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  • 1
    Electronic Resource
    Electronic Resource
    Overview of the space environmental effects observed on the retrieved long duration exposure facility (LDEF)
    Amsterdam : Elsevier
    Advances in Space Research 14 (1994), S. 7-16 
    Details
    ISSN: 0273-1177
    Source: Elsevier Journal Backfiles on ScienceDirect 1907 - 2002
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1016/0273-1177(94)90444-8
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Overview of the space environmental effects observed on the retrieved long duration exposure facility (LDEF) (1994)
    Elsevier
    Details
    Publication Date: 1994-10-01
    Print ISSN: 0273-1177
    Electronic ISSN: 1879-1948
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Lateral-directional stability investigation of the space shuttle orbiter at Mach 6 (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Lateral-directional aerodynamic data and oil-flow visualization results are pesented from four tests (conducted in two facilities using three models) which were designed to verify the hypersonic aerodynamics of the Space Shuttle orbiter at M=6. Comparisons of measured lateral-directional stability data and oil-flow results between the tests show excellent agreement, especially considering the nonuniform, unpredictable flow which occurs in the vicinity of the vertical tail. Results ere shown to be sensitive to Reynolds number with the higher Reynolds number cases producing more stable values and also showing good agreement with flight values. The results also show that the effects of Reynolds number, angle of attack, and angle of sideslip on the lateral-directional stability of future entry configuration should be carefully assessed for non-linearities.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 1; p 525-548
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    CID-720 aircraft high-environment flight instrumentation system (1986)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The high-environment flight instrumentation system was designed to acquire Langley's structural response data during the full scale transport-controlled impact demonstration test. There was only one opportunity for data acquisition. Thus, a high reliability and crashworthy design approach was implemented. The approach featured multi-level redundancy and a vigorous quality assurance testing program. Complying with an accelerated schedule, the instrumentation system was developed, tested and shipped within 18 months to Dryden Flight Research Facility. The flight instrumentation system consists of two autonomous data systems, DAS #1 and #2, and an excellent checkout subsystem. Each data system is partitioned into four pallets. The system was designed to operate on manned and unmanned flights. There are 176 data channels per data system. These channels are sequentially sampled and encoded into 1 megabit/sec pulse code modulation (PCM) data signal. To increase the probability of success, a special PCM distribution subsystem was developed. This subsystem distributes the PCM signal to two transmitters, one delay memory, and eight recorder tracks. The data on four of these trackes was digitally delayed approximately 300 msec to maximize data acquisition during impact. Therefore each data system's data is redundantly recorded onboard and on the ground. There are two time code generators. Parallel time from each is encoded into both data systems. Serial time from each is redundantly recorded on both onboard recorders. Instrumentation power is independent of aircraft power and self-contained.
    Keywords: STRUCTURAL MECHANICS
    Type: Full-Scale Transport Controlled Impact Demonstration; p 241-287
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Crash response data system for the controlled impact demonstration (CID) of a full-scale transport aircraft (1986)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: A study involving the Controlled Impact Demonstration (CID) of a transport category aircraft was conducted with the objective to improve occupant safety during survivable crash scenarios. in connection with this study, the first remotely-piloted Full-Scale Transport aircraft was purposely crashed into the California desert. The program was initated to demonstrate the effectiveness of an imisting kerosene (AMK), a fuel additive emplyed to reduce postcrash fires. The unmanned CID flight carried 73 life-like flight research dummies, multiple experiments, high-speed interior cabin cameras, and the high-environment Crash Response Data System. Attention is given to the design approach, a block diagram of the Crash Response Data System, measurements, the digital data subsystem, signal conditioning, telemetry, on-board recording, the power subsystem, preflight checkout and calibration, and aspects of system qualification.
