vehicle, and wherein the reusable staging system is configured to actively monitor flight-related data to detect one or more detach requirements; and further configured to release the one or more rocket stages when the one or more detach requirements is met.

For power-enhanced slew maneuvers, a method determines a power collection function for a satellite. The method determines a power cost function for the satellite. The method calculates a power enhanced slew maneuver based on the power collection function and the power cost function.

A system and method for generating electrical power from a solar power supply using at least one concentrator array having a plurality of photovoltaic cells and corresponding reflector groups to direct light to the photovoltaic. A concentration ratio indicative of a portion of the electrical power capacity to generate to power a spacecraft is determined. The concentration ratio is communicated to a control module on the concentrator array. The control module selects a number of reflectors from the total number of reflectors to orient into a photovoltaic energizing position, where the selected number of reflectors corresponds to a concentration ratio of the total number of reflectors.

According to an embodiment, a testing system for a satellite payload includes a built-in testing component configured at a satellite, the built-in testing component comprising a built-in testing component input and a built-in testing component output, and a payload component configured at the satellite, the payload component comprising a payload component input communicatively connected to the built-in testing component output and a payload component output communicatively connected to the built-in testing component input, wherein the built-in testing component is configured to transmit a digital test signal from the built-in testing component output to the payload component input and receive a digital output signal at the built-in testing component input from the payload component output.