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  • Aircraft Design, Testing and Performance  (9)
  • Air Transportation and Safety  (8)
  • Astrodynamics  (7)
  • 2010-2014  (24)
  • 1
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    Exploration of Configuration Options for a Large Civil Compound Helicopter (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Multiple compound helicopter configurations are designed using a combination of rotorcraft sizing and comprehensive analysis codes. Results from both the conceptual design phase and rotor comprehensive analysis are presented. The designs are evaluated for their suitability to a short-to-medium-haul civil transport mission carrying a payload of 90 passengers. Multiple metrics are used to determine the best configuration, with heavy emphasis placed on minimizing fuel burn.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN6212 , 69th American Helicopter Society Annual Forum; May 21, 2013 - May 23, 2013; Phoenix, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Application of Climate Impact Metrics to Civil Tiltrotor Design (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Multiple metrics are applied to the design of a large civil tiltrotor, integrating minimum cost and minimum environmental impact. The design mission is passenger transport with similar range and capacity to a regional jet. Separate aircraft designs are generated for minimum empty weight, fuel burn, and environmental impact. A metric specifically developed for the design of aircraft is employed to evaluate emissions. The designs are generated using the NDARC rotorcraft sizing code, and rotor analysis is performed with the CAMRAD II aeromechanics code. Design and mission parameters such as wing loading, disk loading, and cruise altitude are varied to minimize both cost and environmental impact metrics. This paper presents the results of these parametric sweeps as well as the final aircraft designs.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN7037 , AIAA Aerospace Sciences Meeting; Jan 07, 2013 - Jan 10, 2013; Grapevine, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Commercial Crew Program Overview (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Air Transportation and Safety
    Type: KSC-2011-279R , 32nd HIGH TEMPLE Workshop; Jan 31, 2012; Palm Springs, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Magnetospheric Multiscale (MMS) Mission Navigation Concept (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Astrodynamics
    Type: GSFC.CPR.5479.2011 , Young Professional, Student, and Education Conference (YPSE-11); Nov 04, 2011; MD; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Comparison of Statistical Estimation Techniques for Mars Entry, Descent, and Landing Reconstruction from MEDLI-like Data Sources (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flight data from an entry, descent, and landing (EDL) sequence can be used to reconstruct the vehicle's trajectory, aerodynamic coefficients and the atmospheric profile experienced by the vehicle. Past Mars missions have contained instruments that do not provide direct measurement of the freestream atmospheric conditions. Thus, the uncertainties in the atmospheric reconstruction and the aerodynamic database knowledge could not be separated. The upcoming Mars Science Laboratory (MSL) will take measurements of the pressure distribution on the aeroshell forebody during entry and will allow freestream atmospheric conditions to be partially observable. This data provides a mean to separate atmospheric and aerodynamic uncertainties and is part of the MSL EDL Instrumentation (MEDLI) project. Methods to estimate the flight performance statistically using on-board measurements are demonstrated here through the use of simulated Mars data. Different statistical estimators are used to demonstrate which estimator best quantifies the uncertainties in the flight parameters. The techniques demonstrated herein are planned for application to the MSL flight dataset after the spacecraft lands on Mars in August 2012.
    Keywords: Astrodynamics
    Type: AIAA Paper 2012-0400 , NF1676L-14037 , 50th AIAA Aerospace Sciences Meeting and Exhibit; Jan 09, 2012 - Jan 12, 2012; Nashville, TN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aeroacoustic and Performance Simulations of a Test Scale Open Rotor (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper explores a comparison between experimental data and numerical simulations of the historical baseline F31/A31 open rotor geometry. The experimental data were obtained at the NASA Glenn Research Center s Aeroacoustic facility and include performance and noise information for a variety of flow speeds (matching take-off and cruise). The numerical simulations provide both performance and aeroacoustic results using the NUMECA s Fine-Turbo analysis code. A non-linear harmonic method is used to capture the rotor/rotor interaction.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2013-217707 , AIAA Paper-2012-3823 , E-18631 , 48th Joint Propulsion Conference and Exhibit; Jul 30, 2012 - Aug 01, 2012; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Conceptual Design and Performance Analysis for a Large Civil Compound Helicopter (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A conceptual design study of a large civil compound helicopter is presented. The objective is to determine how a compound helicopter performs when compared to both a conventional helicopter and a tiltrotor using a design mission that is shorter than optimal for a tiltrotor and longer than optimal for a helicopter. The designs are generated and analyzed using conceptual design software and are further evaluated with a comprehensive rotorcraft analysis code. Multiple metrics are used to determine the suitability of each design for the given mission. Plots of various trade studies and parameter sweeps as well as comprehensive analysis results are presented. The results suggest that the compound helicopter examined for this study would not be competitive with a tiltrotor or conventional helicopter, but multiple possibilities are identified for improving the performance of the compound helicopter in future research.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN4612 , AHS Future Vertical Lift Aircraft Design Conference; Jan 18, 2012 - Jan 20, 2012; San Francisco, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    TSAFE Interface Control Document v 2.0 (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This document specifies the data interface for TSAFE, the Tactical Separation-Assured Flight Environment. TSAFE is a research prototype of a software application program for alerting air traffic controllers to imminent conflicts in enroute airspace. It is intended for Air Route Traffic Control Centers ("Centers") in the U.S. National Airspace System. It predicts trajectories for approximately 3 minutes into the future, searches for conflicts, and sends data about predicted conflicts to the client, which uses the data to alert an air traffic controller of conflicts. TSAFE itself does not provide a graphical user interface.
    Keywords: Air Transportation and Safety
    Type: NASA/TM-2013-216034 , ARC-E-DAA-TN5498
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Trajectory specification for high capacity air traffic control (2010)
    In:  CASI
    Details
    Publication Date: 2019-08-24
    Description: Method and system for analyzing and processing information on one or more aircraft flight paths, using a four-dimensional coordinate system including three Cartesian or equivalent coordinates (x, y, z) and a fourth coordinate .delta. that corresponds to a distance estimated along a reference flight path to a nearest reference path location corresponding to a present location of the aircraft. Use of the coordinate .delta., rather than elapsed time t, avoids coupling of along-track error into aircraft altitude and reduces effects of errors on an aircraft landing site. Along-track, cross-track and/or altitude errors are estimated and compared with a permitted error bounding space surrounding the reference flight path.
    Keywords: Air Transportation and Safety
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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