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  • 1
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    A piloted comparison of elastic and rigid blade-element rotor models using parallel processing technology (1990)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: A piloted comparison of rigid and aeroelastic blade-element rotor models was conducted at the Crew Station Research and Development Facility (CSRDF) at Ames Research Center. FLIGHTLAB, a new simulation development and analysis tool, was used to implement these models in real time using parallel processing technology. Pilot comments and quantitative analysis performed both on-line and off-line confirmed that elastic degrees of freedom significantly affect perceived handling qualities. Trim comparisons show improved correlation with flight test data when elastic modes are modeled. The results demonstrate the efficiency with which the mathematical modeling sophistication of existing simulation facilities can be upgraded using parallel processing, and the importance of these upgrades to simulation fidelity.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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    NASA TECHNICAL REPORTS
  • 2
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    A comparison of real-time blade-element and rotor-map helicopter simulations using parallel processing (1990)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In recent efforts by NASA, the Army, and Advanced Rotorcraft Technology, Inc. (ART), the application of parallel processing techniques to real-time simulation have been studied. Traditionally, real-time helicopter simulations have omitted the modeling of high-frequency phenomena in order to achieve real-time operation on affordable computers. Parallel processing technology can now provide the means for significantly improving the fidelity of real-time simulation, and one specific area for improvement is the modeling of rotor dynamics. This paper focuses on the results of a piloted simulation in which a traditional rotor-map mathematical model was compared with a more sophisticated blade-element mathematical model that had been implemented using parallel processing hardware and software technology.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AHS, Annual Forum; May 21, 1990 - May 23, 1990; Washington, DC; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Parameter identification of aeroelastic modes of rotary wings from transient time histories (1990)
    In:  Other Sources
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    Publication Date: 2019-07-12
    Description: A novel moving-block technique is presented for parameter-identification tasks concerning the aeroelastic modes of rotary wings, using a least-squares solver in the time domain to estimate dampings and eigenvector components. The least-squares moving-block (LSMB) technique is shown to yield superior estimates to those of the previous moving-block technique for four different analytical test cases. An additional advantage of the LSMB approach is its ability to estimate eigenvector components with good accuracy; this feature is useful in assessing the coupling of the different modes. The method can also be used to perform periodic modal identification, and is applicable to experimental data for the extraction of modal information.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 13; 669-674
    Format: text
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    NASA TECHNICAL REPORTS
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