    Keywords: AIRCRAFT INSTRUMENTATION
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Overview of the space environmental effects observed on the retrieved Long Duration Exposure Facility (LDEF) (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-04-02
    Description: The Long Duration Exposure Facility (LDEF), which encompassed 57 experiments with more than 10,000 test specimens, spent 69 months in Low Earth Orbit (LEO) before it was retrieved by the Space Shuttle in January 1990. Hundreds of LDEF investigators, after studying for over two years these retrieved test specimens and the onboard recorded data and systems hardware, have generated a unique first-hand view of the long-term synergistic effects that the LEO environment can have on spacecraft. These studies have also contributed significantly toward more accurate models of the LEO radiation, meteoroid, manmade debris and atomic oxygen environments. This paper provides an overview of some of the many LDEF observations and the implications these can have on future spacecraft such as Space Station Freedom.
    Keywords: ASTROPHYSICS
    Type: Life Sciences and Space Research 25 (2) Radiation Biology: Topical Meeting of the COSPAR Interdisciplinary Scientific Commission F of the COSPAR 29th Plenary Meeting, Washington, DC, Aug. 28-Sep. 5, 1 (ISSN 0273-1177); 14; 10; p. 7-16
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Real-gas simulation for the Shuttle Orbiter and planetary entry configurations including flight results (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: By testing configurations in a gas (like CF4) which can produce high normal-shock density ratios, such as those encountered during hypersonic entry, certain aspects of real-gas effects can be simulated. Results from force-moment, shock-shape and oil flow visualization tests are presented for both the Shuttle Orbiter and a 45 deg sphere-cone in CF4 and air at M = 6, and comparisons are made with flight results. Pitching-moment coefficients measured on a Shuttle Orbiter model in CF4 showed a nose-up increment, compared with air results, that was almost identical to the difference between preflight predictions and flight in the high hypersonic regime. The drag coefficient measured in CF4 on the 45 deg sphere-cone, which is the same configuration used on the forebody of the Pioneer Venus entry vehicles, showed excellent agreement with flight data at M = 6.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0489
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Fine-cut bluntness effects on the hypersonic static stability of a 10 degree cone (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A systematic wind-tunnel investigation has been performed on a series of spherically blunted 10-degree cones to determine Mach number and angle-of-attack effects on the hypersonic static stability. The cones, which range in nose-to-base radius ratios from 0 to 0.5, have been tested from -4 to 20 degrees angle of attack at Mach numbers of 6 and 10 in air and 20 in helium. Relatively large excursions in the center-of-pressure location were observed for small changes in cone nose bluntness. The movement of the center of pressure was also noted to become more pronounced as Mach number increased; increases in angle of attack tended to lessen the magnitude of these excursions. Computational predictions of basic aerodynamic coefficients as well as the center-of-pressure locations using both viscous and inviscid theory compare very well with the experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0503
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Measured and predicted shock shapes and aerodynamic coefficients for blunted cones at incidence in air at Mach 5.9 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental values of shock shapes (angles of attack of 0 deg and 10 deg) and static aerodynamic coefficients (angles of attack of -4 deg to 12 deg for sharp and spherically blunted cones having cone half angles of 30 deg, 45 deg, 60 deg, and 70 deg, and nose bluntness ratios of 0, 0.25, and 0.50 are presented. Shock shapes were measured at 0 deg angle of attack by using a flat faced cylinder (90 deg cone) and a hemispherically blunted cylinder (sphere). All tests were conducted in air at a free stream Mach number of 5.9 and a unit free stream Reynolds number of 2,800,000 per meter. Comparisons between measured values and predicted values were made by using several numerical and simple engineering methods.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1652 , L-13429
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The Aeroassist Flight Experiment (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The key design drivers for the Aeroassist Flight Experiment are discussed and a description is given of the flight test vehicle, its flight conditions, and instrumentation. The aeroassisted orbital transfer vehicle (AOTV) operates at higher velocities than the Space Shuttle and at higher altitudes than Apollo. Issues such as the effect of shock-layer nonequilibrium on the levels of radiative and convective heating and of viscous and real-gas effects on vehicle aerodynamic characteristics are mentioned.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: IAF PAPER 87-197
    Format: text
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    NASA TECHNICAL REPORTS
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