Abstract: An apparatus for detecting the presence of ice includes a sensory circuit including a sensor operable to be coupled to a surface exposed to moisture. The sensory circuit is operable to create an electromagnetic standing wave. A heating element is coupled to the surface and a first transmission line. A first source is coupled to the first transmission line and is operable to inject a driving signal into the first transmission line, the driving signal being operable to drive the heating element. A mixing element is coupled to the sensory circuit and first transmission line and is operable to produce a mixed signal from the driving signal and a measure of the standing wave. A comparator is operable to compare at least one characteristic of the mixed signal with reference data for determining the presence of ice contacting the sensor.

Abstract: A wireless corrosion detector includes a surface acoustic wave (SAW) sensor tag. The SAW sensor tag has an output port. At least one electro-resistive (ER) corrosion sensor is coupled to the output port.

Abstract: A system, method and computer program product is provided for automated defect detection of corrosion or cracks using synthetic aperture focusing technique (SAFT) processed Lamb wave images. The method comprises processing the first image using a synthetic aperture focusing technique (SAFT) to enhance a resolution and a signal to noise ratio of a first extracted ultrasonic image, applying a systemic background noise suppression algorithm to the first extracted ultrasonic image to render a second extracted ultrasonic image having reduced noise, and applying a deconvolution linear filtering process to the second extracted ultrasonic image to render a third extracted ultrasonic image.

Abstract: A structure health monitoring (“SHM”) system according to the invention can be deployed in an onboard environment, such as an aircraft, to provide an ongoing damage assessment of structural components on the aircraft. The SHM system reduces or eliminates time consuming and costly manual inspections of aircraft. The SHM system can leverage known sensor technologies to collect sensor data indicative of the structural health of the monitored components. The sensor data is processed and baselined with sensor feature baselines and damage estimate baselines to provide an accurate final damage estimate for the monitored component. The final damage estimate can be further processed or formatted for compatibility with aircraft maintenance systems.

Abstract: A method for determining damage in a structural health monitoring system comprising a plurality of sensors distributed across a structure is disclosed. The method includes decomposing the plurality of sensors into a plurality of sub-arrays. Each sub-array is associated with a current sensor. For each sub-array, data is collected, the data corresponding to electrical signals produced by waves initiated by the current sensor and detected by a receiving sensor. The data is used to calculate a damage measurement for the sub-array. Then, the damage measurement determined for each sub-array is combined to determining an overall damage assessment from the combined damage measurements.

Abstract: A method is disclosed wherein a plurality of sensors mounted on a structure, a baseline data set for each of the plurality of sensors and a calibration procedure verify the integrity of a structural health management system. Initially a baseline data set is established. Before performing the structural health assessment a calibration-in data set for each of the plurality of sensors is collected. The calibration-in data set is compared to the baseline data set for each sensor of the plurality of sensors. If the calibration-in data set and the baseline data set match then a structure characterization is performed. If the calibration-in data set and the baseline data set do not match, a calibration-out procedure is performed to generate a calibration-out data set. If the calibration-out data set and the calibration-in data sets match, then a determination is made that the structural health management system was working.

Abstract: In the present invention, a method is provided for installing and locating a plurality of sensors distributed on a structure as part of a structural health monitoring system. The method includes verifying the proper installation of the plurality of sensors and determining the location of the plurality of sensors. In one aspect of the present invention, the step of verifying the proper installation further comprises verifying that each of the plurality of sensors are properly coupled to a sensor data collector and verifying that each of the plurality of sensors are installed in a proper location. In another aspect of the present invention, the step of determining the location of the plurality of sensors further comprises determining the positioning of each sensor in reference to fixed structures in the structure.

Abstract: A transducer for use in a structural health monitoring system includes a single transducer element. The transducer includes a transmit assembly coupled to the single transducer element. This assembly is configured to produce a multi-cycle square wave drive signal for stimulating the transducer. Additionally, a transmit/receive switch coupled to the single transducer element is provided. This assembly is configured to isolate the drive signal from the receive assembly used to sense the electrical signal generated from any received elastic waves.

Abstract: In the present invention, a method is provided for installing and locating a plurality of sensors distributed on a structure as part of a structural health monitoring system. The method includes verifying the proper installation of the plurality of sensors and determining the location of the plurality of sensors. In one aspect of the present invention, the step of verifying the proper installation further comprises verifying that each of the plurality of sensors are properly coupled to a sensor data collector and verifying that each of the plurality of sensors are installed in a proper location. In another aspect of the present invention, the step of determining the location of the plurality of sensors further comprises determining the positioning of each sensor in reference to fixed structures in the structure.

