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Flight evaluation of adaptive high-bandwidth control methods for unmanned helicopters

Flight evaluation of adaptive high-bandwidth control methods...

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aiaa Guidance, Navigation, and Control conference and exhibit 2002

作者： Corban, J. Eric Calise, Anthony J. Prasad, J.V.R. Hur, Jeong Kim, Nakwan Guided Systems Technologies Inc P.O. Box 1453 McDonough GA 30253 United States Georgia Institute of Technology School of Aerospace Engineering Atlanta GA 30332-0150 United States

ISBN: (纸本)9781624101083

This paper summarizes design of a high-bandwidth nonlinear adaptive attitude command system for an unmanned helicopter test bed, and presents an evaluation of the controller in both nonlinear simulation and flight test. The attitude command system features a dynamic inversion control law augmented by an on-line neural network. The design is cast in an output feedback setting. The inverting control law is based on a simple linear model of the helicopter and its actuators at the hover condition. An error observer-based method for output feedback design uses either a proportional plus derivative, or a proportional, integral and derivative form for the linear compensator. Pseudo control hedging is employed to prevent adaptation to input characteristics such as actuator position and rate saturation. A brief description is given of the unmanned helicopter testbed, real-time control system implementation, simulation, and flight test facilities. Stable adaptation for a design natural frequency up to 9 radians per second is flight demonstrated in the presence of actuator and unmodeled control rotor dynamics, system time delays, sensor noise, sensor latency, gusts and input saturation. © 2002 by the author(s).

关键词： Actuators

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modeling of the break-up of liquid oxygen droplets for application in a cryogenic rocket engine simulation code

Modeling of the break-up of liquid oxygen droplets for appli...

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38th aiaa/ASME/SAE/ASEE Joint Propulsion conference and exhibit 2002

作者： Bodèle, E. Gökalp, I. Zurbach, S. Saucereau, D. Centre National de la Recherche Scientifique Laboratoire de Combustion et Systèmes Réactifs 1 C avenue de la Recherche Scientifique 45071 Orléans Cedex 2 France SNECMA Moteurs Groupe SNECMA BP 802 - Forêt de Vernon 27208 Vernon France

ISBN: (纸本)9781624101151

From an original experimental study, a secondary atomization model for liquid oxygen droplets has been developed. The first part of this paper is a short review of experimental results and their use for the elaboration of the model. This model has been used, first, in a very simple configuration, which corresponds to the breakup of an initial single spherical droplet in a high speed and high pressure helium jet. In a second step, this model has been used in a more realistic configuration which corresponds to the MASCOTTE test bench operated by ONERA. MASCOTTE is a single co-axial injector combustor burning LOX and GH2. For this simulation, the results concern mainly the spray structure (number and size of droplets, length of the spray), and the compound mass fractions (hydrogen, liquid and gaseous oxygen) in the whole computational domain. These results are obtained for two kinds of simulation, one for which the secondary atomization model is not activated, and one for which the presently developed model is used. The comparison between these computations gives insight on the importance of the secondary atomization process for the mixing properties of a simplified co-axial LOX/GH2 injector. © 2002 by the authors.

关键词： Oxygen

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A simple-based control volume method for compressible flows on arbitrary grids

A simple-based control volume method for compressible flows ...

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32nd aiaa Fluid Dynamics conference and exhibit 2002

作者： Pržzulj, V. Basara, B. AVL United Kingdom Ltd Northwich United Kingdom Ricardo Software Shoreham-by-Sea United Kingdom Advanced Simulation Technologies AVL List GmbH Graz Austria

ISBN: (纸本)9781624101137

A SIMPLE-based control volume method is formulated for all speed turbulent flows on unstructured grids composed of arbitrary polyhedra. The key elements of the discretization procedure, with emphasis on the interpolation practice used to reconstruct the variable values and gradients at control volume faces, are outlined. Special attention is paid to derivation of the general pressure correction equation and the implementation of compressible boundary conditions for this equation. The pressure correction equation enables the introduction of the second correction step, which improves the convergence rate on highly non- orthogonal grids. Also, a simple stability measure is proposed for steady-state runs. The method incorporates the k- Ε turbulence models and its validation is done against experimentally documented flow cases that involve shocks and shock-wave/boundary-layer interactions. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Turbulence models

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Time-accurate simulations and acoustic analysis of slat free-shear-layer: Part II

Time-accurate simulations and acoustic analysis of slat free...

