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  • SPACECRAFT PROPULSION AND POWER  (405)
  • 1985-1989  (405)
  • 1965-1969
  • 1930-1934
  • 1989  (405)
  • 1
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    The liquid rocket booster and its potential for the STS (1989)
    In:  CASI
    Details
    Publication Date: 2006-06-11
    Description: Results of the liquid rocket booster study initiated by NASA to define an alternative to solid rocket boosters, are presented. The prime study contractors, Martin Marietta Corporation and General Dynamics, have identified liquid rocket booster configurations that can increase shuttle performance to 70 klb. These boosters will provide improved reliability, hold down, verification prior to vehicle release, engine-out and abort capabilities. Phasing of these boosters into Space Transportation System (STS) operations without adversely affecting flight rate is described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, Progress in Space Transportation; p 405-41
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Space shuttle solid rocket booster redesign and testing (1989)
    In:  CASI
    Details
    Publication Date: 2006-06-11
    Description: The redesigned solid rocket motor of the Space Shuttle is described. Improvements over the model that led to the loss of the Space Shuttle Challenger are outlined. Scale and full-size tests carried out to verify the quality of the redesign are described. A unique feature of the test program is the introduction of deliberate flaws into some test articles. Post-flight evaluation of the redesigned boosters show excellent results.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, Progress in Space Transportation; p 173-18
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Superfluid Helium On-Orbit Transfer (SHOOT) operations (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The in-flight tests and the operational sequences of the Superfluid Helium On-Orbit Transfer (SHOOT) experiment are outlined. These tests include the transfer of superfluid helium at a variety of rates, the transfer into cold and warm receivers, the operation of an extravehicular activity coupling, and tests of a liquid acquisition device. A variety of different types of instrumentation will be required for these tests. These include pressure sensors and liquid flow meters that must operate in liquid helium, accurate thermometry, two types of quantity gauges, and liquid-vapor sensors.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Cryogenics (ISSN 0011-2275); 29; 493-497
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Electromagnetic emission experiences using electric propulsion systems (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 534-547
    Format: text
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  • 5
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    Probabilistic structural analysis methods for improving Space Shuttle engine reliability (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Probabilistic structural analysis methods are particularly useful in the design and analysis of critical structural components and systems that operate in very severe and uncertain environments. These methods have recently found application in space propulsion systems to improve the structural reliability of Space Shuttle Main Engine (SSME) components. A computer program, NESSUS, based on a deterministic finite-element program and a method of probabilistic analysis (fast probability integration) provides probabilistic structural analysis for selected SSME components. While computationally efficient, it considers both correlated and nonnormal random variables as well as an implicit functional relationship between independent and dependent variables. The program is used to determine the response of a nickel-based superalloy SSME turbopump blade. Results include blade tip displacement statistics due to the variability in blade thickness, modulus of elasticity, Poisson's ratio or density. Modulus of elasticity significantly contributed to blade tip variability while Poisson's ratio did not. Thus, a rational method for choosing parameters to be modeled as random is provided.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 426-430
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  • 6
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    Performance characterizations of an engineering model multipropellant resistojet (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 197-203
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  • 7
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    Computer-controlled xenon ion engine operation (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 42-48
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  • 8
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    Assessment of impingement effects in the isentropic core of a small satellite control thruster plume (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Two computational techniques commonly employed in the calculation of rocket and thruster expansion plumes are assessed. These are the method of characteristics (MOC), which is derived from the continuum Euler equations, and the direct simulation Monte Carlo (DSMC) method, which adopts a discrete particle approach. These techniques vary both in the computational expense and in the accuracy and detail of the solutions that they provide, depending upon the regime of application. The assessment is made with reference to the plume expanding from a small monopropellant hydrazine thruster and concentrates on the isentropic core of the jet for the flow regime lying between the continuum and free molecular limits. It is found that the more numerically intensive DSMC method offers the better correspondence to the available experimental data. In addition, large differences in typical impingement effects such as drag force and heat transfer are found at the free molecular limit of the plume expansion for the two predictive techniques. It is concluded that accurate estimation of impingement potential may only be achieved through application of the discrete particle method.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Institution of Mechanical Engineers, Proceedings, Part G - Journal of Aerospace Engineering (ISSN 0954-4100); 203; G2, 1
    Format: text
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  • 9
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    Electric propulsion for constellation deployment and spacecraft maneuvering (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 26; 352-357
    Format: text
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  • 10
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    Rocket plume spectrometry: A system permitting engine condition monitoring, as applied to the technology test bed engine (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The appearance of visible objects in the exhaust plume of space shuttle main engines (SSME) during test firings is discussed. A program was undertaken to attempt to identify anomalous material resulting from wear, normal or excessive, of internal parts, allowing time monitoring of engine condition or detection of failure precursors. Measurements were taken during test firings at Stennis Space Center and at the Santa Suzanna facility in California. The results indicated that a system having high spectral resolution, a fast time response, and a wide spectral range was required to meet all requirements, thus two special systems have been designed and built. One is the Optical Plume Anomaly Detector (OPAD). The other instrument, which is described in this report, is the superspectrometer, an optical multichannel analyzer having 8,192 channels covering the spectral band 250 to 1,000 nm.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Structural Integrity and Durability of Reusable Space Propulsion Systems; p 127-135
    Format: application/pdf
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