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  • Polymer and Materials Science  (36)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (28)
  • 1980-1984  (32)
  • 1975-1979  (32)
  • 1
    Publication Date: 2019-06-28
    Description: The approach, study results, and recommendations for defining and selecting space station architectural options are described. Space station system architecture is defined as the arrangement of elements (manned and unmanned on-orbit facilities, shuttle vehicles, orbital transfer vehicles, etc.), the number of these elements, their location (orbital inclination and altitude, and their functional performance capability, power, volume, crew, etc.). Architectural options are evaluated based on the degree of mission capture versus cost and required funding rate. Mission capture refers to the number of missions accommodated by the particular architecture.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173694 , NAS 1.26:173694 , MDC-H0537
    Format: application/pdf
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  • 2
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    In:  CASI
    Publication Date: 2019-06-27
    Description: The thermal design work completed for the Thermal Protection System (TPS) of the Space Shuttle System (TPS) of the space shuttle vehicle was documented. This work was divided into three phases, the first two of which reported in previous documents. About 22 separate tasks were completed in phase III, such as: hot gas facility (HGF) support, guarded tank support, shuttle external tank (ET) thermal design handbook support, etc.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144185 , LMSC-HREC-TR-D496704
    Format: application/pdf
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  • 3
    Publication Date: 2019-06-28
    Description: A very simple, yet accurate, heuristic solution for the spiral path of the angular momentum vector during spin-up and spin-down maneuvers of rigid body spacecraft is presented. A two-burn scheme is proposed consisting of a burn, a coast, and a second burn of the spin thruster. The appropriate burn times are found by a transcendental equation similar to Kepler's equation. Numerical results verify the accuracy of the burn, coast, and burn times given by closed form expressions. The scheme can also be applied to the problem of axial thrusting during constant spin.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 83-408
    Format: text
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  • 4
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    In:  Other Sources
    Publication Date: 2019-06-28
    Description: The application of quaternions for the articulation control of the Galileo scan platform is presented in this paper. The purpose of selecting quaternions is to minimize onboard computation time and program size. Attention has been focused on performing inertial pointing while the spacecraft is in a dual spin configuration. Target quaternion and relative target quaternion are introduced and used to specify the target position of the scan platform for point-to-point absolute slews and mosaic relative slews, respectively. The pointing error of the platform is represented by an error quaternion which is converted into gimbal angular errors defining the attitude change. For path control, a moving target quaternion is generated; the corresponding tracking error quaternion and the related spacecraft motion compensation capability are also addressed. A sample slew case is used to demonstrate the implementation of these concepts.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 83-321
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  • 5
    Publication Date: 2019-06-28
    Description: Previously cited in issue 21, p. 3639, Accession no. A81-44132
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 6; 491-498
    Format: text
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  • 6
    Publication Date: 2019-06-28
    Description: For electron beam incidence on large specimens of Kapton thermal blanket material, surface arc discharges are shown to cause damage consisting of punchthrough holes which act as focal points for other types of damage, including subsurface tunnels, blowout holes and surface breakup. Under electron bombardment, dielectric sheet specimens separated by a gap are shown to discharge simultaneously. Teflon specimens which have been brushed or rubbed are shown to exhibit directional guidance of discharge arcs, and this phenomenon has been used to generate straight arcs whose velocities have been measured optically.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: in ESA Spacecraft Mater. in a Space Environ.; p 263-268
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  • 7
    Publication Date: 2019-07-27
    Description: The drift rates of the attitude control gyros onboard the Viking Orbiters were calibrated several times during flight. The calibration was performed by engaging the gyro control of attitude for a six-hour period, recording the Viking Orbiter coordinates of the sun and the roll reference star as a function of time, and processing these data by a computer program. The computer program calculated drift rates for each data increment, and then smoothed the calculated rate versus the time function for all the data on the basis of a Gauss-Markov gyro-drift model. The effects of data noise were minimized by using a relatively long time constant in the Gauss-Markov model and by empirically determining a set of corrections for celestial inertial scale factor error differences. In this way the rms error of the data fit was lessened.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astrodynamics Specialist Conference; Sept. 7-9, 1977; Jackson Hole, WY; US
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  • 8
    Publication Date: 2019-07-13
    Description: Design and performance evaluations of an onboard inertial attitude determination system for a dual-spin planetary spacecraft are presented. A quaternion integration algorithm and a rate estimator sequentially determine the scan platform's inertial attitude and rate from the drift and misalignment compensated gyro outputs. A least-squares estimator algorithm processes the star transit data from a rotor-mounted star scanner, and provides periodic updates of the scan platform's attitude as a means of correcting the drift of the quaternion integration algorithm. Computer simulated algorithm performance in the presence of nutation and sensor noise are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-1764 , Guidance and Control Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
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  • 9
    ISSN: 0021-8995
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Notes: High-density polyethylene up to about 30% by weight was melt-mixed with polypropylene and short-glass-fiber-reinforced polypropylene. The presence of high-density polyethylene and glass fibers in the polypropylene matrix affects its crystallization characteristics, which were studied with the help of differential scanning calorimetry. The blend and composite samples have a large number of polypropylene domains apparently due to an abundance of surface nuclei; as a result, the tensile strength, tensile modulus, and toughness are enhanced. The temperature dependence of shear modulus and logarithmic decrement indicate that high-density polyethylene can have plasticizing effect below the glass transition temperature of polypropylene. The scanning electron micrographs of fractured ends show the presence of dispersed domains in the composite samples.
    Additional Material: 14 Ill.
    Type of Medium: Electronic Resource
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  • 10
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Materialwissenschaft und Werkstofftechnik 6 (1975), S. 361-367 
    ISSN: 0933-5137
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: The Use of Titanium Castings to Produce a Complex Shaped Intermediate Casing of RB 199.This paper describes the present position on a highly stressed casing and its functions in the RB 199-34 R engine. When the parts of the casing are made from solid forged titanium billets, up to 93% of the material used is machined away. For this reason, the most complicated parts of the casing were procured as castings and welded together by TIG welding. The paper describes the present quality standard of the titanium castings. The tests on the materials and their mechanical properties show that the castings are inferior to the forgings only with respect to their HCF behaviour and their elongation at rupture. Macroscopic flaws are not entirely inevitable but can be detected by X-ray tests. The future prospects for titanium castings are considered favourable.
    Notes: Der Bericht beschreibt die Lage eines hochbeanspruchten Gehäuses und dessen Funktionen im Triebwerk RB 199-34 R. Bei der Herstellung der Einzelteile des Gehäuses aus massiv geschmiedeten Titanblöcken wird bis zu 93% des eingesetzten Materials zerspant. Die kompliziertesten Partien des Gehäuses wurden deshalb als Gußteil bezogen und mittels WIG-Schweißung verbunden. Der Bericht beschreibt den heutigen Qualitätsstand der Titangußteile. Die Ergebnisse der Werkstoff- und Festigkeitsuntersuchungen weisen nur im HCF-Verhalten und der Bruchdehnung Nachteile des Gusses gegenüber dem geschmiedeten Material aus. Makroskopische Fehler sind nicht vollständing vermeidbar, aber durch Röntgenprüfung nachzuweisen. Die künftigen Aussichten des Titangusses werden positiv beurteilt.
    Additional Material: 14 Ill.
    Type of Medium: Electronic Resource
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