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Deflection Based Structural Loads Estimation From The Active Aeroelastic Wing F A 18 Aircraft
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Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723718212 Total Pages :28 pages Book Rating :4.7/5 (182 download)
Book Synopsis Deflection-Based Structural Loads Estimation from the Active Aeroelastic Wing F/A-18 Aircraft by : National Aeronautics and Space Adm Nasa
Download or read book Deflection-Based Structural Loads Estimation from the Active Aeroelastic Wing F/A-18 Aircraft written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-14 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Traditional techniques in structural load measurement entail the correlation of a known load with strain-gage output from the individual components of a structure or machine. The use of strain gages has proved successful and is considered the standard approach for load measurement. However, remotely measuring aerodynamic loads using deflection measurement systems to determine aeroelastic deformation as a substitute to strain gages may yield lower testing costs while improving aircraft performance through reduced instrumentation weight. This technique was examined using a reliable strain and structural deformation measurement system. The objective of this study was to explore the utility of a deflection-based load estimation, using the active aeroelastic wing F/A-18 aircraft. Calibration data from ground tests performed on the aircraft were used to derive left wing-root and wing-fold bending-moment and torque load equations based on strain gages, however, for this study, point deflections were used to derive deflection-based load equations. Comparisons between the strain-gage and deflection-based methods are presented. Flight data from the phase-1 active aeroelastic wing flight program were used to validate the deflection-based load estimation method. Flight validation revealed a strong bending-moment correlation and slightly weaker torque correlation. Development of current techniques, and future studies are discussed.Lizotte, Andrew M. and Lokos, William A.Armstrong Flight Research CenterAEROELASTICITY; DEFLECTION; WINGS; F-18 AIRCRAFT; AERODYNAMIC LOADS; BENDING MOMENTS; FEASIBILITY ANALYSIS; STRAIN GAGES; CIRCUITS; POTENTIOMETERS (INSTRUMENTS); WING ROOTS; ROOT-MEAN-SQUARE ERRORS; GROUND TESTS
Book Synopsis Deflection-Based Structural Loads Estimation from the Active Aeroelastic Wing F/a-18 Aircraft by : Andrew M. Lizotte
Download or read book Deflection-Based Structural Loads Estimation from the Active Aeroelastic Wing F/a-18 Aircraft written by Andrew M. Lizotte and published by BiblioGov. This book was released on 2013-07 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.
Book Synopsis Loads Model Development and Analysis for the F/A-18 Active Aeroelastic Wing Airplane by :
Download or read book Loads Model Development and Analysis for the F/A-18 Active Aeroelastic Wing Airplane written by and published by . This book was released on 2005 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721510016 Total Pages :32 pages Book Rating :4.5/5 (1 download)
Book Synopsis Strain Gage Loads Calibration Testing of the Active Aeroelastic Wing F/a-18 Aircraft by : National Aeronautics and Space Administration (NASA)
Download or read book Strain Gage Loads Calibration Testing of the Active Aeroelastic Wing F/a-18 Aircraft written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-20 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes strain-gage calibration loading through the application of known loads of the Active Aeroelastic Wing F/A-18 airplane. The primary goal of this test is to produce a database suitable for deriving load equations for left and right wing root and fold shear; bending moment; torque; and all eight wing control-surface hinge moments. A secondary goal is to produce a database of wing deflections measured by string potentiometers and the onboard flight deflection measurement system. Another goal is to produce strain-gage data through both the laboratory data acquisition system and the onboard aircraft data system as a check of the aircraft system. Thirty-two hydraulic jacks have applied loads through whiffletrees to 104 tension-compression load pads bonded to the lower wing surfaces. The load pads covered approximately 60 percent of the lower wing surface. A series of 72 load cases has been performed, including single-point, double-point, and distributed load cases. Applied loads have reached 70 percent of the flight limit load. Maximum wingtip deflection has reached nearly 16 in. Lokos, William A. and Olney, Candida D. and Chen, Tony and Crawford, Natalie D. and Stauf, Rick and Reichenbach, Eric Y. and Bessette, Denis (Technical Monitor) Armstrong Flight Research Center NASA/TM-2002-210726, NAS 1.15:210726, H-2490
Book Synopsis Shock Location Dominated Transonic Flight Loads on the Active Aeroelastic Wing by : William A. Lokos
Download or read book Shock Location Dominated Transonic Flight Loads on the Active Aeroelastic Wing written by William A. Lokos and published by BiblioGov. This book was released on 2013-07 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: During several Active Aeroelastic Wing research flights, the shadow of the over-wing shock could be observed because of natural lighting conditions. As the plane accelerated, the shock location moved aft, and as the shadow passed the aileron and trailing-edge flap hinge lines, their associated hinge moments were substantially affected. The observation of the dominant effect of shock location on aft control surface hinge moments led to this investigation. This report investigates the effect of over-wing shock location on wing loads through flight-measured data and analytical predictions. Wing-root and wing-fold bending moment and torque and leading- and trailing-edge hinge moments have been measured in flight using calibrated strain gages. These same loads have been predicted using a computational fluid dynamics code called the Euler Navier-Stokes Three Dimensional Aeroelastic Code. The computational fluid dynamics study was based on the elastically deformed shape estimated by a twist model, which in turn was derived from in-flight-measured wing deflections provided by a flight deflection measurement system. During level transonic flight, the shock location dominated the wing trailing-edge control surface hinge moments. The computational fluid dynamics analysis based on the shape provided by the flight deflection measurement system produced very similar results and substantially correlated with the measured loads data.
