发明名称 SYSTEM FOR MONITORING AND CONTROLLING A REDUNDANT ELECTROHYDRAULIC POSITIONING DRIVE
摘要 1459516 Fluid-pressure servomotor systems VEREINIGTE FLUGTECHNISCHE WERKEFOKKER GmbH 9 April 1974 [9 April 1973] 15665/74 Heading G3P A system for controlling a redundant electrohydraulic positioning drive comprising at least three working cylinders acting on a common load includes at least as many pressure dependent signal transmitters as the number of working cylinders, each transmitter being connected to the working chambers of at least one cylinder, and a common comparator to receive the signals and acting to switch-off a faulty cylinder. In one arrangement, four working cylinders 10 to 13 have a common piston-rod 18 connected to control nozzles 41 and surfaces 44 of a VTOL aircraft. Each cylinder 10 to 13 is connected to a respective servovalve 19 to 22 which is supplied by an individual hydraulic system via a shut-off valve 23 to 26. Four signal transmitters 27 to 30 are provided, each having an auxiliary cylinder 31 with a potentiometer 32 displaceable thereby. The working spaces of each auxiliary cylinder 31 are connected to the working spaces of two adjacent working cylinders 10 to 13. The signals generated by potentiometers 32 are fed to an error logic unit 35 which, in the case of minor deviations, transmits signals to scanning amplifiers 36 to 39 controlling servovalves 19 to 22. The amplifiers also receive primary input signals together with positional feedback signals from potentiometers 40. In the case of a major fault in a working cylinder 10 to 13, logic unit 35 transmits a signal to the appropriate valve 23 to 26 to cutoff the hydraulic supply to the faulty cylinder. In a modification Fig. 3 (not shown), the auxiliary cylinders 31 and potentiometers 32 are replaced by capsules (56 to 59) which generate electric signals corresponding to the applied pressure. Each capsule is connected to the working spaces of only one working cylinder 10 to 13 and a comparison of the signals from all the capsules is made in the logic unit 35. In a further modification Fig. 4 (not shown) the system includes two additional signal transmitters (60, 61) which provide diagonal monitoring paths.
申请公布号 GB1459516(A) 申请公布日期 1976.12.22
申请号 GB19740015665 申请日期 1974.04.09
申请人 VEREINIGTE FLUGTECHNISCHE WERKE FOKKER GMBH 发明人
分类号 F15B9/03;F15B18/00;G05D1/00;(IPC1-7):F15B18/00 主分类号 F15B9/03
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