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  • AERODYNAMICS
  • Aircraft Design, Testing and Performance
  • INSTRUMENTATION AND PHOTOGRAPHY
  • Life and Medical Sciences
  • Organic Chemistry
  • 2005-2009  (41)
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  • 1
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    Gen 2.0 Mixer/Ejector Nozzle Test at LSAF June 1995 to July 1996 (2005)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: Testing of the HSCT Generation 2.0 nozzle model hardware was conducted at the Boeing Low Speed Aeroacoustic Facility, LSAF. Concurrent measurements of noise and thrust were made at critical takeoff design conditions for a variety of mixer/ejector model hardware. Design variables such as suppressor area ratio, mixer area ratio, liner type and thickness, ejector length, lobe penetration, and mixer chute shape were tested. Parallel testing was conducted at G.E.'s Cell 41 acoustic free jet facility to augment the LSAF test. The results from the Gen 2.0 testing are being used to help shape the current nozzle baseline configuration and guide the efforts in the upcoming Generation 2.5 and 3.0 nozzle tests. The Gen 2.0 results have been included in the total airplane system studies conducted at MDC and Boeing to provide updated noise and thrust performance estimates.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NASA/CR-2005-213334 , E-14804
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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    Large Engine Technology Program. Task 21: Rich Burn Liner for Near Term Experimental Evaluations (2005)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: The objective of the task reported herein, which was conducted as part of the NASA sponsored Large Engine Technology program, was to define and evaluate a near-term rich-zone liner construction based on currently available materials and fabrication processes for a Rich-Quench-Lean combustor. This liner must be capable of operation at the temperatures and pressures of simulated HSCT flight conditions but only needs sufficient durability for limited duration testing in combustor rigs and demonstrator engines in the near future. This must be achieved at realistic cooling airflow rates since the approach must not compromise the emissions, performance, and operability of the test combustors, relative to the product engine goals. The effort was initiated with an analytical screening of three different liner construction concepts. These included a full cylinder metallic liner and one with multiple segments of monolithic ceramic, both of which incorporated convective cooling on the external surface using combustor airflow that bypassed the rich zone. The third approach was a metallic platelet construction with internal convective cooling. These three metal liner/jacket combinations were tested in a modified version of an existing Rich-Quench-Lean combustor rig to obtain data for heat transfer model refinement and durability verification.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NASA/CR-2005-213136 , E-14650
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    INITIAL ASSESSMENT OF SURFACE PRESSURE CHARACTERISTICS OF TWO ROTARY WING UAV DESIGNS (2006)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents results of an experimental investigation of two rotary-wing UAV designs. The primary goal of the investigation was to provide a set of interactional aerodynamic data for an emerging class of rotorcraft. The present paper provides an overview of the test and an introduction to the test articles, and instrumentation. Sample data in the form of fixed system pressure coefficient response to changes in configuration attitude and flight condition for both rotor off and on conditions are presented. The presence of the rotor is seen to greatly affect the magnitude of the response. Pressure coefficients were measured using both conventional pressure taps and via pressure sensitive paint. Comparisons between the two methods are presented and demonstrate that the pressure sensitive paint is a promising method; however, further work on the technique is required.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: AHS International 62nd Annual Forum and Technology Display; May 09, 2006 - May 11, 2006; Phoenix, AZ; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 4
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    Bias Momentum Sizing for Hovering Dual-Spin Platforms (2005)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: An atmospheric flight vehicle in hover is typically controlled by varying its thrust vector. Achieving both levitation and control with the propulsion system places considerable demands on it for agility and precision, particularly if the vehicle is statically unstable, or nearly so. These demands can be relaxed by introducing an appropriately sized angular momentum bias about the vehicle's yaw axis, thus providing an additional margin of attitude stability about the roll and pitch axes. This paper describes an approach for specifying the appropriate size of such angular momentum bias, based on the vehicle s physical parameters and its disturbance environment. It also describes several simplifications that provide a more physical and intuitive understanding of the dynamics. This will enhance the possibility of practically applying this technology to a flying vehicle.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: AIAA Paper 2005-5973 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 15, 2005 - Aug 18, 2005; San Francisco, CA; United States
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    CMG-Augmented Control of a Hovering VTOL Platform (2007)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper describes how Control Moment Gyroscopes (CMGs) can be used for stability augmentation to a thrust vectoring system for a generic Vertical Take-Off and Landing platform. The response characteristics of the platform which uses only thrust vectoring and a second configuration which includes a single-gimbal CMG array are simulated and compared for hovering flight while subject to severe air turbulence. Simulation results demonstrate the effectiveness of a CMG array in its ability to significantly reduce the agility requirement on the thrust vectoring system. Albeit simplifying physical assumptions on a generic CMG configuration, the numerical results also suggest that reasonably sized CMGs will likely be sufficient for a small hovering vehicle.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: AIAA Paper 2007-6458 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 20, 2007 - Aug 23, 2007; Hilton Head, SC; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 6
