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Wednesday, April 29, 2020 | History

3 edition of Investigation of control law for active flutter suppression found in the catalog.

Investigation of control law for active flutter suppression

Investigation of control law for active flutter suppression

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  • 32 Currently reading

Published by National Aeronautics and Space Administration in Washington, DC .
Written in English

    Subjects:
  • Flutter (Aerodynamics)

  • Edition Notes

    StatementWang Weiping, Gu Zhongquan and Zhu Demao.
    SeriesNASA technical translation -- NASA TT-20126., NASA technical translation -- 20126.
    ContributionsZhongquan, Gu., Demao, Zhu., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15285774M

    Suppress. To stop something or someone; to prevent, prohibit, or subdue. To suppress evidence is to keep it from being admitted at trial by showing .


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Investigation of control law for active flutter suppression Download PDF EPUB FB2

Get this from a library. Investigation of control law for active flutter suppression. [Wang Weiping; Gu Zhongquan; Zhu Demao; United States. The flutter suppression control law was designed using linear quadratic Gaussian theory, and involved control law order reduction, a gain root-locus study, and use of previous experimental results.

A flutter suppression control law synthesis for this project is described here. The state-space mathematical model uscd for the synthesis. included ten flexible modes, four control surface modes and.

rational function approximation of the doublet-lattice unsteady aerodynamics. be realized by active suppression techniques using existing control surfaces.

However, it should be noted that no aircraft is currently flown beyond its flutter speed through the incorporation of a flutter suppression system. The main objective of this study is to demonstrate in principle that by using on.

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 Cited by: which is actuated by the motion of the main surface and which leads to an appropriate deflection of the control surface.

In this way, use is made of control-surface aerody­ namic forces to combat flutter instability. Such a system is referred to as an active control Size: 4MB.

Active stability augmentation system is an attractive and promising technology to suppress flutter and limit cycle oscillation (LCO). In order to design a good active control law, the control plant model with low order and high accuracy must be provided, which is one of the most important key by: 8.

modern control theory; for the sake of clarity, explicit formulae are derived and numerical results are given for a test-case. The validity of the active-flutter-suppression concept is well recognized.

The concept's performances will be discussed in Part II of this paper. Keywords: aeroelasticity, flutter, active flutter suppression 1. Introduction. The flap deflection is due to the active control law applied to the servoactuator. The control aims at suppression of flutter type instability by changing the wing configuration to cause the total aerodynamic lift and moment variations.

The airstream speed was considered in this study as a parametric Size: KB. Typically, the flutter boundary for the wing is conservatively defined below the Airplane speed [7], and limited altitudes. An obligatory thing to design an active control is to have a goodmodel which captures the salient.

characteristics of the aeroelastic phenomenaalong with manageable control design ].Author: Bruce Ralphin, Rose J. The closed-loop control systems designed by the sliding mode control (SMC) and linear quadratic Gaussian (LQG) control were constructed with ROM/CSD to suppress the AGARD wing flutter.

The detailed implementation of the two control approaches is presented, and the flutter suppression effectiveness is discussed and by: 1. An optimization procedure, based on the Aerodynamic Energy concept, is applied to the problem of flutter suppression using trailing-edge (T.E.) and tab control surfaces.

A control law. In this investigation, a new active flutter control method which can suppress the flutter effectively and without affecting the natural frequency of the structural system is proposed by exerting active control forces on some discrete points of the by: 4.

This video is unavailable. Watch Queue Queue. Watch Queue Queue. In this study, a delayed controller was designed for active flutter suppression of a three-dimensional wing model.

The design of controller can be divided into two by: H∞ Control Design for Active Flutter Suppression of Flexible-Wing Unmanned Aerial Vehicle Demonstrator Author(s): Sérgio Waitman, Andrés Marcos Published in: Journal of Guidance, Control, and Dynamics, Issue Online: 20 Dec., Page(s)ISSN A new adaptive robust nonlinear predictive control law is designed in this paper to mitigate the damage during airfoil flutter of a generic hypersonic flight vehicle.

A three-degrees-of-freedom airfoil dynamic motion model is established, in which the third piston theory is employed to derive the unsteady : Xiaohui Zhang, Yuhui Wang, Xingkai Feng, Siyuan Hou. The active flutter suppression is performed by means of a rotary actuator situated at approximately 80 % of the semi-span on each wing.

The final position of the actuators is a result of a sensitivity study performed by Wuestenhagen et al. The inertia of the actuators has been used as an additional degree of freedom to affect the aeroelastic Cited by: 1. In this project, the various methodologies were applied to design a flutter suppression system for the Benchmark Active Controls Technology (BACT) Wing.

This report describes a project at the University of Washington to design a multirate suppression system for the BACT wing. The objective of the project was two fold. The model-based flight control system design for a highly flexible flutter demonstrator, developed in the European FLEXOP project, is presented.

The flight control system includes a baseline controller to operate the aircraft fully autonomously and a flutter suppression controller to stabilize the unstable aeroelastic modes and extend the aircraft’s operational by: 6.

Chap 1 InvestigTech 10/10/07 PM Page i. OCT. Investigative Uses of Technology: Devices,Tools, and Techniques. NCJ Chapter Suppression Motions A motion to suppress illegally obtained evidence is one of the most effective weapons in a criminal defense lawyer’s arsenal, and there are several reasons to file a suppression motion.

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University of Minnesota, Minneapolis, Minnesota Two linear parameter-varying gain-scheduled controllers for active ‘ utter suppression of the NASA Langley. Research Center’ s Benchmark Active Control Technology(BACT)wing section are presented and compared to. a previously presented gain-scheduled controller.

An active control law is synthesized for the suppression of wing flutter for a mathematical model of a flight test vehicle.

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This document you requested has moved permanently. It's now at /help/rptgenext/;jsessionid=16fe3fcb2fe8de5cf6eae The Federal Aviation Regulation Sec. - Flutter. Sec. — Flutter. (a) It must be shown by the methods of paragraph (b) and either paragraph (c) or (d) of this section, that the airplane is free from flutter, control reversal, and divergence for any condition of operation within the limit V-n envelope and at all speeds up to the speed specified for the selected method.

or his usual occupation he will be available to render active service as a volunteer fireman in the fire district or in territory outside the fire district which is afforded fire protection pursuant to a contract for fire protection by the fire department of the fire district, or a fire company Size: 39KB.

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