Abstract: A heating system for a component within a compartment of a spacecraft includes a fuel source, a gas generator, and a heat sink. The fuel source includes hydrazine. The gas generator is in fluid communication with the fuel source. The gas generator includes a catalyst. The catalyst is configured to decompose the hydrazine and generate an exhaust gas. The heat sink is thermally coupled to the gas generator and configured to receive heat from the exhaust gas of the gas generator. The heat sink is thermally coupled to the component within the compartment of the spacecraft to transfer heat from the exhaust gas to the component.

Abstract: Sealed containers for radioactive material are presented herein. A sealed container forms an interior envelope for housing a radioactive material and prevents escape of the radioactive material into a surrounding environment. The sealed container provides a diffusion window for gaseous decay products to escape at a particular diffusion rate. In one example, an apparatus, comprises a container forming a sealed interior envelope for a radioactive material. The container has an aperture covered by a window material, and properties of the window material are selected to provide for diffusion of at least one gas produced by radioactive decay of the radioactive material.

Abstract: Sealed containers for radioactive material are presented herein. A sealed container forms an interior envelope for housing a radioactive material and prevents escape of the radioactive material into a surrounding environment. The sealed container provides a diffusion window for gaseous decay products to escape at a particular diffusion rate. In one example, an apparatus, comprises a container forming a sealed interior envelope for a radioactive material. The container has an aperture covered by a window material, and properties of the window material are selected to provide for diffusion of at least one gas produced by radioactive decay of the radioactive material.