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    Plans and Status of Wind-Tunnel Testing Employing an Aeroservoelastic Semispan Model (2007)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: This paper presents the research objectives, summarizes the pre-wind-tunnel-test experimental results to date, summarizes the analytical predictions to date, and outlines the wind-tunnel-test plans for an aeroservoelastic semispan wind-tunnel model. The model is referred to as the Supersonic Semispan Transport (S4T) Active Controls Testbed (ACT) and is based on a supersonic cruise configuration. The model has three hydraulically-actuated surfaces (all-movable horizontal tail, all-movable ride control vane, and aileron) for active controls. The model is instrumented with accelerometers, unsteady pressure transducers, and strain gages and will be mounted on a 5-component sidewall balance. The model will be tested twice in the Langley Transonic Dynamics Tunnel (TDT). The first entry will be an "open-loop" model-characterization test; the second entry will be a "closed-loop" test during which active flutter suppression, gust load alleviation and ride quality control experiments will be conducted.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: AIAA 2007-1770 , 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Apr 23, 2007 - Apr 26, 2007; Waikiki, HI; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 7
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    General Matrix Inversion for the Calibration of Electric Field Sensor Arrays on Aircraft Platforms (2006)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-12
    Beschreibung: We have developed a matrix calibration procedure that uniquely relates the electric fields measured at the aircraft with the external vector electric field and net aircraft charge. Our calibration method is being used with all of our aircraft/electric field sensing combinations and can be generalized to any reasonable combination of electric field measurements and aircraft. We determine a calibration matrix that represents the individual instrument responses to the external electric field. The aircraft geometry and configuration of field mills (FMs) uniquely define the matrix. The matrix can then be inverted to determine the external electric field and net aircraft charge from the FM outputs. A distinct advantage of the method is that if one or more FMs need to be eliminated or de-emphasized (for example, due to a malfunction), it is a simple matter to reinvert the matrix without the malfunctioning FMs. To demonstrate our calibration technique, we present data from several of our aircraft programs (ER-2, DC-8, Altus, Citation).
    Schlagwort(e): Aircraft Design, Testing and Performance
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
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    Wake Vortex Wingtip-Turbine Powered Circulation Control High-Lift System (2005)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-11
    Beschreibung: NASA s Vehicle Systems Program is investing in aeronautics technology development across six vehicle sectors, in order to improve future air travel. These vehicle sectors include subsonic commercial transports, supersonic vehicles, Uninhabited Aerial Vehicles (UAVs), Extreme Short Takeoff and Landing (ESTOL) vehicles, Rotorcraft, and Personal Air Vehicles (PAVs). While the subsonic transport is firmly established in U.S. markets, the other vehicle sectors have not developed a sufficient technology or regulatory state to permit widespread, practical use. The PAV sector has legacy products in the General Aviation (GA) market, but currently only accounts for negligible revenue miles, sales, or market share of personal travel. In order for PAV s to ever capture a significant market, these small aircraft require technologies that permit them to be less costly, environmentally acceptable, safer, easier to operate, more efficient, and less dependent on large support infrastructures.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: Proceedings of the 2004 NASA/ONR Circulation Control Workshop, Part 2; 641-674; NASA/CP-2005-213509/PT2
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
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    Change Detection Experiments Using Low Cost UAVs (2005)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-27
    Beschreibung: This paper presents the progress in the development of a low-cost change-detection system. This system is being developed to provide users with the ability to use a low-cost unmanned aerial vehicle (UAV) and image processing system that can detect changes in specific fixed ground locations using video provided by an autonomous UAV. The results of field experiments conducted with the US Army at Ft. A.P.Hill are presented.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: Infotech@Aerospace; 26-29 Sept. 2005; Arlington, VA; United States
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
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    Slotted Aircraft Wing (2006)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: A swept aircraft wing includes a leading airfoil element and a trailing airfoil element. At least one full-span slot is defined by the wing during at least one transonic condition of the wing. The full-span slot allows a portion of the air flowing along the lower surface of the leading airfoil element to split and flow over the upper surface of the trailing airfoil element so as to achieve a performance improvement in the transonic condition.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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