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  • Aircraft Design, Testing and Performance
  • Cell & Developmental Biology
  • GENERAL
  • 2000-2004  (88)
  • 1955-1959  (65)
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Keywords
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Years
Year
  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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    A Summary of DOD-Sponsored Research Performed at NASA Langley's Impact Dynamics Research Facility (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Impact Dynamics Research Facility (IDRF) is a 240-ft.-high gantry structure located at NASA Langley Research Center in Hampton, Virginia. The IDRF was originally built in the early 1960's for use as a Lunar Landing Research Facility. As such, the facility was configured to simulate the reduced gravitational environment of the Moon, allowing the Apollo astronauts to practice lunar landings under realistic conditions. In 1985, the IDRF was designated a National Historic Landmark based on its significant contributions to the Apollo Moon Landing Program. In the early 1970's the facility was converted into its current configuration as a full-scale crash test facility for light aircraft and rotorcraft. Since that time, the IDRF has been used to perform a wide variety of impact tests on full-scale aircraft, airframe components, and space vehicles in support of the General Aviation (GA) aircraft industry, the U.S. Department of Defense (DOD), the rotorcraft industry, and the NASA Space program. The objectives of this paper are twofold: to describe the IDRF facility and its unique capabilities for conducting structural impact testing, and to summarize the impact tests performed at the IDRF in support of the DOD. These tests cover a time period of roughly 2 1/2 decades, beginning in 1975 with the full-scale crash test of a CH-47 Chinook helicopter, and ending in 1999 with the external fuel system qualification test of a UH-60 Black Hawk helicopter. NASA officially closed the IDRF in September 2003; consequently, it is important to document the past contributions made in improved human survivability and impact tolerance through DOD-sponsored research performed at the IDRF.
    Keywords: Aircraft Design, Testing and Performance
    Type: AHS international 60th Annual Forum and Technology Display; Jun 07, 2004 - Jun 10, 2004; Baltimore, MD; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Development of Micro Air Reconnaissance Vehicle as a Test Bed for Advanced Sensors and Electronics (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the development of a Micro/Mini Air Reconnaissance Vehicle for advanced sensors and electronics at NASA Langley Research Center over the last year. This vehicle is expected to have a total weight of less than four pounds, a design velocity of 40 mph, an endurance of 15-20 minutes, and a maximum range of 5km. The vehicle has wings that are simple to detach yet retain the correct alignment. The upper fuselage surface has a quick release hatch used to access the interior and also to mount the varying propulsion systems. The sensor suite developed for this vehicle consists of a Pitot-static measurement system for determining air speed, an absolute pressure measurement for determining altitude, magnetic direction measurement, and three orthogonal gyros to determine body angular rates. Swarming GPS-guidance and in-flight maneuvering is discussed, as well as design and installation of some other advance sensors like MEMS microphones, infrared cameras, GPS, humidity sensors, and an ultrasonic sonar sensor. Also low cost, small size, high performance control and navigation system for the Micro Air Vehicle is discussed. At the end, laboratory characterization of different sensors, motors, propellers, and batteries will be discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2002-3411 , 1st AIAA Unmanned Aerospace Vehicles, Systems, Technologies and Operations Technical Conference and Workshop; May 20, 2002 - May 23, 2002; Portsmouth, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Full-Scale Crash Test and Finite Element Simulation of a Composite Prototype Helicopter (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A full-scale crash test of a prototype composite helicopter was performed at the Impact Dynamics Research Facility at NASA Langley Research Center in 1999 to obtain data for validation of a finite element crash simulation. The helicopter was the flight test article built by Sikorsky Aircraft during the Advanced Composite Airframe Program (ACAP). The composite helicopter was designed to meet the stringent Military Standard (MIL-STD-1290A) crashworthiness criteria and was outfitted with two crew and two troop seats and four anthropomorphic dummies. The test was performed at 38-ft/s vertical and 32.5-ft/s horizontal velocity onto a rigid surface. An existing modal-vibration model of the Sikorsky ACAP helicopter was converted into a model suitable for crash simulation. A two-stage modeling approach was implemented and an external user-defined subroutine was developed to represent the complex landing gear response. The crash simulation was executed with a nonlinear, explicit transient dynamic finite element code. Predictions of structural deformation and failure, the sequence of events, and the dynamic response of the airframe structure were generated and the numerical results were correlated with the experimental data to validate the simulation. The test results, the model development, and the test-analysis correlation are described.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TP-2003-212641 , L-18228 , NAS 1.60:212641 , ARL-TR-2824
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A History of Full-Scale Aircraft and Rotorcraft Crash Testing and Simulation at NASA Langley Research Center (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper summarizes 2-1/2 decades of full-scale aircraft and rotorcraft crash testing performed at the Impact Dynamics Research Facility (IDRF) located at NASA Langley Research Center in Hampton, Virginia. The IDRF is a 240-ft.-high steel gantry that was built originally as a lunar landing simulator facility in the early 1960's. It was converted into a full-scale crash test facility for light aircraft and rotorcraft in the early 1970 s. Since the first full-scale crash test was preformed in February 1974, the IDRF has been used to conduct: 41 full-scale crash tests of General Aviation (GA) aircraft including landmark studies to establish baseline crash performance data for metallic and composite GA aircraft; 11 full-scale crash tests of helicopters including crash qualification tests of the Bell and Sikorsky Advanced Composite Airframe Program (ACAP) prototypes; 48 Wire Strike Protection System (WSPS) qualification tests of Army helicopters; 3 vertical drop tests of Boeing 707 transport aircraft fuselage sections; and, 60+ crash tests of the F-111 crew escape module. For some of these tests, nonlinear transient dynamic codes were utilized to simulate the impact response of the airframe. These simulations were performed to evaluate the capabilities of the analytical tools, as well as to validate the models through test-analysis correlation. In September 2003, NASA Langley closed the IDRF facility and plans are underway to demolish it in 2007. Consequently, it is important to document the contributions made to improve the crashworthiness of light aircraft and rotorcraft achieved through full-scale crash testing and simulation at the IDRF.
    Keywords: Aircraft Design, Testing and Performance
    Type: 4th Triennial International Aircraft and Cabin Safety Research Conference; Nov 15, 2004 - Nov 18, 2004; Lisbon; Portugal
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
    Electronic Resource
    Electronic Resource
    The histones and lipoproteins of the liver cell nucleusWe gratefully acknowledge the support of The National Cancer Institute, National Institutes of Health, United States Public Health Service, Research Grant No. C-994 which has made this work possible. (1959)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 53 (1959), S. 377-392 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030530304
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    Paper (German National Licenses)
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  • 10
    Electronic Resource
    Electronic Resource
    Aldol and ketol condensations (1959)
    Philadelphia : Wiley-Blackwell
    Journal of Cellular and Comparative Physiology 54 (1959), S. 89-107 
    Details
    ISSN: 0095-9898
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Additional Material: 22 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1030540409
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    Paper (German National Licenses)
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