2 edition of Application of model control to wing-flutter suppression found in the catalog.
Application of model control to wing-flutter suppression
Aaron J Ostroff
by 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
|Statement||Aaron J. Ostroff, Samuel Pines|
|Series||NASA technical paper -- 1983|
|Contributions||Pines, Samuel, Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch|
|The Physical Object|
|Pagination||71 p. :|
|Number of Pages||71|
This document you requested has moved permanently. It's now at /help/rptgenext/;jsessionid=16fe3fcb2fe8de5cf6eae Regarding methods for controlling or suppressing LCOs, several control laws such as linear theory, partial feedback linearization, and adaptive control have been utilized to stabilize an inherently unstable aeroelastic system with a single trailing edge control surface4 or with leading and trailing edge control surfaces.5 These studies have shown.
In today’s aviation world, the design of aircraft wing becomes a challenging one for aeronautical engineers, in order to meet the aero elastic phenomenon such as flutter, wing divergence in both aerodynamics and structural aspects. There are so many FEM packages available for both flow and structural analysis such as ANSYS, NASTRAN, ALGOR, NISA, ADINA, COSMOS, : Anjani Kumar Sinha, Eriki Ananda Kumar, A. Johnrajan. I succeeded George Schmidt as the Editor-in-Chief (EIC) of the Journal of Guidance, Control, and Dynamics (JGCD) on 1 September I want to use this space to offer my congratulations and gratitude to George for his 17 years of distinguished service and leadership as the EIC of the Journal of Guidance, Control, and Dynamics!. I had served continuously as an Associate Cited by: 4.
Brad Paden is recognized for theoretical contributions in control, including nonsmooth stability theory, inversion of nonlinear systems, and control of robot manipulators. He has also led major design projects including the mechatronic design of left-ventricular assist devices (a . Aeroelastic Concepts for Flexible Wing Structures 3 Abstract This thesis summarizes investigations performed within design, analy-sis and experimental evaluation of exible aircraft structures. Not only the problems, but rather the opportunities related to aeroelasticity are discussed. In the rst part of the thesis, different concepts for using.
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Application of model control to wing-flutter suppression. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: For sale by the National Technical Information Service], tion of the control law (such as phase lags and amplitude gains) are investigated.
A broad discussion is also included regarding application of the flutter-suppressing system to three-dimensional wings, the parameters affecting the reduction of the number of conFile Size: 4MB. To study the effectiveness of various control system design methodologies, the NASA Langley Research Center initiated the Benchmark Active Controls Project.
In this project, the various methodologies will be applied to design a flutter suppression systems for the Benchmark Active Controls Technology (BACT)Wing (also called the PAPA wing). • Use active control, through the action of control effectors driven by actuators and control laws, to solve the problems.
In this case Active Flutter Suppression is used as a fix of flutter problems. 9File Size: KB. Flutter prediction, suppression and control in aircraft composite wings as a design prerequisite modelling and application in panel flutter plate, Suleman  concluded that can be inferred used to structurally model the wing.
The supersonic flutter analysis was done using theFile Size: KB. "Modeling the Benchmark Active Control Technology Wind Tunnel Model for Application to Flutter Suppression" by Martin R. Waszak of NASA Langley. Automatic flutter detection is implemented via a state-machine in s: 8. The wing flutter is a dynamic instability of a flight vehicle associated with the interaction of aerodynamic, elastic, and inertial forces (aeroelastics phenomena).
In this study, just the primary control is investigated. Also, in order to control the two-dimensional wing flutter, the force jet and pulse width pulse frequency (PWPF) are suggested. The PWPF modulator has the advantage Author: A. Ansari, A. Novinzadeh. Wing Flutter Control.
Transportation. Next page. Orbital Research Inc. of Cleveland, Ohio has developed a software program that "thinks" change. By way of Small Business Innovation Research (SBIR) contracts from Langley Research Center, an Orbital Research Intelligent Control Algorithm™ (ORICA™, rhymes with "eureka") has been developed.
In January of the BACT wind-tunnel model was used to successfully demonstrate the application of robust multivariable control design methods (H Author: Martin Waszak. A rather high aspect ratio motivates a numerical model based on linear beam theory for the structural dynamics and strip theory for the unsteady aerodynamic loads.
Experimental flutter testing shows good agreement with the numerical stability analysis, and the impact of the trailing edge flap on the dynamics is verified by open-loop by: In January of the BACT wind-tunnel model was used to successfully demonstrate the application of robust multivariable control design methods (H ∞ and µ-synthesis) to flutter suppression.
This paper introduces a novel LPV (linear parameter-varying) virtual control scheme to deal with a class of hard constrained control problems with an application to flutter suppression of a smart.
In order to test control surface flutter suppression techniques, this blended wing aircraft was designed to exhibit body freedom flutter.
For more conventional design aircraft, body freedom flutter tends to appear less frequently, however it should not be dismissed. Wing Flutter on a A Boeing model undergoes “flutter” testing in a wind tunnel, circa The purpose of the test was to determine the effects (primarily the aerodynamics) of the large cowls surrounding the engine fans on the flutter characteristics of the aircraft.
The control design and analysis presented in this work demonstrates the suitability of the developed state-space model for use in design and development of active stall flutter suppression systems.
Further work has to be performed on detailed controller by: Lin, J.: Suppression of Bending Torsion Wing Flutter Using Self Straining Controllers. Dissertation, Engineering UCLA () Google ScholarAuthor: A V Balakrishnan.
Aeroelasticity is the branch of physics and engineering that studies the interactions between the inertial, elastic, and aerodynamic forces that occur when an elastic body is exposed to a fluid flow. The study of aeroelasticity may be broadly classified into two fields: static aeroelasticity, which deals with the static or steady state response of an elastic body to a fluid flow; and dynamic.
The flutter is also caused by the tips being up in the airstream on a Poly angle and with the drag trying to rotate each wingtip backwards it bends the wingtip back and the strenth of the spar etc rotates in back in place - then backwards again from the air pressure and rotates it back and this action pick's up speed and then you have flutter.
The paper deals with unstable aeroelastic modes for aircraft wing model in subsonic, incompressible, inviscid air flow.
In recent author’s papers asymptotic, spectral and stability analysis of the model has been carried out. The model is governed Cited by: 2. Error-correction Method of the Modal Frequency for the Manufacturing of Wing Flutter Model with Structure-similarity [J].
Journal of Mechanical Engineering. vol. 49(), p: DOI: /jmeAuthor: Wei Long, Yan Liu, Jia Ming Cao. Get this from a library! Proceedings of the Second International Conference on Structural Stability and Dynamics: Singapore, December [C M Wang; G R Liu; K K Ang;] -- ICSSD is the second in the series of International Conferences on Structural Stability and Dynamics, which provides a forum for the exchange of ideas and experiences in structural stability and.For this study, a simplified wing model is augmented including the short-period approximation aircraft model and the rigid–elastic coupling terms.
The proposed model captures properties and trends of both restrained wing flutter and body freedom flutter by: 4.American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA