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  • PROPULSION SYSTEMS  (359)
  • Inorganic Chemistry  (316)
  • 1970-1974  (595)
  • 1940-1944  (80)
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Year
  • 1
    Publication Date: 2019-06-27
    Description: The fabrication procedures are described for a filament-wound rocket motor case, approximately 56 cm long x 71 cm diameter, utilizing high tensile strength graphite fibers. The process utilized Fiberite Hy-E-1330B prepreg tape which consists of Courtaulds HTS fibers in a temperature-sensitive epoxy matrix. This fabrication effort, with resultant design, material and process recommendations, substantiates the manufacturing feasibility of graphite/epoxy rocket motor cases in the 56 cm x 71 cm size range.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-128417 , BC-8845-FAB
    Format: application/pdf
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  • 2
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 245 (1940), S. 1-7 
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
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  • 3
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Reactions of (CH3)3Si—NSN—Si(CH3)3 for Preparation of New Sulfur-Nitrogen CompoundsR3Si—NSN—SiR3 (1) [R = CH3] and chlorine react under formation of R3Si—NSN—Cl (3). From 1 and trifluoromethyl acetylchloride CF3CO(S3N3) is obtained, and 1 with sulfur dichloride yields S(NSN—SiR3)2 (5). This compound reacts with SCl2under formation of S4N4. A new method for the preparation of S( = NSiR3)3 (6) is given. Investigation of the chemical bonds of 5 by ESCA measurements was tried.
    Notes: Die Reaktion des R3Si—NSN—SiR3 (1) [R = CH3] mit Chlor führt zum R3Si—NSN—Cl (3). Mit Trifluoracetylchlorid erhält man aus 1 CF3CO(S3N3) und mit Schwefeldichlorid S(NSNSiR3)2 (5), welches sich mit weiterem Schwefeldichlorid unter Ringschluß zu S4N4 umsetzt. Eine günstige Darstellungsmethode für S(=NSiR3)3 (6) wird mitgeteilt. Durch ESCA-Spektren werden die Bindungsverhältnisse in 5 zu ermitteln versucht.
    Additional Material: 1 Tab.
    Type of Medium: Electronic Resource
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  • 4
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    In:  CASI
    Publication Date: 2005-11-30
    Description: The selection and design of velocity diagrams for axial flow turbines are considered. Application is treated in two parts which includes: (1) mean-section diagrams, and (2) radial variation of diagrams. In the first part, the velocity diagrams occurring at the mean section are assumed to represent the average conditions encountered by the turbine. The different types of diagrams, their relation to stage efficiency, and their selection when staging is required are discussed. In the second part, it is shown that in certain cases the mean-section diagrams may or may not represent the average flow conditions for the entire blade span. In the case of relatively low hub- to tip-radius ratios, substantial variations in the velocity diagrams are encountered. The radial variations in flow conditions and their effect on the velocity diagrams are considered.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 69-99
    Format: text
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  • 5
    Publication Date: 2006-04-20
    Description: Propulsion technology for STOL and V/STOL commercial aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 135-168
    Format: text
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  • 6
    Publication Date: 2006-03-27
    Description: The characteristics of aircraft engine noise are discussed. Data are provided to show the noise produced by the following aircraft components: (1) fan noise, (2) noise suppressing structures, (3) sonic inlets, (4) jet mixing noise due to nozzle flow, and (5) thrust reversers. Charts are developed to show the sound pressure level and the frequencies for each type of noise source. The use of laminates and composite materials to dissipate acoustic power is examined.
    Keywords: PROPULSION SYSTEMS
    Type: STOL Technol.; p 371-412
    Format: text
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  • 7
    Publication Date: 2013-08-31
    Description: Stage integration requirements for space shuttle main engine
    Keywords: PROPULSION SYSTEMS
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 4 JUL. 1970; P 122-143
    Format: application/pdf
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  • 8
    Publication Date: 2011-08-16
    Description: Review of some chemical propulsion technology advances suitable for future unmanned spacecraft applications. Discussed system varieties include liquid space-storable propulsion systems, advanced liquid monopropellant systems, liquid systems for rendezvous and landing applications, and low-thrust high-performance solid-propellant systems, as well as hybrid space-storable systems. To optimize the performance and operational characteristics of an unmanned interplanetary spacecraft for a particular mission, and to achieve high cost effectiveness of the entire system, it is shown to be essential that the type of spacecraft propulsion system to be used matches, as closely as possible the various requirements and constraints. The systems discussed are deemed to be the most promising candidates for some of the anticipated interplanetary missions.
    Keywords: PROPULSION SYSTEMS
    Type: Journal of Spacecraft and Rockets; 9; Oct. 197
    Format: text
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  • 9
    Publication Date: 2019-06-27
    Description: A review of typical surveillance and monitoring practices followed during the flight phases of representative solid-propellant upper stages and apogee motors was conducted to evaluate the need for improved flight diagnostic instrumentation on future spacecraft. The capabilities of the flight instrumentation package were limited to the detection of whether or not the solid motor was the cause of failure and to the identification of probable primary failure modes. Conceptual designs of self-contained flight instrumentation packages capable of meeting these reqirements were generated and their performance, typical cost, and unit characteristics determined. Comparisons of a continuous real time and a thresholded hybrid design were made on the basis of performance, mass, power, cost, and expected life. The results of this analysis substantiated the feasibility of a self-contained independent flight instrumentation module as well as the existence of performance margins by which to exploit growth option applications.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-136561 , JPL-TM-33-656
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-27
    Description: Results from the postflight analysis of the ascent propulsion system (APS) performance during the Apollo 15 mission are presented. The duty cycle for the LM-10 APS consisted of two firings, and ascent stage liftoff from the lunar surface and the terminal phase ignition (TPI) burn. An evaluation was made of APS performance for the first firing and found to be satisfactory. No propulsion data was received from the second APS burn; however, all indications were that the burn was nominal. All performance parameters were well within their LM-10 3-sigma limits. Calculated throat erosion at engine cutoff for the LM-10 APS was approximately 3 percent greater than predicted.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-68932 , TRW-20029-H062-R0-00 , MSC-05161-SUPPL-3
    Format: application/pdf
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