发明名称 ADAPTIVE CONTROL TYPE FAULT DETECTOR FOR AIRCRAFT ACTUATOR
摘要 The operation of an actuator (16) is monitored by comparing its position (21) with the position (31, 136) indicated by a model which integrates (45, 135) a limited amount of the difference between the position command (24) applied to the actuator and the achieved model position (31, 136), the limited amount being variable (63, 67, 124) from a nominal limit (61, 65, 124) in dependence upon limited functions (74, 90, 114, 116) of the difference (33, 109) between the actuator position and the model position, and additionally reduced (80, 94, 122) when pilot input overrides (50, 108) the position of the actuator.
申请公布号 JPS5755409(A) 申请公布日期 1982.04.02
申请号 JP19810120601 申请日期 1981.07.31
申请人 UNITED TECHNOLOGIES CORP 发明人 DAGURASU HARORUDO KURERUFUOODO;DONARUDO UEIN FUOORAA
分类号 G05B13/04;B64C13/00;B64C13/08;G05B23/02;G05D1/00 主分类号 G05B13/04
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