CEAS/AIAA/ICASE/NASA Langley International Forum on Aeroelasticity and Structural Dynamics 1999

The proceedings of a workshop sponsored by the Confederation of European Aerospace Societies (CEAS), the American Institute of Aeronautics and Astronautics (AIAA), the National Aeronautics and Space Administration (NASA), Washington, D.C., and the Institute for Computer Applications in Science and Engineering (ICASE), Hampton, Virginia, and held in Williamsburg, Virginia June 22-25, 1999 represent a collection of the latest advances in aeroelasticity and structural dynamics from the world community. Research in the areas of unsteady aerodynamics and aeroelasticity, structural modeling and optimization, active control and adaptive structures, landing dynamics, certification and qualification, and validation testing are highlighted in the collection of papers. The wide range of results will lead to advances in the prediction and control of the structural response of aircraft and spacecraft

Dynamic behavior of smart thin-walled composite structures

Ова докторска дисертација бави се оптимизацијом и активним пригушењем вибрација паметних танкозидних композитних структура помоћу пиезоелектричних актуатора и сензора. Развијен је математички модел плочасте композитне структуре са интегрисаним актуаторима и сензорима. Проблем је дефинисан методом коначних елемената базиране на теорији смицања трећег реда. Конститутивне једначине и веза између померања и деформација су линеарне. У даљем раду, представљен је проблем одређивања оптималних величина, положаја и оријентација актуатор – сензор парова, а затим су дефинисане функција циља и ограничења. Такође, извршена је синтеза методе коначних елемената и оптимизације ројем честица и применом дефинисаних критеријума оптимизације, извршена је оптимизација величине, положаја и оријентације пет актуатор-сензор парова на квадратним укљештеним композитним плочама са следећим конфигурацијама слојева: (90°/0°/90°/0°)S, (90°/0°/90°/0°/90°/0°/90°/0°) и (45°/-45°/45°/-45°/45°/-45°/45°/-45°). Актуатори и сензори, који се разматрају у овој дисертацији, једнаких су димензија, исто су оријентисани и налазе се на супротним странама плоче: актуатор на горњој страни, а сензор на доњој страни плоче. Ради превазилажења проблема приликом синтезе конвенционалних управљачких алгоритама који се јављају услед стохастичне природе вибрација, представљен је оптимизовани самоподешавајући фази-логички управљачки систем. Главна идеја овог управљачког система је праћење амплитуде и самоподешавање улазних скалирајућих фактора на основу амплитуде. Функције припадности су параметризоване, а оптимална комбинација параметара нађена је помоћу оптимизације ројем честица на основу дефинисаних критеријума оптимизације. Разматрана су два принципа закључивања: Мамдани принцип закључивања и Такаги-Сугено-Канг принцип закључивања нултог реда. Нумерички примери су дати за композитну конзолу и композитну укљештену плочу за слободне и принудне вибрације. За конзолу разматрана је једно-улазно- једно-излазна („Single input – single output“, „SISO“) конфигурација, а за плочу више-улазно-више-излазна („Multiple inputs – multiple outputs“, „MIMO“) конфигурација. Извршено је поређење перформанси приликом употребе различитих принципа фази закључивања, као и поређење оптимизованог самоподешавајућег фази-логичког управљачког система са линеарно-квадратним регулатором.This doctoral dissertation deals with optimization and active vibration suppression of smart thin-walled composite structures by using piezoelectric actuators and sensors. Mathematical model of plate composite structure with integrated actuators and sensors is developed. The problem is formulated using the finite element method based on the third order shear deformation theory. Constitutive equations and the strain - displacement relations are linear. In further work, the problem of determination of optimal sizes, positions and orientations of actuator – sensor pairs are presented and, after that, objective functions and constraints are defined. Also, the integration of finite element method and particle swarm optimization is performed and using defined optimization criteria, the optimization of sizes, positions and orientations of five actuator – sensor pairs on square cantilever composite is performed. The cantilever composite plates have following orientation of layers: (90°/0°/90°/0°)S, (90°/0°/90°/0°/90°/0°/90°/0°) и (45°/-45°/45°/-45°/45°/-45°/45°/-45°). Actuators and sensors considered in dissertation are collocated. In order to overcome problems during conventional control algorithm synthesis which occur due to vibration’s stochastic nature, the optimized self-tuning fuzzy logic controller is presented. The main idea of proposed controller is amplitude monitoring and self-tuning of input scaling factors based on amplitude. Membership functions are parameterized and optimal combination of parameters are found by using the particle swarm optimization method based on previously defined optimization criteria. Two inference methods are considered: the Mamdani and zero-order Takagi-Sugeno-Kang inference methods. Numerical studies are provided for composite cantilever beam and composite cantilever plate for both free and forced vibrations. Single-input single-output (SISO) configuration is considered for the cantilever beam and multiple-input multiple-output (MIMO) configuration is considered for cantilever plate. Comparisons of control performances for these two types of inference methods as well as optimized self-tuning fuzzy logic controller with linear quadratic regulator are performed

