Overview of Dynamic Test Techniques for Flight Dynamics Research at NASA LaRC

Owens, D. Bruce; Brandon, Jay M.; Croom, Mark A.; Fremaux, C. Michael; Heim, Eugene H.; Vicroy, Dan D.

doi:10.2514/6.2006-3146

Cited by 52 publications

(32 citation statements)

References 11 publications

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“…Proper Reynolds number and dynamic scaling parameters are hard to achieve, as described in Ref. 4. One of the objectives of the FASER project is to develop advanced aerodynamic modeling methods.…”

Section: Figure 2amentioning

confidence: 99%

“…One of the objectives of the FASER project is to develop advanced aerodynamic modeling methods. Scaling effects plague the development of these methods when applying sub-scale model aerodynamics to full-scale aircraft 4 . Extensive static wind-tunnel testing has been completed through a large range of angle of attack α and sideslip angle β, with and without power.…”

Section: Figure 2amentioning

confidence: 99%

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Development of a Low-Cost Sub-Scale Aircraft for Flight Research: The FASER Project

Owens

Cox

Morelli

2006

25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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An inexpensive unmanned sub-scale aircraft was developed to conduct frequent flight test experiments for research and demonstration of advanced dynamic modeling and control design concepts. This paper describes the aircraft, flight systems, flight operations, and data compatibility including details of some practical problems encountered and the solutions found. The aircraft, named Free-flying Aircraft for Sub-scale Experimental Research, or FASER, was outfitted with high-quality instrumentation to measure aircraft inputs and states, as well as vehicle health parameters. Flight data are stored onboard, but can also be telemetered to a ground station in real time for analysis. Commercial-off-the-shelf hardware and software were used as often as possible. The flight computer is based on the PC104 platform, and runs xPC-Target software. Extensive wind tunnel testing was conducted with the same aircraft used for flight testing, and a six degree-of-freedom simulation with nonlinear aerodynamics was developed to support flight tests. = center of gravity I. IntroductionAeronautical research requires flight testing, both for validation of results obtained on the ground, and to guide the research. In general, the more complex the research issues, the more flight testing that must be done to get reliable answers. For some research, such as flight testing involving spins or other outof-control motion, or developing reconfigurable controls under failure conditions, it is impractical to use manned aircraft for flight research, because of the high cost and safety risks. Since sub-scale flying models are less expensive and unmanned, risks can be taken in research and development that could never be tolerated in a piloted flight test. There is also a need for an intermediate step between simulation and full-scale flight testing, particularly for nonlinear dynamic modeling and novel control designs. A subscale model aircraft can provide increased confidence in the methods and developments before risking the large investment ultimately necessary for a full-scale flight test demonstration. Subscale aircraft flight tests can be used early in the development phase to address these needs.In terms of funding, the trend in recent NASA spending for flight research and aeronautical research in general has been decreasing.To maintain a high degree of excellence in aeronautics research, this environment requires the development of low-cost flight research aircraft. NASA Langley Research Center (LaRC) has a long history of using sub-scale aircraft for flight research, and currently is heavily invested in using sub-scale aircraft for flight research

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Section: Figure 2amentioning

confidence: 99%

Section: Figure 2amentioning

confidence: 99%

Development of a Low-Cost Sub-Scale Aircraft for Flight Research: The FASER Project

Owens

Cox

Morelli

2006

25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference

Self Cite

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“…The forced oscillation technique, including data reduction, are described in detail in Ref. 10. Stable damping is indicated by negative values of Cm q .…”

Section: B Pitch Damping Characteristicsmentioning

confidence: 99%

Drogue Parachute Effects on the Orion Crew Module Stability

Aubuchon

Owens

Fremaux

2011

29th AIAA Applied Aerodynamics Conference

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“…The various analytical techniques used have been reviewed by Kyle et al and Greenwell. 1,2 Dynamic test techniques range from captive, wind tunnel single degree-of-freedom and free-flying, and outside free-flying. Additional wind tunnel dynamic test techniques have been reviewed by Owens et al and Tomek et al 3,4 The present study focuses on the most commonly used method, forced oscillation testing in a wind tunnel. Forced oscillation experiments are typically conducted at small amplitudes (< 5 deg) and single frequencies ranging from 0.1 to 10 Hz.…”

Section: Introduction and Problem Definitionmentioning

confidence: 99%

The Effect of Systematic Error in Forced Oscillation Testing

Williams

Landman

Flory

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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One of the fundamental problems in flight dynamics is the formulation of aerodynamic forces and moments acting on an aircraft in arbitrary motion. Classically, conventional stability derivatives are used for the representation of aerodynamic loads in the aircraft equations of motion. However, for modern aircraft with highly nonlinear and unsteady aerodynamic characteristics undergoing maneuvers at high angle of attack and/or angular rates the conventional stability derivative model is no longer valid. Attempts to formulate aerodynamic model equations with unsteady terms are based on several different wind tunnel techniques: for example, captive, wind tunnel single degree-of-freedom, and wind tunnel free-flying techniques. One of the most common techniques is forced oscillation testing. However, the forced oscillation testing method does not address the systematic and systematic correlation errors from the test apparatus that cause inconsistencies in the measured oscillatory stability derivatives. The primary objective of this study is to identify the possible sources and magnitude of systematic error in representative dynamic test apparatuses. Sensitivities of the longitudinal stability derivatives to systematic errors are computed, using a high fidelity simulation of a forced oscillation test rig, and assessed using both Design of Experiments and Monte Carlo methods. Nomenclature

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Overview of Dynamic Test Techniques for Flight Dynamics Research at NASA LaRC

Cited by 52 publications

References 11 publications

Development of a Low-Cost Sub-Scale Aircraft for Flight Research: The FASER Project

Development of a Low-Cost Sub-Scale Aircraft for Flight Research: The FASER Project

Drogue Parachute Effects on the Orion Crew Module Stability

The Effect of Systematic Error in Forced Oscillation Testing

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