The development of new, smart materials capable of intrinsically detecting and communicating the occurrence of
external loads and resultant damage present in a material will be crucial in the advancement of future structural health
monitoring (SHM) and nondestructive evaluation (NDE) technologies. Traditionally, many SHM and NDE approaches
have relied on the use of physical sensors to monitor a structure for damage, but are often hindered by their requirements
for power consumption and large-scale data collection. In this work, we seek to evaluate the effectiveness of ultrasmall,
white-light emitting Cadmium Selenide quantum dots (CdSe QDs) as an alternative to providing in-situ material state
monitoring capabilities, while also aiming to reduce reliance on data collection and power consumption to effectively
monitor a material and structure for damage. To achieve this goal, CdSe QDs are embedded in an optically clear epoxy
composite matrix and exposed to external mechanical loadings. Initial results show a corresponding relationship
between the shifts in observed emission spectra and external load for samples containing CdSe QDs. The effectiveness
of CdSe QDs as a surface strain gauge on aluminum and fiberglass are also investigated in this paper. By monitoring
changes in the emission spectra for materials containing CdSe QDs before, during and after the application of external
loads, the effectiveness of CdSe QDs for communicating the occurrence of external loads acting on a material and
detecting changes in material state is evaluated.
Current limitations for diagnosing mineralization state of tooth enamel can lead to improper surgical treatments. A method is investigated by which the tooth health state is characterized according to its thermal response, which is hypothesized to be sensitive to increased porosity in enamel that is caused by demineralization. Several specimens consisting of previously extracted human teeth a re prepared by exposure to Streptococcus mutans A32-2 in trypticase-soy-borth supplemented with 5% sucrose at 37°C for 3 or 6 days to de-mineralize two 1×1mm2-windows on each tooth. One of these windows is then re-mineralized with 250 or 1,100ppm-F as NaF for 10 days by pH-cyclic-model. Pulse thermography is used to measure the thermal response of these sections as well as the sound (healthy) portions of the specimen. A spatial profile of the thermal parameters of the specimens is then extracted from the thermography data and are used to compare the sound, de-mineralized, and re-mineralized areas. Results show that the thermal parameters are sensitive to the mineralization state of the tooth and that this method has the potential to accurately and quickly characterize the mineralization state of teeth, thereby allowing future dentists to make informed decisions regarding the best treatment for teeth that have experienced demineralization.
Improper bonding of composite structures can result in close contact cracks under compressive stresses, called kissing
bonds. These bond defects are very difficult to detect using conventional inspection techniques such as tap testing or
local ultrasonic scanning and can lead to local propagation of damage if the structure is subjected to crack opening
stresses.
A method is investigated for identifying kissing bonds in composite material repairs based on vibration measurements.
A damage feature of the kissing bond is extracted from the response of the input-output measurement that is a function of
the structural path. This path exhibits local decoupling associated with the close contact cracks. Experimental vibration
measurements from sandwich composite materials are presented along with the results of the damage detection algorithm
for the healthy sections of the material and the kissing bond sections.
A vibration based inspection technique could increase the ability to detect kissing bonds in composite material repairs
while decreasing inspection time. Benefits of this method of identification over conventional techniques include its
robust, objective damage detection methodology and the reduced requirement for specimen preparation and surface
texture when compared to ultrasonic scanning.
While semi-active suspension systems have been shown to be effective in the real-time optimization of vehicle ride and
handling, these systems also present a means for system interrogation and damage detection. This research demonstrates
the ability to monitor the condition of a ground vehicle by utilizing a passively tunable suspension system to
systematically alter the suspension parameters in order to probe the system response. By modulating the suspension
parameters at a particular corner of the vehicle, or combinations of corners, selected operational modes of the sprung and
unsprung masses can be probed providing an increased ability to detect and locate damage in certain vehicle
components. The experimental data presented demonstrates that the ability to detect damage was increased by 16.3%
and 22.5% for the two simulated damage conditions using the suspension probing technique.
A major benefit of the active probing method described in this paper is that the associated damage index is based only on
one specific vehicle's response over time. A massive database of historical data from similar vehicles is not required.
The active probing method also benefits from transducers already integrated for the control of a typical semi-active
suspension system. The benefits of an on-board health monitoring system can be realized with minimal added cost, by
adding only a small number of additional sensors. The ability to detect vehicle damage during operation can be
extremely advantageous in terms of safety and condition-based maintenance.
Fiberglass sandwich panels are tested to study a vibration-based method for locating damage in composite materials.
