| 摘要 |
An aircraft control system (12) comprises transducers (40a, 40b) connected by interface units (10m-1, 10m-2, 10c-1, 10c-2) to an avionics network (24), for example, an AFDX network. Each transducer (40a, 40b) may be directly connected to an interface unit local to the transducer (40a, 40b). Each interface unit (10m-1, 10m-2, 10c-1, 10c-2) may be in the form of a configurable unit, so that all interface units are substantially identical. Each interface unit (10m-1, 10m-2, 10c-1, 10c-2) has a signal processing module (44) for converting to/from data suitable for transmission over the network. Each interface unit may be configurable, via software commands, to operate in an application session mode, a data-loading mode, or a maintenance mode. Each interface unit (10m-1, 10m-2, 10c-1, 10c-2) may be directly associated with one only of the software applications (21) of the aircraft control system. The network may include a lower bandwidth part where data communication is conducted over sampling ports only. Interface units (10m-1, 10m-2, 10c-1, 10c-2) may be configured or installed using a plug and play method. |
