KEYWORDS: Satellites, Sensors, Microcontrollers, Metals, Signal generators, Vibration, Semiconducting wafers, Detection and tracking algorithms, Switches, Analog to digital converters
Average satellite lifetime in orbit has been gradually increasing since the advent of the space industry. With the increase in satellite lifespan on orbit it is becoming increasingly economically advantageous to refuel and conduct in-orbit servicing rather than launching new satellites. This presents a challenging problem of automatic docking for refueling. Traditionally, docking mechanisms have used either a physical switch, a force sensor, a torque sensor, or a combination of the three. Traditional docking verification techniques using those sensors are suboptimal for use in an orbital servicing satellite as customer’s satellite mass can vary in a wide range while docking velocity also varies. In addition, the refueling system produces a complex pattern of mechanical signals during docking, which is challenging to classify. For this reason, an SHM system with small unobtrusive piezoelectric sensors was proposed to identify and characterize satellite docking. It was decided that the passive monitoring of the docking is preferable overactive methods not to interfere with satellite dynamics and reduce power use. The mechanical waves resulted from the satellite’s docking momentum annulment, thrusters, electrical motors, and mechanical component deployment were passively monitored using an array of piezoelectric wafer sensors. Features in mechanical signals corresponding to the docking were distinguished from other mechanical events normal to satellite’s operation. An algorithm was developed that utilize features specific to docking to classify the quality of the docking engagement including potential false positives and misalignment issues. This algorithm was embedded in a real-time microprocessor which was used to capture passive ultrasonic signals and run the associated data analysis algorithm. Experiments conducted on a laboratory scale docking imitator suggested the applicability of the proposed approach and verified performance on the data acquisition and classification system on exemplary signals.
The spline component of gearbox structure is a non-redundant element that requires early detection of flaws for preventing catastrophic failures. The acoustic emission (AE) method is a direct way of detecting active flaws; however, the method suffers from the influence of background noise and location/sensor based pattern recognition method. It is important to identify the source mechanism and adapt it to different test conditions and sensors. In this paper, the fatigue crack growth of a notched and flattened gearbox spline component is monitored using the AE method in a laboratory environment. The test sample has the major details of the spline component on a flattened geometry. The AE data is continuously collected together with strain gauges strategically positions on the structure. The fatigue test characteristics are 4 Hz frequency and 0.1 as the ratio of minimum to maximum loading in tensile regime. It is observed that there are significant amount of continuous emissions released from the notch tip due to the formation of plastic deformation and slow crack growth. The frequency spectra of continuous emissions and burst emissions are compared to understand the difference of sudden crack growth and gradual crack growth. The predicted crack growth rate is compared with the AE data using the cumulative AE events at the notch tip. The source mechanism of sudden crack growth is obtained solving the inverse mathematical problem from output signal to input signal. The spline component of gearbox structure is a non-redundant element that requires early detection of flaws for preventing catastrophic failures. In this paper, the fatigue crack growth of a notched and flattened gearbox spline component is monitored using the AE method The AE data is continuously collected together with strain gauges. There are significant amount of continuous emissions released from the notch tip due to the formation of plastic deformation and slow crack growth. The source mechanism of sudden crack growth is obtained solving the inverse mathematical problem from output signal to input signal.
KEYWORDS: Teeth, Wave propagation, Ultrasonics, Structural health monitoring, Finite element methods, Damage detection, Sensors, Wave plates, 3D modeling, Algorithm development
Gearbox components of aerospace structures are typically made of brittle materials with high fracture toughness, but susceptible to fatigue failure due to continuous cyclic loading. Structural Health Monitoring (SHM) methods are used to monitor the crack growth in gearbox components. Damage detection methodologies developed in laboratory-scale experiments may not represent the actual gearbox structural configuration, and are usually not applicable to real application as the vibration and wave properties depend on the material, structural layers and thicknesses. Also, the sensor types and locations are key factors for frequency content of ultrasonic waves, which are essential features for pattern recognition algorithm development in noisy environments. Therefore, a deterministic damage detection methodology that considers all the variables influencing the waveform signature should be considered in the preliminary computation before any experimental test matrix. In order to achieve this goal, we developed two dimensional finite element models of a gearbox cross section from front view and shaft section. The cross section model consists of steel revolving teeth, a thin layer of oil, and retention plate. An ultrasonic wave up to 1 MHz frequency is generated, and waveform histories along the gearbox are recorded. The received waveforms under pristine and cracked conditions are compared in order to analyze the crack influence on the wave propagation in gearbox, which can be utilized by both active and passive SHM methods.