Acoustic and Elastic Waves: Recent Trends in Science and Engineering

The present Special Issue intends to explore new directions in the field of acoustics and ultrasonics. The interest includes, but is not limited to, the use of acoustic technology for condition monitoring of materials and structures. Topics of interest (among others): • Acoustic emission in materials and structures (without material limitation) • Innovative cases of ultrasonic inspection • Wave dispersion and waveguides • Monitoring of innovative materials • Seismic waves • Vibrations, damping and noise control • Combination of mechanical wave techniques with other types for structural health monitoring purposes. Experimental and numerical studies are welcome

Enhancing the Practical Applicability of Smart Tuned Mass Dampers in High-Rise Civil Engineering Structures

The ability of bones to concentrate material where the body needs most of its strength and the ability of trees to spread roots in search of moisture rich locations are only a few amongst the many examples of nature’s way of building adaptive “structures”. Even though civil engineering structures often appear inefficient, static and cumbersome, a new era of structural design aims to alter the status quo by mimicking nature’s way. This suggested adaptation process in civil structures often takes the form of passive, active and semi- active control. Through direct comparison of these methods, semi-active control is shown to combine the benefits of both active and passive systems and can be arguably considered the next step in improving dynamic structural performance; however the applicability of this exciting and novel for the structural engineering field technology, is not all-embracing. In order to enhance the development of this promising technology and contribute on the creation of a new era of “smart & thinking” structures that encompass an unconventional form of performance based design, this study aimed to develop enabling technologies and tools that enhance the selling strengths of semi-active and smart control using tuned-mass dampers. The original contributions to knowledge in this work are divided in three aspects. Firstly, the investigation of the influence of control algorithms on smart tuned-mass damper equipped high-rise structures, for which practical limitations have been taken into account. Leading to conclusion on the conditions for which each algorithm exhibits superior performance over the other. Secondly, the development of a fail-safe novel semi-active hybrid device configuration that enables performance gains similar to the active mass damper at considerably lower actuation and power demands. Finally, the development of a simple and robust at all gains control algorithm based on the modification of one of the most widely used controller in the engineering industry, namely the proportional-integral-derivative controller

