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2 edition of Flutter analysis of an airplane with multiple structural nonlinearities in the control system found in the catalog.

Flutter analysis of an airplane with multiple structural nonlinearities in the control system

Elmar J Breitbach

Flutter analysis of an airplane with multiple structural nonlinearities in the control system

by Elmar J Breitbach

  • 330 Want to read
  • 6 Currently reading

Published by U.S. National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .
Written in English

    Subjects:
  • Flutter (Aerodynamics)

  • Edition Notes

    StatementElmar J. Breitbach
    SeriesNASA technical paper -- 1620
    ContributionsLangley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
    The Physical Object
    Pagination36 p. :
    Number of Pages36
    ID Numbers
    Open LibraryOL14932626M

    Based on a year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.5/5(2). considering the noisy input-output data, this paper come up with an idea extending the deviation compensation least square (CLS)to the nonlinear separable least square (NSLS).The least square method employed nonlinear separable least square adaptive to the noisy situation is able to identify accurately the airplane flutter model : Jie Yao, Jian Hong Wang.

    Failure condition: The term failure condition is the same as that used in 14 CFR ; however, this special condition applies only to system failure conditions that affect the structural performance of the airplane (e.g., failure conditions that induce loads, lower flutter margins, or change the response of the airplane to inputs, such as. ight control system. Nonlinear analysis is necessary as the falling leaf motion is due to nonlinearities in the aircraft dynamics and cannot be replicated in simulation by linear models. This makes the falling leaf motion a particularly interesting example for the application of nonlinear robustness analysis techniques.

    Nonlinear Analysis of Aircraft Loss-of-Control Harry G. Kwatny 1 and Jean-Etienne T. Dongmo 2 and Bor-Chin Chang 3 Drexel University, Philadelphia, A,P , USA Gaurav Bajpai 4 and Murat asarY 5 chno-ScienceT es, Inc., Beltsville, MD, , USA. phase system results in a system with a linear input-output response but unstable internal dynamics, designing a feedback control based on a minimum phase approximation to the true system results in a system with desirable properties such as bounded tracking and asymptotic stability. 1. INTRODUCTIONFile Size: 1MB.


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Flutter analysis of an airplane with multiple structural nonlinearities in the control system by Elmar J Breitbach Download PDF EPUB FB2

Get this from a library. Flutter analysis of an airplane with multiple structural nonlinearities in the control system. [Elmar J Breitbach; Langley Research Center.; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Branch.]. flutter analysis of airplanes with strong concentrated control system nonlin- earities. In accordance with one of these concepts (concept I1 of ref. 6), the originally nonlinear airplane structure is physically converted to an artifi- cially linearized test configuration by.

Continuation methods are presented that are capable of treating frequency domain flutter equations, including multiple nonlinearities represented by describing functions. A small problem demonstrates how a series of continuation processes can find all limit-cycle oscillations within a specified region with a reasonable degree of : Edward E.

Meyer. Breitbach, E.J., Flutter Analysis of an Airplane with Multiple Structural Nonlinearities in the Control System. NASA TP -May Google Scholar. Breitbach E. () Identification of Nonlinear Systems. In: Natke H.G. (eds) Identification of Vibrating Structures.

Cited by: 1. Nonlinear Stability Analysis of Control Surface Flutter with Free-Play Effects Article in Journal of Aircraft 45(6) November with Reads How we measure 'reads'. Structural and aerodynamic nonlinearities, methods used for aeroelastic analysis, nonlinear aeroelastic behaviors, and flutter active control approaches are introduced.

In Section 3, structural and aerodynamic modeling for the aeroelasticity of high-aspect-ratio wing with geometrically nonlinear deformation is by: In this paper, weinvestigate nonlinear control laws for aeroelastic systems that include polynomial structural nonlinearities, and study the closed loop stability of the system.