This method does not rely on a direct comparison of the natural frequencies, mode shapes, or residues in the forced
vibration response data. Specifically, a nonlinear system identification based method for damage detection is sought that
reduces the sensitivity of damage detection results to changes in vibration measurements due to variations in boundary
conditions, environmental conditions, and material properties of the panel. Damage mechanisms considered include a
disbond between the core and face sheet and a crack within the core. A panel is excited by a skewed piezoelectric
actuator over a broad frequency range while a three-dimensional scanning laser vibrometer measures the surface velocity
of the panel along three orthogonal axes. The forced frequency response data measured using the scanning laser
vibrometer at multiple excitation amplitudes is processed to identify areas of the panel that exhibit significant nonlinear
response characteristics. It is demonstrated that these localized nonlinearities in the panel coincide with the damaged
areas of the composite material. Because changes in the measured frequency response functions due to nonlinear
distortions associated with the damage can be identified without comparing the vibration data to a reference (baseline)
signature of the undamaged material, this vibration technique for damage detection in composite materials exhibits less
sensitivity to variations in the underlying linear characteristics than traditional methods. It is also demonstrated that the
damage at a given location can be classified as either due to a disbond or core crack because these two types of damage
produce difference signatures when comparing the multi-amplitude frequency response functions.
Rising energy prices and carbon emission standards are driving a fundamental shift from fossil fuels to alternative
sources of energy such as biofuel, solar, wind, clean coal and nuclear. In 2008, the U.S. installed 8,358 MW of new
wind capacity increasing the total installed wind power by 50% to 25,170 MW. A key technology to improve the
efficiency of wind turbines is smart rotor blades that can monitor the physical loads being applied by the wind and then
adapt the airfoil for increased energy capture. For extreme wind and gust events, the airfoil could be changed to reduce
the loads to prevent excessive fatigue or catastrophic failure. Knowledge of the actual loading to the turbine is also
useful for maintenance planning and design improvements. In this work, an array of uniaxial and triaxial accelerometers
was integrally manufactured into a 9m smart rotor blade. DC type accelerometers were utilized in order to estimate the
loading and deflection from both quasi-steady-state and dynamic events. A method is presented that designs an
estimator of the rotor blade static deflection and loading and then optimizes the placement of the sensor(s). Example
results show that the method can identify the optimal location for the sensor for both simple example cases and realistic
complex loading. The optimal location of a single sensor shifts towards the tip as the curvature of the blade deflection
increases with increasingly complex wind loading. The framework developed is practical for the expansion of sensor
optimization in more complex blade models and for higher numbers of sensors.
Techniques that analyze nonlinear transformations of high frequency vibration signals, such
as harmonic distortions and frequency modulations, termed nonlinear acoustic techniques (NAT),
offer unique advantages in detecting and characterizing structural damage. Linear techniques are
limited in their ability to detect small incipient damage and false indications caused by
environmental variability and structural features of comparable size to damage. Defects with
contact surfaces, such as cracks and delaminations, lead to strong nonlinear behavior in the form
of nonlinear frequency interactions. The advantage of NAT over traditional linear techniques in
detecting incipient small-scale nonlinear damage is demonstrated by initiating and identifying a
fatigue crack in notched beam specimens. Impact-modulation (IM) is utilized to identify
frequency modulation caused by the initiation of fatigue cracks. Piezo-stack actuators and modal
impact hammers are used to generate structural excitations measured using high frequency
accelerometers. Practical implementation issues of NAT are discussed, such as characterizing the
inherent nonlinearities of electronics, actuators and sensors for reliable defect characterization.
Fatigue tests on a stabilizer bar link of an automotive suspension system are used to initiate a crack and
grow the crack size. During these tests, slow sine sweeps are used to extract narrowband restoring forces across the stabilizer bar link. The restoring forces are shown to characterize the nonlinear changes in component internal forces due to crack growth. Broadband frequency response domain techniques are used to analyze the durability response data. Nonlinear frequency domain models of the dynamic transmissibility across the cracked region are shown to change as a function of crack growth. Higher order spectra are used to show the increase in nonlinear coupling of response frequency components with the appearance and growth of the crack. It is shown that crack growth can be detected and characterized by the changes in nonlinear indicators.