A Summary of NASA Rotary Wing Research: Circa 20082018

The general public may not know that the first A in NASA stands for Aeronautics. If they do know, they will very likely be surprised that in addition to airplanes, the A includes research in helicopters, tiltrotors, and other vehicles adorned with rotors. There is, arguably, no subsonic air vehicle more difficult to accurately analyze than a vehicle with lift-producing rotors. No wonder that NASA has conducted rotary wing research since the days of the NACA and has partnered, since 1965, with the U.S. Army in order to overcome some of the most challenging obstacles to understanding the behavior of these vehicles. Since 2006, NASA rotary wing research has been performed under several different project names [Gorton et al., 2015]: Subsonic Rotary Wing (SRW) (20062012), Rotary Wing (RW) (20122014), and Revolutionary Vertical Lift Technology (RVLT) (2014present). In 2009, the SRW Project published a report that assessed the status of NASA rotorcraft research; in particular, the predictive capability of NASA rotorcraft tools was addressed for a number of technical disciplines. A brief history of NASA rotorcraft research through 2009 was also provided [Yamauchi and Young, 2009]. Gorton et al. [2015] describes the system studies during 20092011 that informed the SRW/RW/RVLT project investment prioritization and organization. The authors also provided the status of research in the RW Project in engines, drive systems, aeromechanics, and impact dynamics as related to structural dynamics of vertical lift vehicles. Since 2009, the focus of research has shifted from large civil VTOL transports, to environmentally clean aircraft, to electrified VTOL aircraft for the urban air mobility (UAM) market. The changing focus of rotorcraft research has been a reflection of the evolving strategic direction of the NASA Aeronautics Research Mission Directorate (ARMD). By 2014, the project had been renamed the Revolutionary Vertical Lift Technology Project. In response to the 2014 NASA Strategic Plan, ARMD developed six Strategic Thrusts. Strategic Thrust 3B was defined as the Ultra-Efficient Commercial VehiclesVertical Lift Aircraft. Hochstetler et al. [2017] uses Thrust 3B as an example for developing metrics usable by ARMD to measure the effectiveness of each of the Strategic Thrusts. The authors provide near-, mid-, and long-term outcomes for Thrust 3B with corresponding benefits and capabilities. The importance of VTOL research, especially with the rapidly expanding UAM market, eventually resulted in a new Strategic Thrust (to begin in 2020): Thrust 4Safe, Quiet, and Affordable Vertical Lift Air Vehicles. The underlying rotary wing analysis tools used by NASA are still applicable to traditional rotorcraft and have been expanded in capability to accommodate the growing number of VTOL configurations designed for UAM. The top-level goal of the RVLT Project remains unchanged since 2006: Develop and validate tools, technologies and concepts to overcome key barriers for vertical lift vehicles. In 2019, NASA rotary wing/VTOL research has never been more important for supporting new aircraft and advancements in technology. 2 A decade is a reasonable interval to pause and take stock of progress and accomplishments. In 10 years, digital technology has propelled progress in computational efficiency by orders of magnitude and expanded capabilities in measurement techniques. The purpose of this report is to provide a compilation of the NASA rotary wing research from ~2008 to ~2018. Brief summaries of publications from NASA, NASA-funded, and NASA-supported research are provided in 12 chapters: Acoustics, Aeromechanics, Computational Fluid Dynamics (External Flow), Experimental Methods, Flight Dynamics and Control, Drive Systems, Engines, Crashworthiness, Icing, Structures and Materials, Conceptual Design and System Analysis, and Mars Helicopter. We hope this report serves as a useful reference for future NASA vertical lift researchers

NASA SBIR abstracts of 1990 phase 1 projects

The research objectives of the 280 projects placed under contract in the National Aeronautics and Space Administration (NASA) 1990 Small Business Innovation Research (SBIR) Phase 1 program are described. The basic document consists of edited, non-proprietary abstracts of the winning proposals submitted by small businesses in response to NASA's 1990 SBIR Phase 1 Program Solicitation. The abstracts are presented under the 15 technical topics within which Phase 1 proposals were solicited. Each project was assigned a sequential identifying number from 001 to 280, in order of its appearance in the body of the report. The document also includes Appendixes to provide additional information about the SBIR program and permit cross-reference in the 1990 Phase 1 projects by company name, location by state, principal investigator, NASA field center responsible for management of each project, and NASA contract number

Engineering Dynamics and Life Sciences

From Preface: This is the fourteenth time when the conference “Dynamical Systems: Theory and Applications” gathers a numerous group of outstanding scientists and engineers, who deal with widely understood problems of theoretical and applied dynamics. Organization of the conference would not have been possible without a great effort of the staff of the Department of Automation, Biomechanics and Mechatronics. The patronage over the conference has been taken by the Committee of Mechanics of the Polish Academy of Sciences and Ministry of Science and Higher Education of Poland. It is a great pleasure that our invitation has been accepted by recording in the history of our conference number of people, including good colleagues and friends as well as a large group of researchers and scientists, who decided to participate in the conference for the first time. With proud and satisfaction we welcomed over 180 persons from 31 countries all over the world. They decided to share the results of their research and many years experiences in a discipline of dynamical systems by submitting many very interesting papers. This year, the DSTA Conference Proceedings were split into three volumes entitled “Dynamical Systems” with respective subtitles: Vibration, Control and Stability of Dynamical Systems; Mathematical and Numerical Aspects of Dynamical System Analysis and Engineering Dynamics and Life Sciences. Additionally, there will be also published two volumes of Springer Proceedings in Mathematics and Statistics entitled “Dynamical Systems in Theoretical Perspective” and “Dynamical Systems in Applications”