| 摘要 |
A distributed data acquisition system for a first engine controller determines a final, validated value of a critical flight condition variable by first determining: a first tentative value based on local environmental conditions, a second tentative value based on the performance of a first engine, and a third tentative value transferred directly from a similar data acquisition system linked to a second engine on the same aircraft. The data acquisition system compares the three tentative values and selects a final, validated value for use by the controller. |