Filament-wound rocket motor casings are being considered by the United States Army for use in future lightweight
missile systems. As part of the design process, a real-time, minimal-sensing, quasi-active health-monitoring system is
being investigated. The health-monitoring scheme is quasi-active because abnormal loads acting on the structure are
identified passively, the input force is not measured directly, and the curve-fit estimate of the impact force is used to
update the frequency response functions (FRFs) that are functions of the system properties. This task traditionally
requires an active-interrogation technique for which the input force is known. The updated FRFs and the estimated
impact force can then be used in model-based damage-quantification methods. The proposed quasi-active approach to
health monitoring is validated both analytically with a lumped-parameter model and experimentally with a composite
missile casing. Minimal sensing is used in both models in order to reduce the complexity and cost of the system, but the
small number of measurement channels causes the system of equations used in the inverse problem for load
identification to be under-determined. However, a novel algorithm locates and quantifies over 3000 impacts at various
locations around the casing with over 98% success, and the FRF-correction process is successfully demonstrated.
This research demonstrates two methodologies for detecting cracks in a metal spindle housed deep within a vehicle wheel end assembly. First, modal impacts are imposed on the hub of the wheel in the longitudinal direction to
produce broadband elastic wave excitation spectra out to 7000 Hz. The response data on the flange is collected using
3000 Hz bandwidth accelerometers. It is shown using frequency response analysis that the crack produces a filter, which
amplifies the elastic response of the surrounding components of the wheel assembly. Experiments on wheel assemblies
mounted on the vehicle with the vehicle lifted off the ground are performed to demonstrate that the modal impact method
can be used to nondestructively evaluate cracks of varying depths despite sources of variability such as the half shaft
angular position relative to the non-rotating spindle.
Second, an automatic piezo-stack actuator is utilized to excite the wheel hub with a swept sine signal extending
from 20 kHz. Accelerometers are then utilized to measure the response on the flange. It is demonstrated using
frequency response analysis that the crack filters waves traveling from the hub to the flange.
A simple finite element model is used to interpret the experimental results. Challenges discussed include
variability from assembly to assembly, the variability in each assembly, and the high amount of damping present in each
assembly due to the transmission gearing, lubricant, and other components in the wheel end. A two-channel
measurement system with a graphical user interface for detecting cracks was also developed and a procedure was created
to ensure that operators properly perform the test.
This research experimentally implements a new method to identify the location and magnitude of a single impulsive excitation to ceramic body armor, which is supported on a compliant torso. The method could easily be extended to other flexibly supported components that undergo rigid body dynamics. Impact loads are identified in two steps. First, the location of the impact force is determined from time domain acceleration responses by comparing them to an array of reference acceleration time histories. Then based on the estimated location, reference frequency response functions are used to reconstruct the input force in the frequency domain through a least squares inverse problem. Experimental results demonstrate the validity of this method at both low energy excitations, which are produced by a medium modally-tuned impact hammer, and at high energy excitations, which are produced by dropping rods with masses up to 0.6 kilograms from a height of 2 meters. The maximum error in the estimated location or magnitude for the low energy excitations on the 10 cm square ceramic body armor was 7.07 mm with an average error of 1.09 mm. In comparing the estimated force for the low energy excitations to the force recorded by the transducer in the modal impact hammer, the maximum error in the predicted force amplitude was 6.78 percent and the maximum error in the predicted impulse was 6.44 percent. For the high energy excitations, which produced accelerations at the measurement locations up to 50 times greater than that of the low energy excitations, the maximum error in the predicted location of the input force was 15 mm with an average error of 6.64 mm. There was no force transducer to capture the input force on the body armor from the rod, but from non-energy-dissipative projectile motion equations the validity of the solutions was confirmed by comparing the impulses.
KEYWORDS: Acoustics, Structural health monitoring, Infrared radiation, Lamps, Temperature metrology, Thermography, System identification, Inspection, Damage detection, Data acquisition
The thermal protection system is an essential part of any launch vehicle. Standoff metallic thermal protection system (TPS) panels protect the vehicle from the hostile environment on the panel exterior; consequently, the panels are exposed to a variety of loads including high temperature thermal stresses, thermal shock, acoustic pressure, and foreign object impact. These loads can cause degradation in the health of mechanically attached metallic TPS panels in the form of, for example, face sheet buckling, deformation/cracking of standoff bolts and standoffs or wrinkling to thermal seals. In this work, two sets of experiments were performed. The first experiment aimed to partially recreate the acoustic environment that the TPS experiences during service by subjecting the panel to broadband noise broadcast from a loudspeaker. In this set of experiments, "damage" was introduced into the TPS by loosening standoff fasteners to represent cracked or warped bolts and a transmissibility-based damage index was implemented to detect and locate damage. The second experiment was designed to examine the variation in damage indices when the panel is subjected to combined thermo-acoustic loading. In this set of experiments, the panel was not subjected to any "damage"; instead, the exterior of the panel was heated with an infrared heat lamp while being excited by acoustic noise. It is demonstrated that the transmissibility-based damage indicator is a viable method for detecting and locating damage in the TPS panel. It is also shown that damage present in the panel may become more or less identifiable while the system is subjected to thermal loading. This paper was approved for unlimited public release on February 18, 2005; LA-UR-05-1192.
