| 摘要 |
An emergency power system (54) is useable on an aircraft having a gas turbine engine (10) with a low pressure spool (20) and a high pressure spool (28). The emergency power system (54) includes an emergency electrical generator (48) coupled to the low pressure spool (20) during an emergency for generating emergency electrical power and one or more additional electrical power sources (48A,66,70,72,74). A plurality of electrical loads (78,78A) are electrically connected to the emergency electrical generator (48) and the one or more additional electrical power sources (48A,66,70,72,74). Aircraft sensors (96A-96G) provide data regarding emergency electrical power availability and emergency electrical power demand. A controller (94) for controlling the emergency electrical generator determines emergency electrical power demand and emergency electrical power availability based upon data from the aircraft sensors (96A-96G). The controller (94) controls the emergency electrical generator (48) based upon the emergency electrical power demand and the emergency electrical power availability. |
