Abstract: A system is provided for structural load assessment of an aircraft. An approximator may receive parameters related to a ground or flight event and calculate the resulting response load on the aircraft using a machine learning algorithm and a structural dynamics model of the aircraft. An analysis engine may compare the calculated response load to a corresponding design load for determining the structural severity of the ground or flight event on the aircraft. A maintenance engine may then automatically perform or trigger a maintenance activity for the aircraft in instances in which the structural severity of the ground or flight event causes a limit exceedance state of the aircraft or at least one structural element thereof.

Abstract: A method and apparatus for identifying deformation of a structure. Training deformation data is identified for each training case in a plurality of training cases. Training strain data is identified for each training case in the plurality of training cases. The training deformation data and the training strain data are configured for use by a heuristic model to increase an accuracy of output data generated by the heuristic model. A group of parameters for the heuristic model is adjusted using the training deformation data and the training strain data for the each training case in the plurality of training cases such that the heuristic model is trained to generate estimated deformation data for the structure based on input strain data. The estimated deformation data has a desired level of accuracy.

Abstract: A method and apparatus for identifying deformation of a structure. Training deformation data is identified for each training case in a plurality of training cases. Training strain data is identified for each training case in the plurality of training cases. The training deformation data and the training strain data are configured for use by a heuristic model to increase an accuracy of output data generated by the heuristic model. A group of parameters for the heuristic model is adjusted using the training deformation data and the training strain data for the each training case in the plurality of training cases such that the heuristic model is trained to generate estimated deformation data for the structure based on input strain data. The estimated deformation data has a desired level of accuracy.

Abstract: Vibration-damping blankets are attached to the back surfaces of fairing panels of a flight vehicle (e.g., an aircraft or spacecraft) to reduce vibration, fatigue, structure and airborne transmitted energy, and cabin noise. In one case, the flight vehicle fairing has an exterior comprising exterior surfaces of a multiplicity of removable panels. A method of retrofitting the flight vehicle with vibration-damping blankets comprises: removing a panel from the flight vehicle exterior; attaching a vibration-damping blanket to a back surface of the removed panel; and installing the panel with attached vibration-damping blanket on the flight vehicle with the exterior surface of the panel forming part of the flight vehicle exterior. In one embodiment, the vibration-damping blanket comprises polymeric (e.g., aromatic polyamide) fibers in a nonwoven structure.

Abstract: A method and apparatus for identifying deformation of a structure. Training deformation data is identified for each training case in a plurality of training cases. Training strain data is identified for each training case in the plurality of training cases. The training deformation data and the training strain data are configured for use by a heuristic model to increase an accuracy of output data generated by the heuristic model. A group of parameters for the heuristic model is adjusted using the training deformation data and the training strain data for the each training case in the plurality of training cases such that the heuristic model is trained to generate estimated deformation data for the structure based on input strain data. The estimated deformation data has a desired level of accuracy.

Abstract: Vibration-damping blankets are attached to the back surfaces of fairing panels of a flight vehicle (e.g., an aircraft or spacecraft) to reduce vibration, fatigue, structure and airborne transmitted energy, and cabin noise. In one case, the flight vehicle fairing has an exterior comprising exterior surfaces of a multiplicity of removable panels. A method of retrofitting the flight vehicle with vibration-damping blankets comprises: removing a panel from the flight vehicle exterior; attaching a vibration-damping blanket to a back surface of the removed panel; and installing the panel with attached vibration-damping blanket on the flight vehicle with the exterior surface of the panel forming part of the flight vehicle exterior. In one embodiment, the vibration-damping blanket comprises polymeric (e.g., aromatic polyamide) fibers in a nonwoven structure.