Vibration-based damage identification using embedded sensitivity functions is discussed. These sensitivity functions are computed directly from experimental frequency response functions and reflect changes in the forced response of structural systems when mass, damping or stiffness parameters are changed. The theory of embedded sensitivity functions is reviewed and applied to characterize damage in a simulated three degree-of-freedom system and a full-scale exhaust system with nonlinear characteristics. Linear damage is shown to be properly detected, located and quantified in theory and practice for structures with one damage mechanism by comparing embedded sensitivity functions with finite difference frequency response functions in undamaged and damaged test data. It is also shown using the exhaust system that false indications of damage due to nonlinear amplitude dependence can be avoided by developing nonlinear baseline models. Experimental results indicate that the technique is most effective when changes to frequency response functions are no larger than 10% to avoid distortions in the estimated perturbations due to variations in the sensitivity functions.
Environmental and operational variability due to changes in the excitation or any other variable can mimic or altogether obscure evidence of structural defects in measured data leading to false positive/negative diagnoses of damage and conservative/tolerant predictions of remaining useful life in structural health monitoring system. Diagnostic and prognostic errors like these in many types of commercial and defense-related applications must be eliminated if health monitoring is to be widely implemented in these applications. A theoretical framework of "dynamic similiarity" in which two sets of mathematical operators are utilized in one system/data model to distinguish damage from nonlinear, time-varying and stochastic events in the measured data is discussed in this paper. Because structural damage initiation, evolution and accumulation are nonlinear processes, the challenge here is to distinguish damage from nonlinear, time-varying and stochastic events in the measured data is discussed in this paper. Because structural damage initiation, evolution and accumulation are nonlinear processes, the challenge here is to distinguish abnormal from normal nonlinear dynamics, which are accentuated by physically or statistically non-stationary events in the operating environment. After discussing several examples of structural diagnosis and prognosis involving dynamic similarity, a simplifeid numerical finite element model of a helicopter blade with time-varying flexural stiffness on a nonlinear aerodynamic elastic foundation that is subjected to a stochastic base excitation is utilized to introduce and examine the effects of dynamic similarity on health monitoring systems. It is shown that environmental variability can be distinguished from structural damage using a physics-based model in conjunction with the dynamic similarity operators to develop more robust damage detection algorithms, which may prove to be more accurate and precise when operating conditions fluctuate.
This work aims to establish a nonlinear dynamics framework for diagnosis and prognosis in structural dynamic systems. The objective is to develop an analytically sound means for extracting features, which can be used to characterize damage, form modal-based input-output data in complex hybrid structures with heterogeneous materials and many components. Although systems like this are complex in nature, the premise of the work here is that damage initiates and evolves in the same phenomenological way regardless of the physical system according to nonlinear dynamic processes. That is, bifurcations occur in healthy systems as a result of damage. By projecting a priori the equations of motion of high-dimensional structural dynamic systems onto lower dimensional center, or so-called 'damage', manifolds, it is demonstrated that model reduction near bifurcations might be a useful way to identity certain features in the input- output data that are helpful in identifying damage. Normal forms describing local co-dimension one and two bifurcations are assumed to govern the initiation and evolution of damage in a low-order model. Real-world complications in damage prognosis involving spatial bifurcations, global bifurcation phenomena, and the sensitivity of damage to small changes in initial conditions are also briefly discussed.
Many different vibration-based dynamic input-output and output only data features have been used to identify structural damage and assess structural integrity. Since structural damage introduces linear or nonlinear variations into all of these features, all of them might give positive indications of damage but may not distinguish between linear or nonlinear types of damage. This information can sometimes be used to more reliably diagnose damage by first, helping to distinguish between damage, which is inherently nonlinear, and healthy nonlinearities in a baseline structure; and second, serving as an absolute damage prognosis indicator which, together with prior information about the structural mechanics, determined the degree to which a structure is damaged. A set of potential features that distinguish between linear and nonlinear damage are discussed here. These features are auto-regressive exogenous dynamic transmissiblity model coefficients in the frequency domain. The auto-regressive coefficients are used to characterize the nonlinear nature of damage states and the exogenous coefficients are used to characterize the linear nature of such states. After reviewing the theoretical development of this data model, experimental measurements from a three-story test structure are analyzed using these model coefficients and statistical features are extracted from the coefficients. By using two complementary features, a better indication of the severity of damage is obtained.
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