INTEGRATED AEROELASTICITY MEASUREMENT FOR VEHICLE HEALTH MANAGEMENT
First Claim
1. A computer based method to monitor structural integrity of an aircraft, comprising:
- receiving, in a processing device aboard the aircraft, a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation;
storing the plurality of aeroelasticity measurements and associated flight parameters in a memory module; and
generating an alert when one or more aeroelasticity parameters exceeds a threshold.
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Accused Products
Abstract
Systems and methods for aeroelasticity measurement and vehicle structural health analysis and monitoring are disclosed. In one embodiment, a computer based system to monitor structural integrity of an aircraft comprises a processor and a memory module coupled to the processor and comprising logic instructions stored on a computer readable medium which, when executed by the processor, configures the processor to receive a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation, store the plurality of aeroelasticity measurements and associated flight parameters in a persistent storage medium, and generate an alert when one or more aeroelasticity parameters exceeds a threshold. In some embodiments, the system may be implemented in a computing system or as logic instructions recorded on a computer readable medium.
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Citations
24 Claims
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1. A computer based method to monitor structural integrity of an aircraft, comprising:
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receiving, in a processing device aboard the aircraft, a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation; storing the plurality of aeroelasticity measurements and associated flight parameters in a memory module; and generating an alert when one or more aeroelasticity parameters exceeds a threshold. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A computer based system to monitor structural integrity of an aircraft, comprising:
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a processor; a memory module coupled to the processor and comprising logic instructions stored on a computer readable medium which, when executed by the processor, configures the processor to; receive a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation; store the plurality of aeroelasticity measurements and associated flight parameters in a persistent storage medium; and generate an alert when one or more aeroelasticity parameters exceeds a threshold. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16, 24)
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17. A system to monitor structural health of an aircraft, the system comprising a first computer program product to implement a real-time vehicle structural health monitoring process in an aircraft, the computer program product comprising logic instructions stored on a computer readable medium which, when executed by a processor, configure the processor to:
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receive a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation of the aircraft; store the plurality of aeroelasticity measurements and associated flight parameters in a persistent storage medium; and generate an alert when one or more aeroelasticity parameters exceeds a threshold. - View Dependent Claims (18, 19, 20, 21, 22, 23)
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Specification