Book Synopsis Strain Gage Loads Calibration Testing of the Active Aeroelastic Wing F/A-18 Aircraft by :
Download or read book Strain Gage Loads Calibration Testing of the Active Aeroelastic Wing F/A-18 Aircraft written by and published by . This book was released on 2002 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes strain-gage calibration loading through the application of known loads of the Active Aeroelastic Wing F/A-18 airplane. The primary goal of this test is to produce a database suitable for deriving load equations for left and right wing root and fold shear; bending moment; torque; and all eight wing control-surface hinge moments. A secondary goal is to produce a database of wing deflections mesured by string potentiometers and the onboard flight deflection measurement system. Another goal is to produce strain-gage data through both the laboratory data acquisition system and the onboard aircraft data system as a check of the aircraft system. Thirty-two hydraulic jacks have applied loads through whiffletrees to 104 tension-compression load pads bonded to the lower wing surfaces. The load pads covered approximately 60 percent of the lower wing surface.
Book Synopsis Strain-gage Loads Calibration Testing of the Active Aeroelastic Wing F/a-18 Airplane by : William A. Lokos
Download or read book Strain-gage Loads Calibration Testing of the Active Aeroelastic Wing F/a-18 Airplane written by William A. Lokos and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :Ted L. Lomax Publisher :AIAA (American Institute of Aeronautics & Astronautics) ISBN 13 : Total Pages :308 pages Book Rating :4.3/5 (91 download)
Book Synopsis Structural Loads Analysis for Commercial Transport Aircraft by : Ted L. Lomax
Download or read book Structural Loads Analysis for Commercial Transport Aircraft written by Ted L. Lomax and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 1996 with total page 308 pages. Available in PDF, EPUB and Kindle. Book excerpt: This important text covers all aspects of structural loads analysis and provides some continuity between what was done on earlier airplane designs and what the current applications of the present regulations require.
Book Synopsis An Evaluation Technique for an F/A-18 Aircraft Loads Model Using F/A-18 Systems Research Aircraft Flight Data by : Candida D. Olney
Download or read book An Evaluation Technique for an F/A-18 Aircraft Loads Model Using F/A-18 Systems Research Aircraft Flight Data written by Candida D. Olney and published by . This book was released on 2000 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited evaluation of the F/A-18 baseline loads model was performed on the Systems Research Aircraft at NASA Dryden Flight Research Center (Edwards, California). Boeing developed the F/A-18 loads model using a linear aeroelastic analysis in conjunction with a flight simulator to determine loads at discrete locations on the aircraft. This experiment was designed so that analysis of doublets could be used to establish aircraft aerodynamic and loads response at 20 flight conditions. Instrumentation on the right outboard leading edge flap, left airleron, and left stabilator measured the hinge moment so that comparisons could be made between in-flight-measured hinge moments and loads model-predicted values at these locations. Comparisons showed that the difference between the loads model-predicted and in-flight-measured hinge moments was up to 130 percent of the flight limit load. A stepwise regression technique was used to determine new loads derivatives. These derivatives were placed in the load model, which reduced the error to within 10 percent of the flight limit load. This paper discusses the flight test methodology, a process for determining loads coefficients, and the direct comparisons of predicted and measured hinge moments and loads coefficients.