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Khorrami, Mehdi R. Singer, Bart A. Lockard, David P. NASA Langley Research Center Computational Modeling and Simulation Branch MS 128 Hampton VA United States

ISBN: (纸本)9781624101199

Unsteady computational simulations of a multi-element, high-lift configuration are performed. Emphasis is placed on accurate spatio-temporal resolution of the free shear layer in the slat-cove region. The excessive dissipative effects of the turbulence model, so prevalent in previous simulations, are circumvented by switching off the turbulence-production term in the slat cove region. The justifications and physical arguments for taking such a step are explained in detail. The removal of this excess damping allows the shear layer to amplify largescale structures, to achieve a proper non-linear saturation state, and to permit vortex merging. The large-scale disturbances are self-excited, and unlike our prior fully turbulent simulations, no external forcing of the shear layer is required. To obtain the farfield acoustics, the Ffowcs Williams and Hawkings equation is evaluated numerically using the simulated time-accurate flow data. The present comparison between the computed and measured farfield acoustic spectra shows much better agreement for the amplitude and frequency content than past calculations. The effect of the angle-of-attack on the slat's flow features and radiated acoustic field are also simulated and presented. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Acoustic fields

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Reconstructed sub-grid methods for acoustics predictions at all reynolds numbers

Reconstructed sub-grid methods for acoustics predictions at ...

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Batten, Paul Goldberg, Uriel Chakravarthy, Sukumar Metacomp Technologies Inc. Westlake Village CA 91361 United States

ISBN: (纸本)9781624101199

This paper considers the concept and practical application of an artificially-generated, or synthetic, unsteady, turbulent flow field, generated using statistics obtained from a quasi-steady, Reynolds-averaged Navier-Stokes (RANS) solution. Two closely-related applications of this synthesis to the extraction of noise from flow fields of arbitrarily-high Reynolds number are considered. The first application is that of hybrid RANS/Large Eddy simulation (LES), in which the reconstruction enables an energy transfer from the statistical RANS field into the resolved, large-scale (LES) components, thereby automatically providing appropriate boundary conditions for any embedded LES regions. The second application is to a non-linear acoustics solver, in which the reconstruction plays the role of a sub-grid closure, providing the volumetric sources for the unresolved, short-wavelength fluctuations. The synthetic, or artificially-generated, turbulence is constructed so as to mimic certain essential features of the statistical (RANS-represented) turbulence, including spatial and temporal correlations, turbulence energy and anisotropy. This paper considers developments relating to applications in which a limited portion of the turbulence energy spectrum has to be synthesized, and in which the underlying statistical field is both inhomogeneous and time-dependent. © 2002 by the author(s). Published by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Turbulence

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Implementation of a 622 Mbps OFDM digital modem

Implementation of a 622 Mbps OFDM digital modem

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20th aiaa International Communication Satellite Systems conference and exhibit, ICSSC 2002

作者： Kifle, Muli Bizon, Thomas P. Nguyen, Nam T. Tran, Quang K. Mortensen, Dale J. NASA Glenn Research Center MS 54-8 Cleveland OH 44135 United States ZIN Technologies Brook Park OH 44142 United States