Abstract: A method for estimating damage to a structure is provided. The method includes collecting a plurality of damage estimates over time and filtering the plurality of damage estimates with spatio-temporal filters. The method also includes generating an enhanced damage estimate based on the filtered damage estimate. In other embodiments, a damage estimate system and a computer readable medium having instructions embodied thereon for a method for estimating damage to a structure are provided.

Abstract: A method for analyzing test data from nondestructive evaluation of an aircraft includes generating a model of the aircraft with an inspection point. The aircraft is mapped to the model of the aircraft. Then, measurement data is generated by nondestructive testing an area of the aircraft corresponding to the inspection point. The measurement data is stored with associated location data of the inspection point and measurement parameters for comparison. The model of the aircraft with the inspection point is displayed. The measurement test data is displayed for a selected inspection position.

Abstract: A method for verifying the integrity of a structural health management system comprising a plurality of sensors mounted on a structure, a baseline data set for each of the plurality of sensors and a calibration procedure that uses the structure itself as part of the reference standard is disclosed. Initially a baseline data set, including time-of-flight between each of the plurality of sensors and neighboring sensor selected from the plurality of sensors, is established. Before performing the structural health assessment a calibration-in data set for each of the plurality of sensors is collected. The calibration-in data set is compared to the baseline data set for each sensor of the plurality of sensors. If the calibration-in data set and the baseline data set match then a structure characterization is performed. If the calibration-in data set and the baseline data set do not match, an approach to resolving the ambiguity between inoperable sensors versus structural failure is disclosed.

Abstract: A method for estimating damage to a structure is provided. The method comprises collecting a plurality of damage estimates over time and filtering the plurality of damage estimates with spatio-temporal filters. The method also comprises generating an enhanced damage estimate based on the filtered damage estimate.

Abstract: A structure health monitoring (“SHM”) system according to the invention can be deployed in an onboard environment, such as an aircraft, to provide an ongoing damage assessment of structural components on the aircraft. The SHM system reduces or eliminates time consuming and costly manual inspections of aircraft. The SHM system can leverage known sensor technologies to collect sensor data indicative of the structural health of the monitored components. The sensor data is processed and baselined with sensor feature baselines and damage estimate baselines to provide an accurate final damage estimate for the monitored component. The final damage estimate can be further processed or formatted for compatibility with aircraft maintenance systems.

Abstract: A structure health monitoring (“SHM”) system according to the invention can be deployed in an onboard environment, such as an aircraft, to provide an ongoing damage assessment of structural components on the aircraft. The SHM system reduces or eliminates time consuming and costly manual inspections of aircraft. The SHM system can leverage known sensor technologies to collect sensor data indicative of the structural health of the monitored components. The sensor data is processed and baselined with sensor feature baselines and damage estimate baselines to provide an accurate final damage estimate for the monitored component. The final damage estimate can be further processed or formatted for compatibility with aircraft maintenance systems.

Abstract: A transducer for use in a structural health monitoring system comprises a single transducer element. The transducer comprises a transmit assembly coupled to the single transducer element. This assembly is configured to produce a multi-cycle square wave drive signal for stimulating the transducer. Additionally, a transmit/receive switch coupled to the single transducer element is provided. This assembly is configured to isolate the drive signal from the receive assembly used to sense the electrical signal generated from any received elastic waves.

Abstract: A method for determining damage in a structural health monitoring system comprising a plurality of sensors distributed across a structure is disclosed. The method includes decomposing the plurality of sensors into a plurality of sub-arrays. Each sub-array is associated with a current sensor. For each sub-array, data is collected, the data corresponding to electrical signals produced by waves initiated by the current sensor and detected by a receiving sensor. The data is used to calculate a damage measurement for the sub-array. Then, the damage measurement determined for each sub-array is combined to determining an overall damage assessment from the combined damage measurements.

Abstract: In the present invention, a method is provided for installing and locating a plurality of sensors distributed on a structure as part of a structural health monitoring system. The method includes verifying the proper installation of the plurality of sensors and determining the location of the plurality of sensors. In one aspect of the present invention, the step of verifying the proper installation further comprises verifying that each of the plurality of sensors are properly coupled to a sensor data collector and verifying that each of the plurality of sensors are installed in a proper location. In another aspect of the present invention, the step of determining the location of the plurality of sensors further comprises determining the positioning of each sensor in reference to fixed structures in the structure.

Abstract: A structure health monitoring (“SHM”) system according to the invention can be deployed in an onboard environment, such as an aircraft, to provide an ongoing damage assessment of structural components on the aircraft. The SHM system reduces or eliminates time consuming and costly manual inspections of aircraft. The SHM system can leverage known sensor technologies to collect sensor data indicative of the structural health of the monitored components. The sensor data is processed and baselined with sensor feature baselines and damage estimate baselines to provide an accurate final damage estimate for the monitored component. The final damage estimate can be further processed or formatted for compatibility with aircraft maintenance systems.