Book Synopsis Computational Aeroelastic Analysis of Aircraft Wings Including Geometry Nonlinearity by :
Download or read book Computational Aeroelastic Analysis of Aircraft Wings Including Geometry Nonlinearity written by and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Because the flutter phenomenon of aircraft wings is usually associated with large deformations/deflections, the structural solution based on linear theory for the aircraft wings might give inaccurate or totally unphysical solutions. This is due to the equilibrium state of the structure is referred to the initial configuration, which can be very different with actual configuration at a given time when the wing deflection is large. So the changing geometry of the structure has to be taken into account in order to accurately describe the fluid/structure interactions at the onset of flutter, or in the post-flutter regime. The objective of the present study is to show the ability of solving fluid structural interaction problems more realistically by including the geometric nonlinearity of the structure so that the aeroelastic analysis can be extended into the onset of flutter, or in the post flutter regime. A nonlinear Finite Element Analysis software is developed based on second Piola-Kirchhoff stress and Green-Lagrange strain. The second Piola-Kirchhoff stress and Green-Lagrange strain is a pair of energetically conjugated tensors that can accommodate arbitrary large structural deformations and deflection, to study the flutter phenomenon. Since both of these tensors are objective tensors, i.e., the rigid-body motion has no contribution to their components, the movement of the body, including maneuvers and deformation, can be included. The nonlinear Finite Element Analysis software developed in this study is verified with ANSYS, NASTRAN, ABAQUS, and IDEAS for the linear static, nonlinear static, linear dynamic and ...
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 974 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Introduction to Aircraft Aeroelasticity and Loads by : Jan Robert Wright
Download or read book Introduction to Aircraft Aeroelasticity and Loads written by Jan Robert Wright and published by John Wiley & Sons. This book was released on 2008-02-28 with total page 559 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeroelastic phenomena arising from the interaction of aerodynamic, elastic and inertia forces, and the loads resulting from flight / ground manoeuvres and gust / turbulence encounters, have a significant influence upon aircraft design. The prediction of aircraft aeroelastic stability, response and loads requires application of a range of interrelated engineering disciplines. This new textbook introduces the foundations of aeroelasticity and loads for the flexible aircraft, providing an understanding of the main concepts involved and relating them to aircraft behaviour and industrial practice. This book includes the use of simplified mathematical models to demonstrate key aeroelastic and loads phenomena including flutter, divergence, control effectiveness and the response and loads resulting from flight / ground manoeuvres and gust / turbulence encounters. It provides an introduction to some up-to-date methodologies for aeroelastics and loads modelling. It lays emphasis on the strong link between aeroelasticity and loads. It also includes provision of MATLAB and SIMULINK programs for the simplified analyses. It offers an overview of typical industrial practice in meeting certification requirements.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1989 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Structures and Materials Panel. Meeting Publisher : ISBN 13 :9789283600374 Total Pages :190 pages Book Rating :4.6/5 (3 download)
Book Synopsis Charges Et Les Spécifications Des Avions Militaires by : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Structures and Materials Panel. Meeting
Download or read book Charges Et Les Spécifications Des Avions Militaires written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Structures and Materials Panel. Meeting and published by . This book was released on 1997 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1993 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Book Synopsis Introduction to Nonlinear Aeroelasticity by : Grigorios Dimitriadis
Download or read book Introduction to Nonlinear Aeroelasticity written by Grigorios Dimitriadis and published by John Wiley & Sons. This book was released on 2017-03-10 with total page 944 pages. Available in PDF, EPUB and Kindle. Book excerpt: Introduction to Nonlinear Aeroelasticity Introduces the latest developments and technologies in the area of nonlinear aeroelasticity Nonlinear aeroelasticity has become an increasingly popular research area in recent years. There have been many driving forces behind this development, increasingly flexible structures, nonlinear control laws, materials with nonlinear characteristics and so on. Introduction to Nonlinear Aeroelasticity covers the theoretical basics in nonlinear aeroelasticity and applies the theory to practical problems. As nonlinear aeroelasticity is a combined topic, necessitating expertise from different areas, the book introduces methodologies from a variety of disciplines such as nonlinear dynamics, bifurcation analysis, unsteady aerodynamics, non-smooth systems and others. The emphasis throughout is on the practical application of the theories and methods, so as to enable the reader to apply their newly acquired knowledge Key features: Covers the major topics in nonlinear aeroelasticity, from the galloping of cables to supersonic panel flutter Discusses nonlinear dynamics, bifurcation analysis, numerical continuation, unsteady aerodynamics and non-smooth systems Considers the practical application of the theories and methods Covers nonlinear dynamics, bifurcation analysis and numerical methods Accompanied by a website hosting Matlab code Introduction to Nonlinear Aeroelasticity is a comprehensive reference for researchers and workers in industry and is also a useful introduction to the subject for graduate and undergraduate students across engineering disciplines.