Abstract: A method and apparatus for identifying deformation of a structure. Training deformation data is identified for each training case in a plurality of training cases. Training strain data is identified for each training case in the plurality of training cases. The training deformation data and the training strain data are configured for use by a heuristic model to increase an accuracy of output data generated by the heuristic model. A group of parameters for the heuristic model is adjusted using the training deformation data and the training strain data for the each training case in the plurality of training cases such that the heuristic model is trained to generate estimated deformation data for the structure based on input strain data. The estimated deformation data has a desired level of accuracy.

Abstract: A sensor device for monitoring and testing for potential corrosion of structural elements is disclosed comprising a soluble material disposed adjacent to at least one conductor in a transmission line that reacts to the presence of moisture causing a detectable change in an electrical property of the conductor. The conductor may comprise a conductive ink that is disrupted when the soluble material dissolves beneath it. Alternately, the nonconductive soluble membrane may separate two conductors and moisture causes a disruption in the soluble membrane allowing the two conductors to short. Detected changes in the electrical properties of the one or more conductors can be used to indicate potential corrosion or structural imparement in the structural element. Connection to the sensor device may be through a connector or using a wireless reader which remotely energizes the sensor device comprising one or more RFID chips.

Abstract: Vibration-damping blankets are attached to the back surfaces of fairing panels of a flight vehicle (e.g., an aircraft or spacecraft) to reduce vibration, fatigue, structure and airborne transmitted energy, and cabin noise. In one case, the flight vehicle fairing has an exterior comprising exterior surfaces of a multiplicity of removable panels. A method of retrofitting the flight vehicle with vibration-damping blankets comprises: removing a panel from the flight vehicle exterior; attaching a vibration-damping blanket to a back surface of the removed panel; and installing the panel with attached vibration-damping blanket on the flight vehicle with the exterior surface of the panel forming part of the flight vehicle exterior. In one embodiment, the vibration-damping blanket comprises polymeric (e.g., aromatic polyamide) fibers in a nonwoven structure.

Abstract: A structural health management device, system and method are provided for facilitating the inspection of a structure, such as in accordance with a condition-based maintenance strategy. A structural health management device may include a radio frequency identification (RFID) tag and at least one sense line communicably coupled to the RFID tag and configured to extend at least partially along a workpiece. The sense line may be formed of different materials depending upon the objective of the inspection. The RFID tag may include processing circuitry and an antenna configured to facilitate offboard communication. The processing circuitry may be configured to interrogate the at least one sense line to determine a change in continuity which is indicative of a change in the structural health of the workpiece. The structural health management device may therefore detect the onset of structural issues in a timely manner.

Abstract: A structural health management device, system and method are provided for facilitating the inspection of a structure, such as in accordance with a condition-based maintenance strategy. A structural health management device may include a radio frequency identification (RFID) tag and at least one sense line communicably coupled to the RFID tag and configured to extend at least partially along a workpiece. The sense line may be formed of different materials depending upon the objective of the inspection. The RFID tag may include processing circuitry and an antenna configured to facilitate offboard communication. The processing circuitry may be configured to interrogate the at least one sense line to determine a change in continuity which is indicative of a change in the structural health of the workpiece. The structural health management device may therefore detect the onset of structural issues in a timely manner.

Abstract: A sensor device for monitoring and testing for potential corrosion of structural elements is disclosed comprising a soluble material disposed adjacent to at least one conductor in a transmission line that reacts to the presence of moisture causing a detectable change in an electrical property of the conductor. The conductor may comprise a conductive ink that is disrupted when the soluble material dissolves beneath it. Alternately, the nonconductive soluble membrane may separate two conductors and moisture causes a disruption in the soluble membrane allowing the two conductors to short. Detected changes in the electrical properties of the one or more conductors can be used to indicate potential corrosion or structural imparement in the structural element. Connection to the sensor device may be through a connector or using a wireless reader which remotely energizes the sensor device comprising one or more RFID chips.