Active flutter suppression, which is a part of the group of flight vehicle technologies known as active controls, is an important contributor to the effective solution of aeroelastic instability problems when they pop up late in the development of a new aircraft or, if used from the start of the design process, it is a key element in multidisciplinary design optimization that could lead Cited by: In the engineering applications, the effects of structural geometric nonlinearities on the air vehicle design are the most concerns of aeroelasticity before a systematic flutter analysis for the air vehicle.

because the solution for nonlinear flutter speed based on the CFD-CSD method is complex and time by: 4. The flow velocity of the maximum variance of the system response was regarded as the flutter speed. LeBlanc, P.: Flutter analysis of a two-dimensional airfoil with cubic non-linear restoring force.

H., Lee, B.H.K.: The aeroelastic response of a two-dimensional airfoil with bilinear and cubic structural nonlinearities. Fluids Struct. Cited by: 4. The Problem of Control 1 Catching Up to the Wright Brothers 3 The Invention of Flap-Type Control Surfaces and Tabs 3 Handles, Wheels, and Pedals 4 Wright Controls 5 Bleriot and Dep´ erdussin Controls 5´ Stability and Control of World War I Pursuit Airplanes 6 Contrasting Design Philosophies 7 Frederick File Size: KB.

Optimal Flutter Suppression of Nonlinear Typical Wing Section Using Time-Domain Finite Elements Method The numerical results are presented in which the performance of the nonlinear optimal control system designed by the time-domain finite element technique for nonlinear aeroelastic wing sections is illustrated.

Aerodynamic flutter. and moreover, control theory has been crucial in NASA’s Apollo and Space Shuttle pro-grammes. Control systems such as in these examples use in an essential way the idea of feedback, the central theme of this chapter.

Control theory is the branch of engineering/science concerned with the design and analysis of control Size: KB. About this Item: paperback. Condition: New. Paperback. Pub Date: Pages: Language: Chinese in Publisher: Beijing University of Aeronautics and Astronautics Press aircraft structural strength analysis and design basis on the basis of the analysis and design of aircraft structural strength and specialized materials.

a comprehensive introduction to the basic principles of. Analysis of Aircraft Structures Second Edition As with the first edition, this textbook provides a clear introduction to the funda-mental theory of structural analysis as applied to aircraft, spacecraft, automobiles,File Size: KB.

Structural Analysis and Design of Airplanes by Engineering Division McCook Field (Compiler) out of 5 stars 1 rating. ISBN ISBN Why is ISBN important. ISBN. This bar-code number lets you verify that you're getting exactly the right version or edition of a book.

3/5(1). American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The aeroelastic behavior of high-aspect-ratio very flexible flying wing is highly affected by the geometric nonlinearities of the aircraft structure.

This paper reviews the findings on how these nonlinearities influence the structural and flight dynamics, and it shows that the aeroelastic flight envelope could significantly be extended with proper choices of design parameters such as Author: Pezhman Mardanpour, Siavash Rastkar.

dynamics (CFD) tools and computational structural dynamics (CSD) tools, a more accurate portrayal of the nonlinearities of the flow and the aeroelastic effects of the wing can be captured. Mostafa.S and A. ElsayedRamin[1], Accurate Stick Model Development for Static Analysis of Complex Aircraft Wing-Box Structures AIAAFile Size: KB.

structural constraints for an adaptive control system and to verify that the control frequency is sufficiently separate from the structural frequencies, it is necessary to determine the frequency response of the structures in the presence of damage.

Frequency estimation is also necessary to determine the flutter boundary changes due to the Size: 1MB. TY - JOUR. T1 - Design of nonlinear automatic flight control systems. AU - Garrard, William L. AU - Jordan, John M. PY - /9. Y1 - /9.

N2 - A method for the synthesis of nonlinear automatic flight control systems is developed, and the performance of a control system synthesized by use of this method is compared to the performance of control system designed Cited by: Flutter analysis of aircraft has been widely studied in the literature1{4 and numerous researchers have addressed aeroelastic modeling for highly exible aircraft.5{7 Currently, modeling aeroelastic behavior of exible aircraft requires the development of a structural model coupled with an aerodynamic model.

TheCited by:   This is lecture 2 in the series of Nonlinear Systems and Control. This Lecture introduces the concept of phase plane analysis and talks about procedure to find phase portrait of a nonlinear system.