THE DESIGN AND ANALYSIS OF EXPERIMENTS. By Oscar Kempthorne. New York, John Wiley and Sons, Inc., 1952. 631 pp. $8.50. This book by a teacher of statistics (as well as a consultant for \"experimenters\") is a comprehensive study of the philosophical background for the statistical design of experiment. It is necessary to have some facility with algebraic notation and manipulation to be able to use the volume intelligently. The problems are presented from the theoretical point of view, without such practical examples as would be helpful for those not acquainted with mathematics. The mathematical justification for the techniques is given. As a somewhat advanced treatment of the design and analysis of experiments, this volume will be interesting and helpful for many who approach statistics theoretically as well as practically. With emphasis on the \"why,\" and with description given broadly, the author relates the subject matter to the general theory of statistics and to the general problem of experimental inference. MARGARET J. ROBERTSON

The Design and Analysis of Experiments

Fault detection, isolation, and reconfiguration (FDIR) is an important and challenging problem in many engineering applications and continues to be an active area of research in the control community. This paper presents a survey of the various model-based FDIR methods developed in the last decade. In the paper, the FDIR problem is divided into the fault detection and isolation (FDI) step, and the controller reconfiguration step. For FDI, we discuss various model-based techniques to generate residuals that are robust to noise, unknown disturbance, and model uncertainties, as well as various statistical techniques of testing the residuals for abrupt changes (or faults). We then discuss various techniques of implementing reconfigurable control strategy in response to faults.

A Survey of Fault Detection, Isolation, and Reconfiguration Methods

Past, present and future of nonlinear system identification in structural dynamics

Technology developments in structural health monitoring of large-scale bridges

https://people.duke.edu/~hpgavin/SystemID/References/Markovsky+VanHuffel-SP-2007.pdf

Overview of total least-squares methods

This paper presents a method to synthesize aircraft noise. The method provides designers with a tool for sound quality evaluation with which target sounds for future aircraft design can be developed. Quick and economic evaluations concerning the quality of sounds of different design alternatives or improvements on existing aircraft become possible. The method has the potential to become a crucial tool in the determination of the primary factors that determine the quality of aircraft sound.

A new method for aircraft noise synthesis

Big-end bearing knock is considered to be one of the common mechanical faults in internal combustion engines (IC engines). In this paper, a model has been built to simulate the effects of oversized...

Modelling and diagnosis of big-end bearing knock fault in internal combustion engines

The dynamic characterization of lightweight structures is particularly complex as the impact of the weight of sensors and instrumentation (cables, mounting of exciters…) can distort the results. Varying mass loading or constraint effects between partial measurements may determine several errors on the final conclusions. Frequency shifts can lead to erroneous interpretations of the dynamics parameters. Typically these errors remain limited to a few percent. Inconsistent data sets however can result in major processing errors, with all related consequences towards applications based on the consistency assumption, such as global modal parameter identification, model‐based damage detection and FRF‐based matrix inversion in substructuring, load identification and transfer path analysis [1]. This paper addresses the subject of accuracy in the context of the measurement of the dynamic properties of a particular lightweight structure. It presents a comprehensive comparative study between the use of accelerometer, laser vibrometer (scanning LDV) and PU‐probe (acoustic particle velocity and pressure) measurements to measure the structural responses, with as final aim the comparison of modal model quality assessment. The object of the investigation is a composite material blade from the main rotor of a helicopter. The presented results are part of an extensive test campaign performed with application of SIMO, MIMO, random and harmonic excitation, and the use of the mentioned contact and non‐contact measurement techniques. The advantages and disadvantages of the applied instrumentation are discussed. Presented are real‐life measurement problems related to the different set up conditions. Finally an analysis of estimated models is made in view of assessing the applicability of the various measurement approaches for successful fault detection based on modal parameters observation as well as in uncertain non‐deterministic numerical model updating.

Contact Versus Non-Contact Measurement of a Helicopter Main Rotor Composite Blade

** The need of improvements in engineering designs especially with composite materials is nowadays a major request of the aerospace industry . Deterministic approaches are unable to take into account all the variabilities that characterize composites properties without leading to oversized structures. This paper intends to give a description of the most commonly used methods for reliability -bas ed design optimization using the reliability index and the performance measure approaches to point out the advantages of the application of these methods in the design process. For this purpose, a Finite Element model has been created for an industrial com posite wing structure and realistic variability has been assigned to material properties and static load conditions. A range of test cases with gradually increasing complexity has then been defined, that allows the assessment of reported methods in terms o f accuracy, computation time and applicability in conjunction with Finite Element models.

Integration of Probabilistic Methodology in the Aerospace Design Optimization Process

As all experimental procedures, Experimental Modal Analysis (EMA) is subject to a wide range of potential testing and processing errors. The modal identification methods are sensitive to these errors, yielding modal results which are uncertain up to certain error bounds. The question hence is what these error bounds on test data and modal parameters are. In this paper, the studied source of uncertainty is related to the variance (noise) on the Frequency Response Function (FRF) measurements. Under the H1 assumptions and in single-input cases, the FRF variances can be computed from the coherences and the FRFs. In multiple-input cases, some more measurement functions are required. Advanced system identification methods like the Maximum Likelihood Estimator (MLE) and PolyMAX Plus have the possibility to take the uncertainty on the measurement data into account and to propagate the data uncertainty to (modal) parameter uncertainty. This paper will review FRF variance estimation techniques, including some pragmatic approaches. The basic concepts of Maximum Likelihood Estimation and the calculation of confidence bounds will be discussed. Some typical structural testing and modal analysis cases will be used as illustration of the discussed concepts.

Herman Van der Auweraer

Papers

A new method for aircraft noise synthesis

Modelling and diagnosis of big-end bearing knock fault in internal combustion engines

Contact Versus Non-Contact Measurement of a Helicopter Main Rotor Composite Blade

Integration of Probabilistic Methodology in the Aerospace Design Optimization Process

Uncertainty propagation in Experimental Modal Analysis