Incorporation of SemiSpan SuperSonic Transport (S4T) Aeroservoelastic Models into SAREC-ASV Simulation

Christhilf, David M.; Pototzky, Anthony S.; Stevens, William L.

doi:10.2514/6.2010-8099

Cited by 7 publications

(4 citation statements)

References 10 publications

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“…Presented in Figure 26 is a schematic of this simplified APSE system. 17 This schematic identifies the airframe component (ASE Model), the dynamic engine model (Engine Model and related control system), and all the relevant interconnections, including the effects of atmospheric turbulence. Presented in Figure 27 is a comparison of airframe accelerations generated with and without the closedloop coupling of the airframe and the engine.…”

Section: Apsementioning

confidence: 99%

The NASA High Speed ASE Project: Computational Analyses of a Low-Boom Supersonic Configuration

Christhilf

Johnson

Kopasakis

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A summary of NASA's High Speed Aeroservoelasticity (ASE) project is provided with a focus on a low-boom supersonic configuration developed by Lockheed-Martin and referred to as the N+2 configuration. The summary includes details of the computational models developed to date including a linear finite element model (FEM), linear unsteady aerodynamic models, structured and unstructured CFD grids, and discussion of the FEM development including sizing and structural constraints applied to the N+2 configuration. Linear results obtained to date include linear mode shapes and linear flutter boundaries. In addition to the tasks associated with the N+2 configuration, a summary of the work involving the development of AeroPropulsoServoElasticity (APSE) models is also discussed.

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Section: Apsementioning

confidence: 99%

The NASA High Speed ASE Project: Computational Analyses of a Low-Boom Supersonic Configuration

Christhilf

Johnson

Kopasakis

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…A valuable tool that was developed in support of the closed-loop testing was a simulation of the various available S 4 T wind-tunnel model plant models and candidate control laws in the Simulink c -based Simulation Architecture for Evaluating Controls for Aerospace Vehicles (SAREC-ASV) 15 simulation framework. A schematic of the various user options available in this tool is presented as Figure 12.…”

Section: Vb Simulationmentioning

confidence: 99%

An Overview of the Semi-Span Super-Sonic Transport (S4T) Wind-Tunnel Model Program

Silva

Perry²,

Florance³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite

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A summary of computational and experimental aeroelastic (AE) and aeroservoelastic (ASE) results for the Semi-Span Super-Sonic Transport (S 4 T) wind-tunnel model is presented. A broad range of analyses and multiple AE and ASE wind-tunnel tests of the S 4 T wind-tunnel model have been performed in support of the ASE element in the Supersonics Program, part of the NASA Fundamental Aeronautics Program. This paper is intended to be an overview of multiple papers that comprise a special S 4 T technical session. Along those lines, a brief description of the design and hardware of the S 4 T wind-tunnel model will be presented. Computational results presented include linear and nonlinear aeroelastic analyses, and rapid aeroelastic analyses using CFD-based reduced-order models (ROMs). A brief survey of some of the experimental results from two open-loop and two closed-loop wind-tunnel tests performed at the NASA Langley Transonic Dynamics Tunnel (TDT) will be presented as well.

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“…The last two tests employed active control laws for Flutter Suppression (FS), Gust Load Alleviation (GLA), and Ride Quality Enhancement (RQE). Two objectives of the first two wind-tunnel tests were to understand the windtunnel model and to develop state-space representations of the wind-tunnel model for use in subsequent control law design and implementation in a MATLAB/Simulink simulation developed as part of the S 4 T program 5 . Control law designers used the data acquired and processed during these two open-loop tests to select suitable sensor/controleffector pairs.…”

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confidence: 99%

“…The analytical plant models developed for the S 4 T were used for control law design and for a MATLAB/Simulink simulation5 . The matrices Downloaded by MONASH UNIVERSITY on November 26, 2014 | http://arc.aiaa.org | DOI: 10.2514/6.2012-1554…”

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confidence: 99%

Analytical and Experimental Evaluation of Digital Control Systems for the Semi-Span Super-Sonic Transport (S4T) Project
Wieseman¹,
Christhilf²,
Perry³
2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite
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An important objective of the Semi-Span Super-Sonic Transport (S 4 T) wind tunnel model program was the demonstration of Flutter Suppression (FS), Gust Load Alleviation (GLA), and Ride Quality Enhancement (RQE). It was critical to evaluate the stability and robustness of these control laws analytically before testing them and experimentally while testing them to ensure safety of the model and the wind tunnel. MATLAB based software was applied to evaluate the performance of closed-loop systems in terms of stability and robustness. Existing software tools were extended to use analytical representations of the S 4 T and the control laws to analyze and evaluate the control laws prior to testing. Lessons were learned about the complex windtunnel model and experimental testing. The open-loop flutter boundary was determined from the closed-loop systems. A MATLAB/Simulink Simulation developed under the program is available for future work to improve the CPE process. This paper is one of a series of that comprise a special session, which summarizes the S 4 T wind-tunnel program. Nomenclature CLO = control law output CPE = controller performance evaluation FRF = frequency response function or frequency responses det = determinant G = open-loop plant FLAP = wing trailing edge control surface FLAPCOM = command to FLAP FLAPEXC = excitation to FLAP HT = horizontal tail HTCOM = command to HT HTEXC = excitation to HT IBMID15I = accelerometer located on the inboard middle section of the wing LTI = linear time invariant state-space representation of a system. MIMO = multi-input multi-output NIBAFTZ = nacelle inboard aft accelerometer in the z direction ! = dynamic pressure, psf RCV = ride control vane SISO = single-input single-output ! ! = time history of ith excitation to control surface ! ! = time history of ith control law output ! ! = time history of ith plant output ! ! = matrix of frequency responses of control law outputs to excitations ! ! = matrix of frequency responses of plant outputs to excitations σ = singular value Subscripts f = flutter

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Incorporation of SemiSpan SuperSonic Transport (S4T) Aeroservoelastic Models into SAREC-ASV Simulation

Cited by 7 publications

References 10 publications

The NASA High Speed ASE Project: Computational Analyses of a Low-Boom Supersonic Configuration

The NASA High Speed ASE Project: Computational Analyses of a Low-Boom Supersonic Configuration

An Overview of the Semi-Span Super-Sonic Transport (S4T) Wind-Tunnel Model Program

Analytical and Experimental Evaluation of Digital Control Systems for the Semi-Span Super-Sonic Transport (S4T) Project

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