ISBN: (纸本)9781624101113

This paper presents the implementation and initial test results of an Orthogonal Frequency Division Multiplexing (OFDM) digital modem (modulator and demodulator) with an aggregate information throughput of 622 megabits per second (Mbps). The OFDM waveform is constructed by dividing an incoming data stream into four channels, each channel using either a 16-ary Quadrature Amplitude Modulation (16QAM) scheme or an 8-Phase Shift Keying (8PSK) scheme. The generation and detection of the composite waveform are performed using Discrete Fourier Transform (DFT) and polyphase filtering, to digitally stack and band-limit the individual carriers respectively. The four-channel OFDM approach enables the implementation of a modem that can be both power and bandwidth efficient, with sufficient parallelism to meet higher data rate goals. As a result, the OFDM modem requires only a 240 MHz bandwidth to transmit 622 Mbps. Hardware and simulation results in the form of spectrum diagrams and bit-error-rate (BER) curves are also presented in this paper. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Orthogonal frequency division multiplexing

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Dynamic characteristics of a KC-10 wing-pod refueling hose by numerical simulation

Dynamic characteristics of a KC-10 wing-pod refueling hose b...

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20th aiaa Applied Aerodynamics conference 2002

作者： Vassberg, John C. Yeh, David T. Blair, Andrew J. Evert, Jacob M. The Boeing Company-Phantom Works Flight Technologies 5301 Bolsa Avenue Huntington Beach CA 92647 United States

ISBN: (纸本)9781624101106

A numerical model that simulates aerial refueling hose dynamic motion is presented. The numerical model consists of a time accurate model that solves the six degree-of-freedom hose dynamics coupled with an aerodynamic model. The aerodynamic model utilizes multiple arrays of bound and horseshoe vortices for describing the flowfield of a KC-10 tanker with and without flaps and slats deployed. The numerical model has been calibrated for cleanwing flight conditions and the hose dynamic behaviors are found to be consistent with the previous test observations. The numerical capability of modeling a receiver coupling process with a hose reel malfunction has been demonstrated for both the centerline and wingpod refueling hoses. The formation and propagation of a sine wave and the consequent hose whipping phenomena are clearly captured in the simulations. The influence of flap and slat vortices on the hose dynamics with and without a drogue attached at landing conditions is also analyzed. © 2002 by the author(s).

关键词： Hose

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Effects of liner geometry on acoustic impedance

Effects of liner geometry on acoustic impedance

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Jones, Michael G. Tracy, Maureen B. Watson, Willie R. Parrott, Tony L. Structural Acoustics Branch Aerodynamics Aerothermodynamics and Acoustics Competency NASA Langley Research Center Hampton VA United States Aeroacoustics Branch Aerodynamics Aerothermodynamics and Acoustics Competency NASA Langley Research Center Hampton VA United States Computational Modeling and Simulation Branch Aerodynamics Aerothermodynamics and Acoustics Competency NASA Langley Research Center Hampton VA United States

ISBN: (纸本)9781624101199

Current aircraft engine nacelles typically contain acoustic liners consisting of perforated sheets bonded onto honeycomb cavities. Numerous models have been developed to predict the acoustic impedance of these liners in the presence of grazing flow, and to use that information with aeroacoustic propagation codes to assess nacelle liner noise suppression. Recent efforts have provided advances in impedance eduction methodologies that offer more accurate determinations of acoustic liner properties in the presence of grazing flow. The current report provides the results of a parametric study, in which a finite element method was used to assess the effects of variations of the following geometric parameters on liner impedance, with and without the presence of grazing flow: percent open area, sheet thickness, sheet thickness-to-hole diameter ratio and cavity depth. Normal incidence acoustic impedances were determined for eight acoustic liners, consisting of punched aluminum facesheets bonded to hexcell honeycomb cavities. Similar liners were tested in the NASA Langley Research Center grazing incidence tube to determine their response in the presence of grazing flow. The resultant data provide a quantitative assessment of the effects of these perforate, single-layer liner parameters on the acoustic impedance of the liner. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Acoustic impedance

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A method for optimizing non-axisymmetric liners for multimodal sound sources

A method for optimizing non-axisymmetric liners for multimod...