Abstract: A transducer assembly may include a first layer of dielectric material and a pair of electrically conductive traces adjacent to the first dielectric layer. Each of the electrically conductive traces may include a first contact pad and a second contact pad. The first layer of dielectric material may include a pair of vias or openings formed therein to expose each of the first contact pads. A second layer of dielectric material may be attached to the first layer of dielectric material with the pair of electrically conductive traces disposed between the first and second layers of dielectric material. A transducer may be attached to the second layer of dielectric material and each second contact pad may be electrically connected to the transducer.

Abstract: A method for quantifying damage in a test structure having a plurality of transducer units coupled to at least one portion of the test structure includes: (a) training an evaluating algorithmic system coupled with the transducer units to establish a trained algorithmic system able to recognize a plurality of characteristics of signals traversing a plurality of paths through a training structure substantially similar to the test structure after the training structure is damaged. Each path is situated between a respective pair of transducer units coupled to the training structure; the plurality of characteristics relates each path to a plurality of physical aspects of the damage. A trained algorithmic system is employed to recognize the plurality of characteristics of signals traversing paths in the test structure to effect the quantifying. The plurality of physical aspects includes less than ten physical aspects.

Abstract: A method for quantifying damage in a test structure having a plurality of transducer units coupled to at least one portion of the test structure includes: (a) training an evaluating algorithmic system coupled with the transducer units to establish a trained algorithmic system able to recognize a plurality of characteristics of signals traversing a plurality of paths through a training structure substantially similar to the test structure after the training structure is damaged. Each path is situated between a respective pair of transducer units coupled to the training structure; the plurality of characteristics relates each path to a plurality of physical aspects of the damage. A trained algorithmic system is employed to recognize the plurality of characteristics of signals traversing paths in the test structure to effect the quantifying. The plurality of physical aspects includes less than ten physical aspects.

Abstract: A method for diagnosing the health of a transducer may include transmitting a signal to a transducer to cause the transducer to transmit a stress wave into an object being monitored, wherein the signal has a predetermined frequency range or bandwidth. The method may also include receiving response data for the transducer and transforming the response data to data representative of an impedance curve of impedance versus frequency for the predetermined frequency range. The method may further include extracting selected parameters from the impedance curve to diagnose the health of the transducer.

Abstract: A method for diagnosing the health of a transducer may include transmitting a signal to a transducer to cause the transducer to transmit a stress wave into an object being monitored, wherein the signal has a predetermined frequency range or bandwidth. The method may also include receiving response data for the transducer and transforming the response data to data representative of an impedance curve of impedance versus frequency for the predetermined frequency range. The method may further include extracting selected parameters from the impedance curve to diagnose the health of the transducer.

Abstract: A transducer assembly may include a first layer of dielectric material and a pair of electrically conductive traces adjacent to the first dielectric layer. Each of the electrically conductive traces may include a first contact pad and a second contact pad. The first layer of dielectric material may include a pair of vias or openings formed therein to expose each of the first contact pads. A second layer of dielectric material may be attached to the first layer of dielectric material with the pair of electrically conductive traces disposed between the first and second layers of dielectric material. A transducer may be attached to the second layer of dielectric material and each second contact pad may be electrically connected to the transducer.

Abstract: Structural analysis systems and methods are disclosed. One embodiment provides a method for analyzing a structure includes receiving damage image data; converting the received image data into analysis data in an analyzable format; performing a structural analysis on the analysis data; and outputting the results of the structural analysis. The system includes a computer or other processing device that is capable of analyzing a structure. The system receives damage image data; converts the received image data into analysis data in an analyzable format; performs a structural analysis on the analysis data; and outputs the results of the structural analysis.

Abstract: Structural analysis systems and methods are disclosed. One embodiment provides a method for analyzing a structure includes receiving damage image data; converting the received image data into analysis data in an analyzable format; performing a structural analysis on the analysis data; and outputting the results of the structural analysis. The system includes a computer or other processing device that is capable of analyzing a structure. The system receives damage image data; converts the received image data into analysis data in an analyzable format; performs a structural analysis on the analysis data; and outputs the results of the structural analysis.