Last edited by Goltigul
Tuesday, May 5, 2020 | History

3 edition of Flutter suppression digital control law desighn and testing for the AFW wind-tunnel model found in the catalog.

Flutter suppression digital control law desighn and testing for the AFW wind-tunnel model

Flutter suppression digital control law desighn and testing for the AFW wind-tunnel model

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Published by National Aeronautics and Space Administration, Langley Research Center, For sale by the National Technical Information Service in Hampton, Va, [Springfield, Va .
Written in English

    Subjects:
  • Flutter (Aerodynamics),
  • Wind tunnel models.

  • Edition Notes

    StatementVivek Mukhopadhyay.
    SeriesNASA technical memorandum -- 107652.
    ContributionsLangley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15365932M

    BibTeX @INPROCEEDINGS{Mukhopadhyay98transonicflutter, author = {Vivek Mukhopadhyay and Vivek Mukhopadhyay}, title = {Transonic Flutter Suppression Control Law Design, Analysis and WindTunnel Test Results}, booktitle = {Presented at the 2nd International Conference on Nonlinear Problems in Aviation and Aerospace. Daytona Beach, FL. April 29}, year = {}, pages = {}}. These analytical results are often verified by wind-tunnel flutter models and ground vibration tests. Flight flutter testing provides the final verification of the analytical pre-dictions throughout the flight envelope. In the early years of aviation, no formal flutter testing of full File Size: 1MB.

    The Active Flutter Suppression (AFS) Technology Evaluation Project FAA technical monitors / collaborators: David R. Westlund. FAA - Advanced Materials and Structures. John Bakuckas, Ph. D. FAA - Structures and Materials Section, ANG-E Carl J. Niedermeyer. FAA - Airframe and Cabin Safety Branch (ANM) Ian Y. Won. 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. Below is what this vehicle looks like when it .

    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. Norlander et al. () also used simple LQG control techniques to evaluate a model on a wind-tunnel test. Haley and Soloway () have made an experimental investigation in a transonic wind-tunnel to demonstrate the use of the generalized predictive control for flutter suppression of a subsonic airfoil.


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Flutter suppression digital control law desighn and testing for the AFW wind-tunnel model Download PDF EPUB FB2

Flutter suppression digital control law design and testing for the AFW wind tunnel model. VIVEK MUKHOPADHYAY; VIVEK MUKHOPADHYAY. NASA, Langley Research Center, Hampton, VA CFD-Based Control for Flutter Suppression, Gust Load Alleviation.

present the flutter suppression control law design process, numerical nonlinear simulation and wind tunnel test results for the NACA benchmark active control wing model. The flutter suppression control law design processes using classical, and minimax techniques are described.

A unified general formulation and solution for the minimax. Flutter suppression digital control law design and testing for the AFW wind tunnel model. VIVEK MUKHOPADHYAY; Dynamics Specialists Conference August Transonic flutter suppression control law design using classical and optimal techniques with wind tunnel by: The Active Flutter Suppression (AFS) Technology Evaluation Project FAA technical monitors / collaborators: David R.

Westlund. FAA - Advanced Materials and Structures. John Bakuckas, Ph. FAA - Structures and Materials Section, ANG -E Carl J. Niedermeyer. FAA - Airframe and Cabin Safety Branch (ANM ) Ian Y. WonFile Size: KB. AFW Wind-Tunnel Model and Test Conditions Wind-Tunnel Model The AFW wind-tunnel model is a full-span, sting-mounted, wind-tunnel model that can roll about the sting axis (fig.

For tile flutter suppression testing described herein (the TDT entry in November ), the AFW wind-tunnel model was prevented from rolling by applying a locking by: The paper will present the flutter suppression control law design process, numerical nonlinear simulation and wind tunnel test results for the NACA benchmark active control wing model.

The flutter suppression control law design processes using (1) classical, (2) linear quadratic Gaussian (LQG), and (3) minimax techniques are described. Introduction. Active Flutter Suppression (AFS) has a great potential to suppress the flutter instability of a flight vehicle. As reviewed by Mukhopadhyay (), the technique of AFS for aircraft structures has drawn much attention over the past decades.

