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.

A method for thermally stabilizing a communication satellite in orbit around the Earth relies on the discrete rotational symmetry of the pattern of antenna beams of the satellite. Exploiting the symmetry, the orientation of the satellite is changed from time to time by rotating the satellite through a symmetry angle of the rotational symmetry. Because of the symmetry, the beam pattern is unchanged after the rotation; but, because the rotation angle is less than 360°, a different side of the satellite is exposed to sunlight. The use of different thermal radiators and thermal shields on different sides of the satellite means that the thermal budget of the satellite is different after the rotation. By judiciously applying rotations as needed, as the orbit's orientation relative to the Sun evolves in time, it is possible to achieve effective control on the thermal budget of the satellite.

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 Common Bus Structure for Avionics and Satellites (CBSAS) (10) as shown in FIG. 1 is comprised of a module lid (14), module floor (38), module stack base (16), module compression bolts (22) and stackable modules (12). Stackable modules (12) are sub-dividable to create module scaled chamber volumes (45) individually as required, while stackable modules (12) simultaneously create at least one collectively continuous raceway sealed chamber volume (44) perpendicular to individual stackable modules (12) in the vertical direction where no module floor (38) is present, in order to internally electrically interconnect the contents of any stackable module (12) with the contents of any other stackable module (12) via internal connector raceway system (24). Raceway sealed chamber volume (44) therefore collectively and continuously traverses all present stackable modules (12) positioned between module lid (14) and module stack base (16). Modules are interchangeable and inter-connectable in any order, and contain all required electronic or mechanical components required for CBSAS (10) to function as a single box consolidated avionics system that is equally functional in the atmosphere or the vacuum of space, while also being fully functional as a single complete stand-alone satellite system. CBSAS (10) enables a paradigm shift in the aerospace industry whereby all legacy and current multiple black-box systems on aerospace platforms such as missiles, rockets, satellites and aircraft are extremely inefficient when compared to the size, weight and power attributes of CBSAS (10). The ability for CBSAS (10) to be instantly employable as either a single box consolidated avionics system for use within the atmosphere or in space while also being fully functional as a stand-alone satellite enables a hardware, firmware and software capability never before manifested in the aerospace industry.

A hybrid power source and control moment gyroscope (“HPCMG”) is disclosed. The HPCMG includes a control moment gyroscope (“CMG”), a first conductive bearing, and a second conductive bearing. The CMG includes a first transverse gimbal assembly, a central mass that produces a voltage potential, and a second gimbal assembly rotationally connected to the first transverse gimbal assembly. The first transverse gimbal assembly is rotationally connected to the central mass along a first axis of rotation and the central mass is configured to spin about the first axis of rotation and the first transverse gimbal assembly is configured to rotate about a second axis of rotation of the second gimbal assembly. The first conductive bearing rotationally connects the central mass with the first position of the first transverse gimbal assembly along the first axis of rotation.

An electric propulsion module coupled to a spacecraft capable of providing thrust at a level required for multi-burn orbit transfer is disclosed herein. The electric propulsion system includes an electric propulsion thruster, a propellant tank and an energy storage device. In one form the energy storage device is a battery operable to provide sufficient power to maneuver the spacecraft quickly to avoid space debris and/or move to a different orbit through a multi-burn thrust procedure.

A de-orbiting system for a space vehicle may include one or more lithium ion (Li-ion) batteries configured to release hot gases to be used for thrusting during de-orbiting of the apparatus. The system may also include one or more heaters surrounding each of the one or more Li-ion batteries, which are configured to send each of the one or more Li-ion batteries into a thermal runaway. The thermal runaway causes the one or more Li-ion batteries to release stored electrochemical energy within each of the one or more Li-ion batteries.

A nanosatellite with an illumination element, and an arrangement of nanosatellites in low earth orbit (LEO) arranged to controllably apply their illumination to be visible on the ground. The nanosatellites may be coordinated to provide illumination events visible on the ground at particular locations and particular times. Each nanosatellite has an illumination element that provides a sustained external illumination event being of at least momentary duration and to be visible from the ground. The event forms at least part of a display for viewing from the ground.

A satellite includes a housing, a circuit board containing circuitry, a battery electrically connected to the circuit board, a tank, an expandable balloon disposed in the tank, a heater, a valve providing liquid communication between the tank and the heater when in an open position and providing no liquid communication between the tank and the heater when in a closed position, and a nozzle having an orifice in liquid communication with the heater. Operating the satellite includes partially filling the expandable balloon with a gas, loading liquid fuel into the tank, launching the satellite into space, opening the valve to cause the liquid fuel from the tank to pass into the heater under pressure provided by the gas in the expandable balloon, activating the heater to heat and vaporize the liquid fuel into a fuel vapor, and expelling the fuel vaper out of the nozzle.

To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.