|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||364/42403 ; 244/76R ; 318/564 ; 371/681|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 56 인용 특허 : 18|
A control system includes a dual actuator (2) and primary and secondary controllers (20, 22), each of which has two control channels. In a normal mode of operation, the primary controller (20) controls both valves (32, 38) of the actuator (2). Each primary channel generates a model signal and a monitoring signal corresponding to expected and actual operation of the actuator, respectively. The two signals from each channel are communicated to the other channel. Each channel monitors itself as well as the other channel by comparing model and monitoring sig...
A method of detecting faults in an aircraft control system having an actuator, and a plurality of control channels for receiving control signals and processing said signals to generate output signals for driving said actuator, said method comprising: in each said channel, generating a monitoring signal representative of actual operation of said actuator and a model signal corresponding to expected operation of said actuator, comparing said monitoring signal to said model signal, and determining an operating status based on results of said comparing; comm...