From the viewpoint of control design, a number of studies have focused on how to synthesize advanced controllers to stabilize a wing Cited by: Testing of a Digital Active Flutter Suppression System for a Modified B Wind-Tunnel Model John R.

Matthew _'/NA,_ MILII'A/IYA/RPLAAIE _nOMPAAIY A Division of The Boeing Company o Wichita, Kansas o Contract NASI March National Aeronautics and Space Administration Langley Research Center Hampton, Virginia AC The concept of this programme consisted of the design, wind tunnel test, and evaluation of Three Active Flutter Suppression Controllers.

Classic and modern control techniques were exploited with. A Nonlinear Controller for Flutter Suppression: from Simulation to Wind Tunnel Testing quadratic Gaussian control that takes into account a control input delay was designed and applied to control an experimental wind tunnel model for flutter suppression.

More recently, control design has been shown for stability augmentation and gust load. PANEL FLUTTER 1. INTRODUCTION Panel flutter is a self-excited, dynamic-aeroelastic instability of thin plate or shell-like components of a vehicle.!t OCCL~ most frequently, though not exclusively, in File Size: 2MB.

Technology (BACT) wind-tunnel model for application to design and analysis of flutter suppression controllers. The model is formed by combining the equations of motion for the BACT wind-tunnel model with actuator models and a model of wind-tunnel turbulence. The primary focus of this paper is the development of the equations of motion.

applied to design a flutter suppression systems for the Benchmark Active Controls Technology (BACT)Wing (also called the PAPA wing).

Eventually, the designs will be implemented in hardware and tested on the BACT wing in a wind tunnel. This report describes a project at the University of Washington to design a multirate flutter suppression. A typical active control system for flutter suppression performs three main functions: sensing the motion, feeding back the signal to the controller and generating the appropriate law to be.

A slogan for Dynamic Engineering Inc. (DEI) is "mobilizing minds and materials in research and development for land, sea, air, and space." That blend of talent and technology came together in to establish DEI of Newport News, Virginia.

The core of early work by the company was building aircraft. LPV Modeling and Control for Active Flutter Suppression of a Smart Airfoil was evaluated in wind tunnel testing.

wind tunnel test model was a rectangular wing with an NACA airfoil section and with a trailing edge control surface actuator. The main goal was to suppress flutter and to maintain the stability of the closed-loop system.

The proposed feedback control technique will be demonstrated with SuperSonic SemiSpan Transport S4T wind tunnel model for flutter suppression and gust load alleviation.

* Information listed above is at the time of on: AZ, Scottsdale, AZ, Application of two design methods for active flutter suppression and wind-tunnel test results (NASA technical paper) [Newsom, Jerry R] on *FREE* shipping on qualifying offers.

Application of two design methods for active flutter suppression and wind-tunnel test results (NASA technical paper)Author: Jerry R Newsom. The paper presents a digital adaptive controller of recurrent neural networks for the active flutter suppression of a wing structure over a wide transonic range.

The basic idea behind the controller is as follows. At first, the parameters of recurrent neural networks, such as the number of neurons and the learning rate, are initially determined so as to suppress the flutter under a specific Cited by: 6. pressure of flutter boundary in the experiment was lower than that in the calculation, they suggested the change of wind tunnel test condition and the ability of the actuator must be considered for the controller design.

A digital adaptive controller was introduced for active flutter suppression undergoing time varying flight conditions [4]. Abstract: This article presents experimental results of a transonic wind-tunnel test that demonstrates the use of generalized predictive control for flutter suppression for a subsonic wind-tunnel wing model.

The generalized predictive control algorithm is based on the minimization of a suitable cost function over finite costing and control horizons.Project Overview Goal: Actively Optimize Wing Shape - Transport Aircraft Approach: Use Flexibility to an Advantage, MDAO, active control • Active flutter suppression is a key enabling technology • Critical PAAW program components – Three different vehicles will be developed and flight tested The first will be very similar to Lockheed Martin’s FFAD.These analytical results are often verified by wind-tunnel flutter models and ground vibration tests.

Flight flutter testing provides the final verification of the analytical pre-dictions throughout the flight envelope. In the early years of aviation, no formal flutter testing of full-scale aircraft was carried out.

The aircraft was simplyFile Size: KB.