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  • AIRCRAFT
  • Aircraft Design, Testing and Performance
  • Aircraft Stability and Control
  • Cell & Developmental Biology
  • GENERAL
  • 2000-2004  (112)
  • 1955-1959  (86)
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Keywords
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Year
  • 1
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    Multidisciplinary Techniques and Novel Aircraft Control Systems (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Aircraft Morphing Program at NASA Langley Research Center explores opportunities to improve airframe designs with smart technologies. Two elements of this basic research program are multidisciplinary design optimization (MDO) and advanced flow control. This paper describes examples where MDO techniques such as sensitivity analysis, automatic differentiation, and genetic algorithms contribute to the design of novel control systems. In the test case, the design and use of distributed shape-change devices to provide low-rate maneuvering capability for a tailless aircraft is considered. The ability of MDO to add value to control system development is illustrated using results from several years of research funded by the Aircraft Morphing Program.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2000-4848 , Multidisciplinary Analysis and Optimization; Sep 06, 2000 - Sep 08, 2000; Long Beach, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Multidisciplinary Techniques and Novel Aircraft Control Systems (2000)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Aircraft Morphing Program at NASA Langley Research Center explores opportunities to improve airframe designs with smart technologies. Two elements of this basic research program are multidisciplinary design optimization (MDO) and advanced flow control. This paper describes examples where MDO techniques such as sensitivity analysis, automatic differentiation, and genetic algorithms contribute to the design of novel control systems. In the test case, the design and use of distributed shapechange devices to provide low-rate maneuvering capability for a tailless aircraft is considered. The ability of MDO to add value to control system development is illustrated using results from several years of research funded by the Aircraft Morphing Program.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2000-4848 , Multidisciplinary Analysis and Optimization; Sep 06, 2000 - Sep 08, 2000; Long Beach, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    HSCT4.0 Application: Software Requirements Specification (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The software requirements for the High Performance Computing and Communication Program High Speed Civil Transport application project, referred to as HSCT4.0, are described. The objective of the HSCT4.0 application project is to demonstrate the application of high-performance computing techniques to the problem of multidisciplinary design optimization of a supersonic transport configuration, using high-fidelity analysis simulations. Descriptions of the various functions (and the relationships among them) that make up the multidisciplinary application as well as the constraints on the software design arc provided. This document serves to establish an agreement between the suppliers and the customer as to what the HSCT4.0 application should do and provides to the software developers the information necessary to design and implement the system.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2001-210867 , NAS 1.15:210867 , L-18072
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    External-store drag reduction at transonic and low supersonic Mach numbers by application of Baldwin's moment-of-area rule (1955)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: NACA Conf. on Aerodyn. of High Speed Aircraft; p 93-103
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    INVESTIGATION OF STATIC PRESSURES AND BOUNDARY-LAYER CHARACTERISTICS ON THE FORWARD PARTS OF NINE FUSELAGES OF VARIOUS CROSS-SECTIONAL SHAPES AT M INFINITY EQUAL 2.01 (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Boundary layer characteristics of fuselages of various cross sectional shapes at static pressure
    Keywords: AIRCRAFT
    Type: NACA-RM-L56I13
    Format: application/pdf
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  • 6
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    AERODYNAMIC CHARACTERISTICS OF SOME FAMILIES OF BLUNT BODIES AT TRANSONIC SPEEDS (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Static stability and drag characteristics of blunt bodies at transonic speed
    Keywords: AIRCRAFT
    Type: NASA-MEMO-10-28-58L
    Format: text
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  • 7
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    PERFORMANCE OF AN ALL-INTERNAL CONICAL COMPRESSION INLET WITH ANNULAR THROAT BLEED AT MACH NUMBER 5.0 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Internal compression inlet with throat bleed-off at hypersonic flow
    Keywords: AIRCRAFT
    Type: NACA-RM-E58E14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    The Influence of Mesh Density on the Impact Response of a Shuttle Leading-Edge Panel Finite Element Simulation (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A study was performed to examine the influence of varying mesh density on an LS-DYNA simulation of a rectangular-shaped foam projectile impacting the space shuttle leading edge Panel 6. The shuttle leading-edge panels are fabricated of reinforced carbon-carbon (RCC) material. During the study, nine cases were executed with all possible combinations of coarse, baseline, and fine meshes of the foam and panel. For each simulation, the same material properties and impact conditions were specified and only the mesh density was varied. In the baseline model, the shell elements representing the RCC panel are approximately 0.2-in. on edge, whereas the foam elements are about 0.5-in. on edge. The element nominal edge-length for the baseline panel was halved to create a fine panel (0.1-in. edge length) mesh and doubled to create a coarse panel (0.4-in. edge length) mesh. In addition, the element nominal edge-length of the baseline foam projectile was halved (0.25-in. edge length) to create a fine foam mesh and doubled (1.0- in. edge length) to create a coarse foam mesh. The initial impact velocity of the foam was 775 ft/s. The simulations were executed in LS-DYNA version 960 for 6 ms of simulation time. Contour plots of resultant panel displacement and effective stress in the foam were compared at five discrete time intervals. Also, time-history responses of internal and kinetic energy of the panel, kinetic and hourglass energy of the foam, and resultant contact force were plotted to determine the influence of mesh density. As a final comparison, the model with a fine panel and fine foam mesh was executed with slightly different material properties for the RCC. For this model, the average degraded properties of the RCC were replaced with the maximum degraded properties. Similar comparisons of panel and foam responses were made for the average and maximum degraded models.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2004-213501 , ARL-TR-3337 , L-19059
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Occupant Responses in a Full-Scale Crash Test of the Sikorsky ACAP Helicopter (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A full-scale crash test of the Sikorsky Advanced Composite Airframe Program (ACAP) helicopter was performed in 1999 to generate experimental data for correlation with a crash simulation developed using an explicit nonlinear, transient dynamic finite element code. The airframe was the residual flight test hardware from the ACAP program. For the test, the aircraft was outfitted with two crew and two troop seats, and four anthropomorphic test dummies. While the results of the impact test and crash simulation have been documented fairly extensively in the literature, the focus of this paper is to present the detailed occupant response data obtained from the crash test and to correlate the results with injury prediction models. These injury models include the Dynamic Response Index (DRI), the Head Injury Criteria (HIC), the spinal load requirement defined in FAR Part 27.562(c), and a comparison of the duration and magnitude of the occupant vertical acceleration responses with the Eiband whole-body acceleration tolerance curve.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2002-211733 , NAS 1.15:211733 , ARL-TR-2735 , L-18189 , AHS International: The Vertical Flight Society''s 58th Annual Forum and Technology Display; Jun 11, 2002 - Jun 13, 2002; Montreal; Canada
    Format: application/pdf
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  • 10
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    Nonlinear Analysis of Airfoil High-Intensity Gust Response Using a High-Order Prefactored Compact Code (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The nonlinear response of symmetric and loaded airfoils to an impinging vortical gust is investigated in the parametric space of gust dimension, intensity, and frequency. The study, which was designed to investigate the validity limits for a linear analysis, is implemented by applying a nonlinear high-order prefactored compact code and comparing results with linear solutions from the GUST3D frequency-domain solver. Both the unsteady aerodynamic and acoustic gust responses are examined.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2002-2535 , 8th AIAA/CEAS Aeroacoustics Conference and Exhibit; Jun 17, 2002 - Jun 19, 2002; Breckenridge, CO; United States
    Format: application/pdf
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