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  • 1
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    Spectroscopy of a Synthetic Trapped Ion Qubit (2017)
    American Physical Society (APS)
    Details
    Publication Date: 2017-09-07
    Description: Author(s): David Hucul, Justin E. Christensen, Eric R. Hudson, and Wesley C. Campbell The trapping and cooling of the radioactive isotope barium-133 offers up an attractive system for encoding quantum information. [Phys. Rev. Lett. 119, 100501] Published Wed Sep 06, 2017
    Keywords: General Physics: Statistical and Quantum Mechanics, Quantum Information, etc.
    Print ISSN: 0031-9007
    Electronic ISSN: 1079-7114
    Topics: Physics
    Published by American Physical Society (APS)
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    PAPER CURRENT
  • 2
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    The effect of nonsymmetric pressure stiffness on the dynamic characteristics of Solid Rocket Motors (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper discusses the effect of pressure on the dynamics of pre-stiffened structures such as the Advanced Solid Rocket Motor (ASRM). Previous work in which the stiffness terms resulting from constant pressure were derived has been extended to enable modeling of nonconstant pressure applied over nonenclosed volumes. These conditions will result in nonsymmetric terms in the global stiffness matrix which will not cancel out. Three new pressure stiffness elements incorporating these nonsymmetric terms have been implemented as dummy elements in COSMIC NASTRAN and have been tested on various simple examples as well as an existing ASRM NASTRAN finite element model. The results indicate that for all load cases of practical interest to the ASRM program, the nonsymmetric terms have very little effect on the dynamic characteristics. In addition, the pressure stiffness elements developed in the previous work which assumed constant pressure gave virtually the same results as the new elements even for problems in which the pressures are not constant. The original elements appear to work well as long as the pressure gradient across any individual element is no larger than about 0.75 psi/inch. The new elements are therefore most useful for determining the conditions under which the original pressure stiffness elements can be used.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-1600 , In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 5 (A93-33876 1; p. 2577-2586.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Engine System Loads Analysis Compared to Hot-Fire Data (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Early implementation of structural dynamics finite element analyses for calculation of design loads is considered common design practice for high volume manufacturing industries such as automotive and aeronautical industries. However with the rarity of rocket engine development programs starts, these tools are relatively new to the design of rocket engines. In the NASA MC-1 engine program, the focus was to reduce the cost-to-weight ratio. The techniques for structural dynamics analysis practices, were tailored in this program to meet both production and structural design goals. Perturbation of rocket engine design parameters resulted in a number of MC-1 load cycles necessary to characterize the impact due to mass and stiffness changes. Evolution of loads and load extraction methodologies, parametric considerations and a discussion of load path sensitivities are important during the design and integration of a new engine system. During the final stages of development, it is important to verify the results of an engine system model to determine the validity of the results. During the final stages of the MC-1 program, hot-fire test results were obtained and compared to the structural design loads calculated by the engine system model. These comparisons are presented in this paper.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2002-1510 , 43rd AIAA Structures, Structural Dynamics and Materials Conference; Apr 22, 2002 - Apr 25, 2002; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Engine System Loads Development for the Fastrac 60K Flight Engine (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Early implementation of structural dynamics finite element analyses for calculation of design loads is considered common design practice for high volume manufacturing industries such as automotive and aeronautical industries. However, with the rarity of rocket engine development programs starts, these tools are relatively new to the design of rocket engines. In the new Fastrac engine program, the focus has been to reduce the cost to weight ratio; current structural dynamics analysis practices were tailored in order to meet both production and structural design goals. Perturbation of rocket engine design parameters resulted in a number of Fastrac load cycles necessary to characterize the impact due to mass and stiffness changes. Evolution of loads and load extraction methodologies, parametric considerations and a discussion of load path sensitivities are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA Paper 00-XXXX , 41st Structures, Structural Dynamic and Materials Conference; Apr 04, 2000 - Apr 06, 2000; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Calculation of Dynamic Loads Due to Random Vibration Environments in Rocket Engine Systems (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An important part of rocket engine design is the calculation of random dynamic loads resulting from internal engine "self-induced" sources. These loads are random in nature and can greatly influence the weight of many engine components. Several methodologies for calculating random loads are discussed and then compared to test results using a dynamic testbed consisting of a 60K thrust engine. The engine was tested in a free-free condition with known random force inputs from shakers attached to three locations near the main noise sources on the engine. Accelerations and strains were measured at several critical locations on the engines and then compared to the analytical results using two different random response methodologies.
    Keywords: Mechanical Engineering
    Type: American Institute of Aeronautics and Astronautics, Structures, Structural Dynamics, and Materials Conference; Apr 23, 2007 - Apr 27, 2007; Honolulu, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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