Integrated vibration reducing and health monitoring system for a helicopter
First Claim
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1. An integrated vibration reducing and health monitoring system for a helicopter comprising:
- a plurality of vibration sensors for measuring vibration responses located on a helicopter structure;
a computer;
a plurality of actuators for inputting forces into the structure to reduce vibration of the structure, said vibration sensors providing first data comprising signals representative of the vibration of the structure to said computer;
wherein said computer constructs second data comprising a transfer matrix providing a linear transfer relationship between the vibration responses measured by said vibration sensors and the forces from said actuators and representative of the dynamic characteristics of the helicopter,said computer further producing third data comprising actuator command signals for inputting calculated actuator control forces; and
monitoring means for monitoring said second and third data provided by said computer, for comparing said monitored data with predetermined data and for providing a warning signal and diagnostic information if said predetermined data values are exceeded by said monitored data, wherein health monitoring is achieved in relation to helicopter dynamic characteristics independent of flight state characteristics.
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Abstract
This invention monitors data produced by a vibration reducing system relating to the vibration of a structure, compares the data against a predetermined value and provides a warning if the predetermined value is exceeded to provide an integrated vibration reducing and structural health monitoring system.
82 Citations
4 Claims
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1. An integrated vibration reducing and health monitoring system for a helicopter comprising:
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a plurality of vibration sensors for measuring vibration responses located on a helicopter structure; a computer; a plurality of actuators for inputting forces into the structure to reduce vibration of the structure, said vibration sensors providing first data comprising signals representative of the vibration of the structure to said computer; wherein said computer constructs second data comprising a transfer matrix providing a linear transfer relationship between the vibration responses measured by said vibration sensors and the forces from said actuators and representative of the dynamic characteristics of the helicopter, said computer further producing third data comprising actuator command signals for inputting calculated actuator control forces; and monitoring means for monitoring said second and third data provided by said computer, for comparing said monitored data with predetermined data and for providing a warning signal and diagnostic information if said predetermined data values are exceeded by said monitored data, wherein health monitoring is achieved in relation to helicopter dynamic characteristics independent of flight state characteristics. - View Dependent Claims (2, 3, 4)
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Current AssigneeWestland Helicopters Limited (Leonardo S.p.A.)
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Original AssigneeWestland Helicopters Limited (Leonardo S.p.A.)
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InventorsStaple, Alan E.
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Primary Examiner(s)ZANELLI, MICHAEL J
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Application NumberUS07/966,400Time in Patent Office813 DaysField of Search364/508, 364/551.01, 364/424.06, 364/424.03, 364/424.04, 364/574, 73/583, 73/588, 73/662, 73/663, 73/668, 244/17.13, 340/963US Class Current700/280CPC Class CodesB64C 2027/004 using actuators, e.g. activ...B64C 27/001 Vibration damping devicesB64D 2045/0085 Devices for aircraft health...B64D 45/00 Aircraft indicators or prot...F16F 15/02 Suppression of vibrations o...G01H 1/00 Measuring characteristics o...