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8th aiaa/CEAS Aeroacoustics conference and exhibit, 2002

作者： Watson, W.R. Jones, M.G. Parrott, T.L. Sobieski, J. NASA Langley Research Center Hampton VI 23681-2199 United States Computational Modeling and Simulation Branch Aerodynamics Aerothermodynamics and Acoustics Competency United States Structural Acoustics Branch Aerodynamics Aerothermodynamics and Acoustics Competency United States Analytical and Computational Structures Branch Structures and Material Competency United States

ISBN: (纸本)9781624101199

Central processor unit times and memory requirements for a commonly used solver are compared to that of a state-of-the-art, parallel, sparse solver. The sparse solver is then used in conjunction with three constrained optimization methodologies to assess the relative merits of non-axisymmetric versus axisymmetric liner concepts for improving liner acoustic suppression. This assessment is performed with a multimodal noise source (with equal mode amplitudes and phases) in a finite-length rectangular duct without flow. The sparse solver is found to reduce memory requirements by a factor of five and central processing time by a factor of eleven when compared with the commonly used solver. Results show that the optimum impedance of the uniform liner is dominated by the least attenuated mode, whose attenuation is maximized by the Cremer optimum impedance. An optimized, four-segmented liner with impedance segments in a checkerboard arrangement is found to be inferior to an optimized spanwise segmented liner. This optimized spanwise segmented liner is shown to attenuate substantially more sound than the optimized uniform liner and tends to be more effective at the higher frequencies. The most important result of this study is the discovery that when optimized, a spanwise segmented liner with two segments gives attenuations equal to or substantially greater than an optimized axially segmented liner with the same number of segments. © 2002 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Constrained optimization

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Direct and large eddy simulations of compressible wall-injection flows in laminar, transitional, and turbulent regimes

Direct and large eddy simulations of compressible wall-injec...

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38th aiaa/ASME/SAE/ASEE Joint Propulsion conference and exhibit 2002

作者： Wasistho, B. Haselbacher, A. Najjar, F.M. Tafti, D. Balachandar, S. Moser, R.D. Center for Simulation of Advanced Rockets University of Illinois at Urbana-Champaign Urbana IL 61801 United States Mechanical Engineering Dept. Virginia Tech United States Department of Theoretical and Applied Mechanics University of Illinois at Urbana-Champaign Urbana IL 61801 United States

ISBN: (纸本)9781624101151

Numerical simulations of compressible rocket flows are conducted in laminar, transition and turbulent regimes. The laminar simulation is carried out on a planar rocket flow without nozzle using the unsteady 2D Navier-Stokes system. The transitional and turbulent flows are performed in 3D on an extended rocket geometry with a divergent outlet using compressible large eddy simulation (LES) models. In both cases compressibility effect plays an important role. In the laminar case, pressure oscillation is forced at the outflow boundary. We compare the time averaged part of the solution with the inviscid theory of compressible rocket flow of Balakrishnan et al. (Balakrishnan, G., Linan, A., and Williams F.A., "Compressibility Effects in Thin Channels with Injection" aiaa Journal, 29 (12), 1991, pp. 2149-2154), and the oscillatory part with the acoustic layer model of Majdalani (Majdalani, J., Van Moorhem, W.K., "Improved Time-Dependent Flowfield Solution for Solid Rocket Motors" aiaa Journal, 36 (2), 1998, pp. 241-248). The mean flow from the present numerical result is in better agreement with the compressible theory than the conventional Culick's profiles (Culick, F.E.C., "Rotational Axisymmetric Mean Flow and Damping of Acoustic Waves in a Solid Propellant Rocket" aiaa Journal, 4 (8), 1966, 1462-1464), as expected. The oscillatory part of the flow agrees well in the first quarter of the axial extent, near the head end. Further downstream, the discrepancies develop rapidly between the numerical result and the acoustic layer model. The source of the difference is believed to be the interference of the hydrodynamical instabilities inherent to the flow at hand. In the transition and turbulent regimes we apply different types of LES models and degrees of physical modeling. We compare compressible dynamic eddy viscosity and dynamic mixed models and investigate the role of energy subgrid models. The measurements data of Traineau et. al. (Traineau, J.C., Hervat, P., and Kuentz

关键词： Rockets

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