| 摘要 |
A passive cooling system (1701) for an aircraft (11; 111) includes a rotor assembly (15, 19; 113a, 113b and a closed heat pipe (70; 80). The closed heat pipe (70; 80) is carried by the rotor assembly (15, 19; 113a, 113b) and configured to extract heat energy from a heat source positioned away from the rotor assembly and configured to dissipate the heat energy through the rotor assembly (15, 19; 113a, 113b). |
