3 edition of Eigensystem synthesis for active flutter suppression on an oblique-wing aircraft found in the catalog.
Eigensystem synthesis for active flutter suppression on an oblique-wing aircraft
by National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, For sale by the National Technical Information Service] in Edwards, Calif, [Springfield, Va
Written in English
|Statement||Gurbux S. Alag, John J. Burken and Glenn B. Gilyard.|
|Series||NASA technical memorandum -- 88275.|
|Contributions||Gilyard, Glenn B., Burken, John J., Dryden Flight Research Facility.|
|The Physical Object|
On its AFRL lead mission the ft.-span vehicle will test active flutter suppression and gust load alleviation. Following that phase the XA will be transferred to NASA, to support NASA Dryden Flight Research Center, to assist the research of lightweight structures and advanced technology for future low-emissions transport aircraft. Flutter is one of the most important aspects that engineers have to care about while seeking the design certification of an aircraft. Basically it is an unstable oscillation of the airframe, the.
This analytical study of active flutter suppression systems for military aircraft was directed toward the accomplishment of two broad objectives: (1) Establish flutter modes, configurations, and flight conditions where active flutter control can show an advantage; (2) Formulate design guidelines and criteria to implement and test active flutter suppression systems. reduced order models control synthesis are generatedfor by retaining a common set of states across the flight results, full order models of states are red uced to 43 states. The reduced order models capture the dynamics of interest and can be used in the synthesis of active flutter suppression controllers. INTRODUCTION.
Triplett, A feasibility study of active wing/store flutter control, J. Aircraft. 9 (6) () – Crossref, Google Scholar; N. Gade, V. Prasad and D. J. Inman, Two-dimensional active wing/store flutter suppression using H. A method of formulating a model to evaluate the aeroelastic structural acoustic response of a panel subjected to turbulent boundary layer (TBL) noise sources and coupled with full potential flow aerodynamics is presented. Reduced-order models of both the aerodynamics and the structural acoustic coupling are presented such that a state-variable realization of the entire system dynamics can be.
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Claude Charles Bloch, Julius Augustus Furer, John Franklin Shafroth, William Harrison Standley: a register of their papers in the Library of Congress.
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 to Cited by: Get this from a library.
Eigensystem synthesis for active flutter suppression on an oblique-wing aircraft. [Gurbux S Alag; Glenn B Gilyard; John J Burken; Dryden Flight Research Facility.]. Eigensystem Synthesis for Active Flutter Suppression on an Obli Author: Gurbux S.
Alag, John J. Burken, and Glenn B. Gilyard Subject: H Keywords: Active flutter suppression; Eigenstructure; Oblique-wing aircra Created Date: 4/16/ AM. The oblique-wing aircraft, because of its configuration, provides two independent surfaces (left and right ailerons), making the application of eigensystem synthesis practical.
This paper presents the application of eigensystem synthesis using output feedback for the design of an active flutter suppression system for an oblique-wing : J. Burken, G. Alag and G. Gilyard. G.S. Alag, J.J. Burken“Eigensystem Synthesis for Active Flutter Suppression on an Oblique-Wing Aircraft” Journal of Guidance, Control, and Dynamics, 10 (no.
6) Cited by: 7. pression. The oblique-wing aircraft, because of its configuration, provides two independent sur faces (left and right ailerons), making the appli cation of eigensystem synthesis practical. This paper presents the application of eigensystem synthesis using output feedback for the design of an active flutter suppression system for an oblique.
Aircraft Active Flutter Suppression: State of the Art and Technology Maturation Needs. Eli Livne; 22 December | Journal of Aircraft, Vol. 55, No. 1 Eigensystem synthesis for active flutter suppression on an oblique-wing aircraft. suppression (OAMS) system designed to dampen out a structural vibration in the wing.
23 Mar FAA and Boeing agree on -8 OAMS special condition. The XA Multi-utility Aeroelastic Demonstration (MAD) is an innovative modular unmanned air vehicle designed to test active flutter suppression and gust load alleviation.
Design and flight test of active flutter suppression on the XA multi-utility technology test-bed aircraft - Volume Issue - E. Burnett, J. Beranek, B. Holm-Hansen, C. Atkinson, P. Flick.
EIGENSYSTEM SYNTHESIS FOR ACTIVE FLUTTER SUPPRESSION ON AN OBLIQUE-WING AIRCRAFT, Technical Memorandum Authors: G. Alag (University of Western Michigan), J. Burken (NASA Hugh L. Dryden Flight Research Center) and G. Gilyard (NASA Hugh L. Dryden Flight Research Center) Report Number: NASA-TM Aeroelasticity is the branch of physics and engineering studying the interactions between the inertial, elastic, and aerodynamic forces occurring while an elastic body is exposed to a fluid flow.
The study of aeroelasticity may be broadly classified in two fields: static aeroelasticity dealing with the static or steady state response of an elastic body to a fluid flow; and dynamic.
The method is applied to the synthesis of an active flutter-suppression control law for an aeroelasticwind tunnel wing model. The reduced-order control law is.
aircraft designs require a 15% flutter free margin beyond the designed speed and altitude envelope . In order to develop the next-generation aircraft or spacecraft, or to improve the performance of existing aircraft, the extension of flutter-free margins needs to be realized by active suppression techniques.
This type of behavior is particularly apparent in the Air Force Research Lab (AFRL) Body Freedom Flutter (BFF) aircraft, XA, seen below in a picture from the NASA website: Image Source. In order to test control surface flutter suppression techniques, this blended wing aircraft was designed to exhibit body freedom flutter.
Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A cumulative index to a continuing bibliography (supplement )" See other formats.
envelope, active flutter suppression is required for these aircraft that achieves targeted damping of specific aeroelastic modes in isolation. This paper describes three different active. b-1 aircraft structural mode control system.
 G. Xiong and C. Yang. Synthesis on utter suppression control law for active aeroelastic wing. AIAA Paper, E. Yates Jr. Calculation of utter characteristics for nite-span swept or unswept wings at subsonic and supersonic speeds by a modi ed strip analysis.
NASA Technical Memorandum FLUTTER SUPPRESSION CONTROL LAW SYNTHESIS FOR THE ACTIVE FLEXIBLE WING MODEL (NA SA -TH- 1 0 15 8 4) CONTROL LAU SYNTHESIS FOH THB ALTIVE FLEXIBLE WING MODEL (NASA.
Lanqley Research Center) 9 p CSCL 31c Unclas F LU TT EH S UPPR ESS IO N N G3/08 Vivek Mukhopadhyay, Boyd Perryand. A morphing wing can enhance aerodynamic characteristics and control authority as an alternative to using ailerons. To use morphing technology for flutter suppression, the dynamical behavior and stability of a variable-span wing subjected to the supersonic aerodynamic loads are investigated numerically in this paper.
flutter speed a certain amount above the aircraft's limit speed. In a traditional approach, this objective would be attained through stiffening the structure and/or mass adding or redistribution, both leading usually to some extra weight.
The active flutter suppression appears as a "modern" alternative to the "classical" one described above. In this paper a novel robust control is proposed for the purpose of active flutter suppression of a nonlinear 2-D wing-flap system in the incompressible flow field.
The controller consists of an optimized robust stabilizer in the form of state feedback control and a Proportional-Integral Observer (PI-Observer).adaptive controller was introduced for active flutter suppression undergoing time varying flight conditions .
It was indicated that the parameter estimator possibly failed to follow the aeroelastic system change depending on the flight paths. Another adaptive control application for the transonic flutter suppression.This banner text can have markup.
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