| 摘要 |
The thermal control device comprises at least one capillary pumped diphasic fluid loop (1), comprising, in a known manner, an evaporator (2) extracting the heat from a source known as hot (A) and connected via a steam pipe (4) to a condenser (3) wherein the condensation of the fluid steam releases a thermal energy transmitted to a source known as cold (B), the condenser (3) being connected via a pipe of liquid (7) to the evaporator (2), and the device moreover comprises at least one heat capacity (17) in relation to permanent heat exchange with the fluid in liquid phase of said diphasic fluid loop (1). Use in particular with space vehicles such as satellites. |
