A method for cooling a satellite system comprising configuring a plurality of fins to absorb and emit thermal radiation, wherein the ratio of absorptivity/emissivity is less than one; mechanically coupling the plurality of fins to the outside surface of a satellite, wherein the angle of the plurality of fins can be adjusted and controlled such that they can be stowed against the surface of the satellite or deployed; deploying the fins as necessary to expel heat from the satellite.

Implementations of the disclosed subject matter provides a system having an artificial light source disposed at a distance from earth or other celestial body, where the artificial light source is configured to project one or more beams of light onto the earth or other celestial body. The system may include a photovoltaic array disposed in an area on the earth or other celestial body that is 200 m-20 km or more in any one dimension that is configured to receive the projected one or more beams of light and is configured to convert the received one or more beams of light into electricity.

An energy-saving loop heat pipe apparatus and an application. The loop heat pipe apparatus comprises a capillary pump component and an evaporation unit component. The loop heat pipe apparatus further comprises at least one heat exchanger disposed between the capillary pump component and the evaporation unit component for heating, by using heat of a circulating working medium in the loop heat pipe, the circulating working medium about to enter the evaporation unit component. By providing heat exchangers between the evaporation unit component and the capillary pump component, the energy-saving loop heat pipe apparatus may use heat of a gas-phase working medium flowing out of the evaporation unit component to heat a liquid-phase working medium about to enter the evaporation unit component, so that waste heat is utilized to the fullest extent and energy is saved.

A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.

A compartment for a space vehicle includes a pressurized structure having a structural wall, the structural wall having interior surfaces facing an interior of the compartment and exterior surfaces exposed to an external environment. An internal mounting structure for mounting a component is provided within the compartment, and mounting features support the internal mounting structure from the pressurized structure. The internal mounting structure is spaced away from the interior surfaces of the pressurized structure, and a thermal fluid is provided in the pressurized structure. The thermal fluid enables convective heat transfer between the component mounted on the internal mounting structure and the interior surfaces of the pressurized structure.

A sublimator control valve system may include a sublimator having an injection port, a feedwater supply, a first solenoid valve in fluid communication with the feedwater supply and the injection port of the sublimator, a first sensor in electronic communication with a first controller, the first sensor configured to measure at least one of a first pressure parameter or a first temperature parameter; and a first tangible, non-transitory memory configured to communicate with the first controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the first controller, cause the first controller to perform operations comprising receiving, by the first controller, a command signal and the first pressure parameter, and controlling, by the first controller, the first solenoid valve in response to at least one of the command signal or the first pressure parameter.

A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An apparatus includes a space vehicle including means for performing propulsion operations without using a chemical propulsion system.

A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.

A heat pipe has an evaporator portion, a condenser portion, and at least one flexible portion that is sealingly coupled between the evaporator portion and the condenser portion. The flexible portion has a flexible tube and a flexible separator plate held in place within the flexible tube so as to divide the flexible tube into a gas-phase passage and a liquid-phase artery. The separator plate and flexible tube are configured such that the flexible portion is flexible in a plane that is perpendicular to the separator plate.