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  • 1
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    Examination of the effect of propulsion system performance variables on the life prediction for the SSME Lox Post (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The main objective is to calculate damage evolution at the critical location of selected components of reusable space propulsion systems as the function of their operating environments and to relate the evolution of damage at the critical locations to the performance variables of the propulsion system using advanced constitutive and damage models. The models so developed will be oriented toward use in an advanced diagnostic/prognostic health monitoring system for reusable propulsion systems. The components to be modelled include a Lox Post (injector element), a thrust chamber, and a turbine blade. The study conducted on the Lox Post is reported.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Structural Integrity and Durability of Reusable Space Propulsion Systems; p 219-227
    Format: application/pdf
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  • 2
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    New electronic states of NH and ND observed by resonance enhanced multiphoton ionization spectroscopy (1990)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Resonance Enhanced MultiPhoton Ionization (REMPI) spectra of NH and ND, which reveal four new electronic states are presented. Transitions from NH a 1 delta to 3s and 3p Rydberg states in both NH and ND have been observed and rotationally analyzed. The transitions were observed in the wavelength range of 258 to 288 nm. The state assignments are: e 1 pi (3s sigma) at 82857/cm, f 1 pi (3p sigma) at 86378/cm, g 1 delta (3p pi) at 88141/cm and h 1 sigma (3p pi) at 89151/cm.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: NASA, Goddard Space Flight Center, First International Conference on Laboratory Research for Planetary Atmospheres; p 164-167
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  • 3
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    Constitutive and damage material modeling in a high pressure hydrogen environment (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerous components in reusable space propulsion systems such as the SSME are exposed to high pressure gaseous hydrogen environments. Flow areas and passages in the fuel turbopump, fuel and oxidizer preburners, main combustion chamber, and injector assembly contain high pressure hydrogen either high in purity or as hydrogen rich steam. Accurate constitutive and damage material models applicable to high pressure hydrogen environments are therefore needed for engine design and analysis. Existing constitutive and cyclic crack initiation models were evaluated only for conditions of oxidizing environments. The main objective is to evaluate these models for applicability to high pressure hydrogen environments.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Structural Integrity and Durability of Reusable Space Propulsion Systems; p 187-196
    Format: application/pdf
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  • 4
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    Significant issues in proof testing: A critical appraisal (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Issues which impact on the interpretation and quantification of proof test benefits are reviewed. The importance of each issue in contributing to the extra quality assurance conferred by proof testing components is discussed, particularly with respect to the application of advanced fracture mechanics concepts to enhance the flaw screening capability of a proof test analysis. Items covered include the role in proof testing of elastic-plastic fracture mechanics, ductile instability analysis, deterministic versus probabilistic analysis, single versus multiple cycle proof testing, and non-destructive examination (NDE). The effects of proof testing on subsequent service life are reviewed, particularly with regard to stress redistribution and changes in fracture behavior resulting from the overload. The importance of proof test conditions are also addressed, covering aspects related to test temperature, simulation of service environments, test media and the application of real-time NDE. The role of each issue in a proof test methodology is assessed with respect to its ability to: promote proof test practice to a state-of-the-art; aid optimization of proof test design; and increase awareness and understanding of outstanding issues.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-4628 , M-757 , NAS 1.26:4628
    Format: application/pdf
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  • 5
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    Reliability of a Shuttle reaction timer (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Reaction, movement, and task times refer to the times needed to initially respond to a stimulus, make the specific movement, and complete the entire task. This study evaluated the reliability of a simple reaction timer designed to mimic a Space Shuttle task (turning on an overhead switch).
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA-TP-3176 , S-659 , NAS 1.60:3176
    Format: application/pdf
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  • 6
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    Preliminary investigation of a low power pulsed arcjet thruster (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A type of pulsed arcjet is examined which operates with gaseous helium propellant at powers from 100 to 1500 W and pulse rats from 360 to 6000 pulses per second. During the pulse, peak power is 50 to 250 kW generating chamber pressures of 10 to 50 atmospheres. The high operating pressure substantially reduces ionization in the 2.5 mm diameter x 12.5 mm long capillary and lowers frozen flow losses in the nozzle. The thruster thermal efficiency, measured calorimetrically, is 43 percent at 440 W and 8 mg/sec helium mass flow rate. Thruster performance trends are predicted by a time-dependent lumped-parameter model which includes heat exchange between the propellant and the wall. The model substantially underpredicts the experimental thermal efficiency values. Alternative thruster configurations yielding significant improvements in thrust efficiency and specific impulse are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3113
    Format: text
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  • 7
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    A numerical study of longitudinal vortex interaction with a boundary layer (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical study of vortex generator aerodynamics has been carried out with a reduced set of Navier-Stokes equations. These are used to model the physical process of longitudinal vortex interaction with a turbulent boundary layer on a flat plate in incompressible flow. Comparison with experimental data is used to validate the approach, and detailed predictions are made. Results show an increase in skin friction and a decrease in integral layer thicknesses where the flow is toward the wall, and the reverse where the flow is away from the wall. The major controlling parameters of vortex strength, spacing and height are each found to have optimum values for which the efficiency of boundary-layer thinning is maximized. Vortex core spreading and secondary vorticity produced in the layer are observed and studied, as well as circulation decay and other features of the flow.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-1630
    Format: text
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  • 8
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    Manipulator design and development for the Ranger satellite servicing vehicle (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Ranger program is a planned series of low cost telerobotics flight experiments, based on the use of Pegasus launch vehicles. As the first step towards this goal, the Space Systems Lab was developing a neutral buoyancy version of Ranger for use in design verification and operations testing. The design approach and results of the Ranger manipulator development program is related. Ranger is designed to incorporate four appendages: a pair of dexterous, seven degree of freedom manipulators for general manipulation; a six DOF grappling arm for securing the vehicle to the local work site; and a five DOF positioning manipulator for the stereo camera pair that provide feedback to the remote operator. Each of these manipulators incorporate unique approaches to satisfying design requirements. The numerical and operational requirements are given for Ranger manipulators, and the evolution is discussed of the differing design approaches based on similarities and differences in the requirements. Testing results for individual joints and manipulator assemblies are presented, followed by initial results of operational testing on satellite servicing tasks with the integrated Ranger neutral buoyancy vehicle.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center, The 26th Aerospace Mechanisms Symposium; p 61-74
    Format: text
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  • 9
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    Laser Com Pointing Acquisition and Tracking Control Using a CCD-Based Tracker (1994)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: A CCD-based spatial acquisition and tracking subsystem has been developed to perform both spatial acquisition and tracking functions for a lasercom instrument. By operating the CCD in the.
    Keywords: Electronics and Electrical Engineering
    Format: text
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  • 10
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    Single-Cycle Versus Multicycle Proof Testing (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Report compares single-cycle with multiple-cycle mechanical-stress tests of parts under mechanical stresses. Objective of proof testing: to screen out gross manufacturing or material deficiencies and provide additional assurance of quality. Report concludes that changes in distribution of crack sizes during multicycle proof testing depend on initial distribution, number of cycles, relationship between resistance of material and elastic/plastic fracture-mechanics parameter, relationship between load control and displacement control, and magnitude of applied load or displacement. Whether single-cycle or multicycle testing used depends on shape, material, and technique of fabrication of components tested.
    Keywords: MECHANICS
    Type: MFS-27255 , NASA Tech Briefs (ISSN 0145-319X); 16; 12; P. 70
    Format: text
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