| 摘要 |
An aircraft engine fuel system (10) is provided and includes a pump (20), including an inlet (21) and an outlet (22), from which pressurized output is produced, a valve (30) disposed downstream from the pump outlet to receive and to direct the pump output flow toward the engine and to provide a leak tight seal when the pump is not operating, a sensor (50) configured to issue a signal reflective of a state of the valve at first and second conditions and a controller (160), operably coupled to the pump and the sensor, which is receptive of the signal and which modifies performance models of the pump and engine to control pump speed to modify pump flow accordingly. |