Structural Health Monitoring technologies have the potential to reduce life-cycle costs and improve reliability for aircraft. Previous research conducted by the Metis Design Corporation has demonstrated the ability of Lamb wave methods to provide reliable information regarding the presence, location and type of damage in coupon-level specimens. Several critical system components have been developed during the course of this research, including circuitry and packaging, and integrated into the Monitoring & Evaluation Technology Integration (M.E.T.I.) Disk. In order to demonstrate the validity of M.E.T.I.-Disks for aircraft applications, a testbed has been fabricated by dividing a 1/8" plate of aircraft-grade aluminum into four equal quadrants with several c-channels. M.E.T.I.-Disk nodes were then placed in the center of each quadrant, and data was collected and interpreted by the METISv2.10 software package. The results produced by this software validated the M.E.T.I.-Disk by using a single undamaged cell to calibrate the system, and then correctly identify that there was no damage present in the remaining quadrants. Next, representative damage was introduced into several combinations of the quadrants, and the software was executed again to query the structure. The resulting data revealed the presence and location of damage, while still identifying the two undamaged regions.
Structural Health Monitoring (SHM) technologies have the potential to realize economic benefits in a broad range of commercial and defense markets. Previous research conducted by Metis Design and MIT has demonstrated the ability of Lamb waves methods to provide reliable information regarding the presence, location and type of damage in composite specimens. The present NSF funded program was aimed to study manufacturing, packaging and interface concepts for critical SHM components. The intention is to be able to cheaply manufacture robust actuating/sensing devices, and isolate them from harsh operating environments including natural, mechanical, or electrical extremes. Currently the issues related to SHM system durability have remained undressed. During the course of this research several sets of test devices were fabricated and packaged to protect the piezoelectric component assemblies for robust operation. These assemblies were then tested in hot and wet conditions, as well as in electrically noisy environments. Future work will aim to package the other supporting components such as the battery and wireless chip, as well as integrating all of these components together for operation. SHM technology will enable the reduction or complete elimination of scheduled inspections, and will allow condition-based maintenance for increased reliability and reduced overall life-cycle costs.
In a continuing effort to examine the effectiveness of Lamb wave methods for the health monitoring of composite structures, this paper presents the conclusions of an analytical and experimental study optimizing piezoelectric patches to detect damage within composite laminates. Previous research has demonstrated the ability of Lamb waves to provided useful information about the presence of damage in simple narrow coupons, and they have yielded the possibility of estimating severity and location of damage as well. During the course of this NRO funded research program, several types of piezoelectric materials in various configurations were analyzed in order to produce the highest force actuator and best resolution sensor at the lowest power level. Consideration was also placed towards directionality of wave propagation, and durability, reliability and reproducibility of the sensing patch itself. Experiments were then carried out on narrow coupon laminates to qualify and tune these actuating/sensing patches. New algorithms were used to filter and decompose the resulting signals to more efficiently detect the presence of damage for automated use, and gather information relating to the damage type, severity and location. SHM technologies will enable condition-based maintenance for efficient structural design, will reduced overall life-cycle costs, and eliminate scheduled inspections.
Cost-effective and reliable damage detection is critical for the utilization of composite materials. This paper presents the conclusions of an experimental and analytical survey of candidate methods for in-situ damage detection in composite structures. Experimental results are presented for the application of modal analysis and Lamb wave techniques to quasi-isotropic graphite/epoxy test specimens containing representative damage. Piezoelectric patches were used as actuators and sensors for both sets of experiments. Modal analysis methods were reliable for detecting small amounts of global damage in a simple composite structure. By comparison, Lamb wave methods were sensitive to all types of local damage present between the sensor and actuator, provided useful information about damage presence and severity, and present the possibility of estimating damage type and location. Analogous experiments were also performed for more complex built-up structures. These techniques are suitable for structural health monitoring applications since they can be applied with low power conformable sensors and can provide useful information about the state of a structure during operation. Piezoelectric patches could also be used as multipurpose sensors to detect damage by a variety of methods such as modal analysis, Lamb wave, acoustic emission and strain based methods simultaneously, by altering driving frequencies and sampling rates. This paper present guidelines and recommendations drawn from this research to assist in the design of a structural health monitoring system for a vehicle. These systems will be an important component in future designs of air and spacecraft to increase the feasibility of their missions.
Cost effective and reliable damage detection is critical for the utilization of composite materials in structural applications. Non-destructive evaluation techniques (e.g. ultrasound, radiography, infra-red imaging) are available for use during standard repair and maintenance cycles, however by comparison to the techniques used for metals these are relatively expensive and time consuming. This paper presents part of an experimental and analytical survey of candidate methods for the detection of damage in composite materials. The experimental results are presented for the application of modal analysis techniques applied to rectangular laminated graphite/epoxy specimens containing representative damage modes, including delamination, transverse ply cracks and through-holes. Changes in natural frequencies and modes were then found using a scanning laser vibrometer, and 2-D finite element models were created for comparison with the experimental results. The models accurately predicted the response of the specimems at low frequencies, but the local excitation and coalescence of higher frequency modes make mode-dependent damage detection difficult and most likely impractical for structural applications. The frequency response method was found to be reliable for detecting even small amounts of damage in a simple composite structure, however the potentially important information about damage type, size, location and orientation were lost using this method since several combinations of these variables can yield identical response signatures.
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