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  • 1
    Electronic Resource
    Electronic Resource
    Springer
    European journal of clinical pharmacology 50 (1996), S. 275-277 
    ISSN: 1432-1041
    Keywords: Key words Budesonide ; Fluticasone; inhaled corticosteroids ; collagen metabolism ; bone metabolism
    Source: Springer Online Journal Archives 1860-2000
    Topics: Chemistry and Pharmacology , Medicine
    Notes: Abstract Objectives: Novel assays have been developed for markers of type 1 collagen turnover. The aim of this study was to evaluate the effect of short-term exposure to inhaled corticosteroids on both the novel and conventional markers of bone metabolism. Methods: Nine healthy subjects received 2 weeks treatment with inhaled budesonide 800 μg per day in week 1, and 1600 μg per day in week 2, or fluticasone 750 μg per day in week 1 and 1500 μg per day in week 2, with a 1-week washout in between. Measurement of carboxy-terminal propeptide of type 1 collagen (PICP), carboxy-terminal telopeptide of type 1 collagen (ICTP), plasma alkaline phosphatase bone isoenzyme, and 24-h urinary calcium excretion were made at baseline and at the end of each 2-week treatment period. Results: ICTP was significantly reduced following treatment with budesonide but not fluticasone compared with baseline: baseline 4.2 μg⋅1−1 budesonide 3.0 μg⋅1−1, fluticasone 3.6 μg⋅1−1. There were no significant changes in PICP compared with baseline after treatment with budesonide or fluticasone. The ratio of PICP:ICTP increased significantly after treatment with both budesonide and fluticasone compared with baseline: baseline 27.4, budesonide 43.7, t 42.6. There were no significant differences between the two treatments for any of the measured parameters. Conclusions: Thus, when using sensitive markers of collagen turnover, short-term inhaled corticosteroid therapy was found paradoxically to reduced bone resorption.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2011-08-24
    Description: A development status evaluation is presented for the aerodynamics of missile configurations with noncircular cross-sections and bank-to-turn maneuvering systems, giving attention to cases with elliptical and square cross-sections, as well as bodies with variable cross-sections. The assessment of bank-to-turn missile performance notes inherent stability/control problems. A summary and index are provided for aerodynamic data on monoplanar configurations, including those which incorporate airbreathing propulsion systems.
    Keywords: AERODYNAMICS
    Format: text
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  • 3
    Publication Date: 2011-08-19
    Description: An evaluation is made of prospective missile applications for noncircular cross section bodies, and of recent developments in bank-to-turn missile configuration aerodynamics. The discussion encompasses cross-flow analysis techniques, as well as study results obtained for bodies with elliptical and square cross sections and with variable cross sections. Attention is given to both the performance advantages and the stability and control problems of bank-to-turn missile configurations; the aerodynamic data presented for monoplanar configurations extend to those incorporating airbreathing propulsion systems.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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  • 4
    Publication Date: 2019-06-27
    Description: A preliminary experimental investigation has been made to evaluate the powered ground-effect capability of a low-aspect-ratio, wing-body configuration with forward-mounted propulsion. The tests were limited to static ground-effect conditions in order to obtain information on an air-cushion mode of operation. The results indicate, in general, that an air-cushion mode is within the capability of the type of configuration examined. The conditions examined indicated the possibility of hover mode and also forward acceleration capability in near-ground effect. Center-of-pressure movement did not appear to be a problem. However, it was recognized that longitudinal trim would be a problem to consider in both the hover and acceleration modes.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3031 , L-9368
    Format: application/pdf
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  • 5
    Publication Date: 2019-06-27
    Description: Theoretical method for calculating aerodynamic loading on wing-body combinations
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6441 , L-7822
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  • 6
    Publication Date: 2019-06-27
    Description: Mathematical model for determining total drag of pointed body of revolution in supersonic flow with turbulent boundary layer
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-5046
    Format: application/pdf
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  • 7
    Publication Date: 2019-07-13
    Description: An experimental investigation has been made at supersonic Mach numbers to determine the feasibility of using a ram-air-spoiler roll control device on a typical canard control missile configuration. As a basis for roll control comparisons, conventional aileron controls on the tail fins were also tested. Results are presented which indicate that the addition of nacelles on the missile tail fins resulted in satisfactory roll control effectiveness and only small changes in basic missile stability. The ram-air-spoiler roll control effectiveness is relatively constant over the range of vehicle attitudes and Mach numbers investigated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 78-24 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
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  • 8
    Publication Date: 2019-06-27
    Description: Computational method for surface pressures on blunt bodies of revolution at small angles of attack in supersonic flow
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-4865
    Format: application/pdf
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  • 9
    Publication Date: 2019-06-28
    Description: The two test sections of the Langley Unitary Plan Wind Tunnel were calibrated over the operating Mach number range from 1.47 to 4.63. The results of the calibration are presented along with a a description of the facility and its operational capability. The calibrations include Mach number and flow angularity distributions in both test sections at selected Mach numbers and tunnel stagnation pressures. Calibration data are also presented on turbulence, test-section boundary layer characteristics, moisture effects, blockage, and stagnation-temperature distributions. The facility is described in detail including dimensions and capacities where appropriate, and example of special test capabilities are presented. The operating parameters are fully defined and the power consumption characteristics are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1905 , L-14024
    Format: application/pdf
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  • 10
    Publication Date: 2019-07-13
    Description: This paper presents an overview of the role NASA has had and continues to pursue in providing missile aerodynamic technology. In the past, NASA has provided considerable support to the missile industry and the military. The support has generally taken the form of theoretical aerodynamic analyses, experimental studies to provide solutions for specific problems, and the documentation of existing foreign missile systems and domestic missiles. In 1975, NASA shifted its missile-related efforts in aerodynamics from this largely service role to one of conducting more basic research. The areas of research include: innovative methods for roll control of cruciform missiles, airbreathing missiles with maneuver requirements, and an advanced generation of monoplanar missiles for efficient supersonic carriage and delivery.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0247 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
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