Design And Validation Of A Dual-channel And Fault-tolerant EEC Based On BIT

In order to enhance the reliability of aircraft engine electronic controller (EEC), the design and validation technology of dual channel fault-tolerant EEC based on built-in test (BIT) is discussed. The design scheme of dual channel fault-tolerant EEC based on BIT was brought forward, which consists of two similar redundant control channels (channel A and B) and a monitor channel (channel C). Channel A and B realizes the fundamental control function of EEC, and channel C realizes the switch and reconfiguration function of EEC. Through the comparison analysis of reliability model with some normal EEC schemes, it has proved that this design scheme has a more reliability.On the base of analyzing the summarization of typical fault models of EEC, this paper focuses on the BIT hardware and software design of channel A (B), which could realize the fault detection of the circuits of channel A, and B, as well as the sensors and actuators. The software and hardware of channel C which has a certain function of BIT is designed too.The validation technology of EEC is discussed .An integrated simulation adaptor with functions of normal signal emulation and fault signal injection is devised, which could be used as the validation tools for BIT technology and fault-tolerant control technology of EEC. Furthermore, the normal con-trol experiments and fault injection experiments were both carried out, and the results indicate that the BIT functions, channel switching and fault-tolerant controlling of EEC are effective.