A radiator for a geostationary satellite is disclosed having a radiative panel perpendicular to a radiation axis, and pivoting relative to the radiation axis, a mounting foot for the panel, a motor which rotates the mounting foot about a rotation axis, the radiation axis and the rotation axis being tilted relative to each other by an angle corresponding to the angle of the satellite's orbital plane relative to the ecliptic plane of the planet, and a guidance system for the panel, limiting rotation of the panel about the rotation axis, including a connecting arm pivoting relative to the satellite about a first axis and relative to the panel about a second axis concurrent with the first axis at a point of intersection of all the axes.

Various aspects as described herein are directed to a radiative cooling device and method for cooling an object. As consistent with one or more embodiments, a radiative cooling device includes a solar spectrum reflecting structure configured and arranged to suppress light modes, and a thermally-emissive structure configured and arranged to facilitate thermally-generated electromagnetic emissions from the object and in mid-infrared (IR) wavelengths.

Various aspects as described herein are directed to a radiative cooling device and method for cooling an object. As consistent with one or more embodiments, a radiative cooling device includes a solar spectrum reflecting structure configured and arranged to suppress light modes, and a thermally-emissive structure configured and arranged to facilitate thermally-generated electromagnetic emissions from the object and in mid-infrared (IR) wavelengths.

There is provided a thermal management apparatus for use with a vehicle comprising: a chassis in thermal contact with one or more first components that require thermal management and one or more second components that require thermal management, wherein the chassis is configured to transfer heat from the one or more first components to the one or more second components.

Thermal control of powered systems on-board a flight vehicle is achieved by leveraging the latent heat storage capacity of Phase Change Materials (PCMs) to maintain the operating temperature at or slightly above the melting temperature of the PCM. The invention is particularly well suited for use with powered systems such as laser, microwave emitters, RF sensors and high-density power electronics that must operate at a desired operating temperature while generating considerable waste heat in a confined packaging volume of smaller flight vehicles such as missiles, rockets, guided projectiles, drones or other such platforms.

Thermal control of powered systems on-board a flight vehicle is achieved by leveraging the latent heat storage capacity of Phase Change Materials (PCMs) to maintain the operating temperature at or slightly above the melting temperature of the PCM. The invention is particularly well suited for use with powered systems such as laser, microwave emitters, RF sensors and high-density power electronics that must operate at a desired operating temperature while generating considerable waste heat in a confined packaging volume of smaller flight vehicles such as missiles, rockets, guided projectiles, drones or other such platforms.

The present disclosure relates to a thermal emissivity control system. The system may have a segmented array that makes use of a thermally conductive base layer configured to be connectable to an external heat generating subsystem, with the base layer including a thermally emissive surface. The array may also have a plurality of actuation elements at least one of positioned on or adjacent to the thermally emissive surface. A plurality of movable shutter elements is disposed adjacent one another in a grid pattern, and controlled in movement by the actuation elements to create gaps of controllably varying dimension therebetween. The shutter elements control at least one of a magnitude of, or direction of, thermal radiation through the gaps.

A kinked thin tube that deploys, possibly using pressurized fluid, and can transport heat to other structures. Radiator panels attached to the tubes can deploy into a flat plane from a stowed configuration, allowing for efficient storage and reduced mass. Additionally, hollow brackets can be used to connect to the thin tubes structurally and thermally.

A spacecraft sunshade is provided. The sunshade includes a surface that is maintained in a sun facing orientation. Adjustments to a position of the sunshade are made in a plane that is transverse to a line of sight to the sun, in order to block sunlight from being directly incident on an instrument associated with the spacecraft. The sunshade can include photovoltaic elements on the sun-facing surface of the sunshade. In addition, the sunshade can be formed from an opaque material, and further from a material that absorbs heat from the sun and reradiate that heat to the instrument. The sunshade can perform stray light blocking, electrical power generation, and radiational heating functions.

A method for providing thermal balance of spacecraft electronics is provided. The spacecraft includes two or more electronic units wherein each electronic unit is capable of performing the same spacecraft operational task. The method for balancing the temperature of spacecraft electronics further includes providing each of the two or more electronic units with a temperature sensor for determining the temperature of that electronics unit. The electronic units and their respective temperature sensors are connected to a controller. In the event that the controller determines that the temperature of an activated first electronics unit has reached or exceeded a predetermined threshold, and the controller has determined that the temperature of a second deactivated electronics unit is below a predetermined threshold, the controller automatically deactivates the first electronics unit and activates the second electronics unit to perform the task previously being performed by the first electronics unit. This process continues automatically.