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  • Other Sources  (516)
  • SPACECRAFT PROPULSION AND POWER  (516)
  • 1990-1994  (516)
  • 1994  (121)
  • 1992  (395)
  • 11
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    Optical measurements in rocket engine liquid sprays (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The performance of liquid propellant rocket engines is dependent upon many elements of the entire system. One of the most fundamental and most critical is the performance of the injector elements. Their characterization is an important part of the development of combustion devices. Optical measurements within these environments have proven to be invaluable tools in quantifying the physical environment of two phase flows. The effort reported herein involves the measurement of drop velocity, drop size, and most importantly mass flux using Phase-Doppler Particle Anemometry within a spray generated by a single swirl injector element operating in atmospheric pressure conditions. The mass flux has been determined and validated by mechanical patternation methods and by profile integration of the mass flux.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., Research Reports: 1994 NASA(ASEE Summer Faculty Fellowship Program; 6 p
    Format: application/pdf
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  • 12
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    Evaluation of SSME test data reduction methods (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Accurate prediction of hardware and flow characteristics within the Space Shuttle Main Engine (SSME) during transient and main-stage operation requires a significant integration of ground test data, flight experience, and computational models. The process of integrating SSME test measurements with physical model predictions is commonly referred to as data reduction. Uncertainties within both test measurements and simplified models of the SSME flow environment compound the data integration problem. The first objective of this effort was to establish an acceptability criterion for data reduction solutions. The second objective of this effort was to investigate the data reduction potential of the ROCETS (Rocket Engine Transient Simulation) simulation platform. A simplified ROCETS model of the SSME was obtained from the MSFC Performance Analysis Branch . This model was examined and tested for physical consistency. Two modules were constructed and added to the ROCETS library to independently check the mass and energy balances of selected engine subsystems including the low pressure fuel turbopump, the high pressure fuel turbopump, the low pressure oxidizer turbopump, the high pressure oxidizer turbopump, the fuel preburner, the oxidizer preburner, the main combustion chamber coolant circuit, and the nozzle coolant circuit. A sensitivity study was then conducted to determine the individual influences of forty-two hardware characteristics on fourteen high pressure region prediction variables as returned by the SSME ROCETS model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., Research Reports: 1994 NASA(ASEE Summer Faculty Fellowship Program; 6 p
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  • 13
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    Steady and unsteady blade stresses within the SSME ATD/HPOTP inducer (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: There were two main goals of the ATD HPOTP (alternate turbopump development)(high pressure oxygen turbopump). First, determine the steady and unsteady inducer blade surface strains produced by hydrodynamic sources as a function of flow capacity (Q/N), suction specific speed (Nss), and Reynolds number (Re). Second, to identify the hydrodynamic source(s) of the unsteady blade strains. The reason the aforementioned goals are expressed in terms of blade strains as opposed to blade hydrodynamic pressures is because of the interest regarding the high cycle life of the inducer blades. This report focuses on the first goal of the test program which involves the determination of the steady and unsteady strain (stress) values at various points within the inducer blades. Strain gages were selected as the strain measuring devices. Concurrent with the experimental program, an analytical study was undertaken to produce a complete NASTRAN finite-element model of the inducer. Computational fluid dynamics analyses were utilized to provide the estimated steady-state blade surface pressure loading needed as load input to the NASTRAN inducer model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., Research Reports: 1994 NASA(ASEE Summer Faculty Fellowship Program; 6 p
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  • 14
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    Data driven propulsion system weight prediction model (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of the research was to develop a method to predict the weight of paper engines, i.e., engines that are in the early stages of development. The impetus for the project was the Single Stage To Orbit (SSTO) project, where engineers need to evaluate alternative engine designs. Since the SSTO is a performance driven project the performance models for alternative designs were well understood. The next tradeoff is weight. Since it is known that engine weight varies with thrust levels, a model is required that would allow discrimination between engines that produce the same thrust. Above all, the model had to be rooted in data with assumptions that could be justified based on the data. The general approach was to collect data on as many existing engines as possible and build a statistical model of the engines weight as a function of various component performance parameters. This was considered a reasonable level to begin the project because the data would be readily available, and it would be at the level of most paper engines, prior to detailed component design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., Research Reports: 1994 NASA(ASEE Summer Faculty Fellowship Program; 6 p
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  • 15
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    Development of CFD model for augmented core tripropellant rocket engine (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Space Shuttle era has made major advances in technology and vehicle design to the point that the concept of a single-stage-to-orbit (SSTO) vehicle appears more feasible. NASA presently is conducting studies into the feasibility of certain advanced concept rocket engines that could be utilized in a SSTO vehicle. One such concept is a tripropellant system which burns kerosene and hydrogen initially and at altitude switches to hydrogen. This system will attain a larger mass fraction because LOX-kerosene engines have a greater average propellant density and greater thrust-to-weight ratio. This report describes the investigation to model the tripropellant augmented core engine. The physical aspects of the engine, the CFD code employed, and results of the numerical model for a single modular thruster are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., Research Reports: 1994 NASA(ASEE Summer Faculty Fellowship Program; 6 p
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  • 16
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    A preliminary analysis of low frequency pressure oscillations in hybrid rocket motors (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Past research with hybrid rockets has suggested that certain motor operating conditions are conducive to the formation of pressure oscillations, or flow instabilities, within the motor combustion chamber. These combustion-related vibrations or pressure oscillations may be encountered in virtually any type of rocket motor and typically fall into three frequency ranges: low frequency oscillations (0-300 Hz); intermediate frequency oscillations (400-1000 Hz); and high frequency oscillations (greater than 1000 Hz). In general, combustion instability is characterized by organized pressure oscillations occurring at well-defined intervals with pressure peaks that may maintain themselves, grow, or die out. Usually, such peaks exceed +/- 5% of the mean chamber pressure. For hybrid motors, these oscillations have been observed to grow to a limiting amplitude which may be dependent on factors such as fuel characteristics, oxidizer injector characteristics, average chamber pressure, oxidizer mass flux, combustion chamber length, and grain geometry. The approach taken in the present analysis is to develop a modified chamber length, L, instability theory which accounts for the relationship between pressure and oxidizer to fuel concentration ratio in the motor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ., Research Reports: 1994 NASA(ASEE Summer Faculty Fellowship Program; 6 p
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  • 17
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    Coupling gravity, electromagnetism and space-time for space propulsion breakthroughs (1994)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: spaceflight would be revolutionized if it were possible to propel a spacecraft without rockets using the coupling between gravity, electromagnetism, and space-time (hence called 'space coupling propulsion'). New theories and observations about the properties of space are emerging which offer new approaches to consider this breakthrough possibility. To guide the search, evaluation, and application of these emerging possibilities, a variety of hypothetical space coupling propulsion mechanisms are presented to highlight the issues that would have to be satisfied to enable such breakthroughs. A brief introduction of the emerging opportunities is also presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Pennsylvania State Univ., NASA Propulsion Engineering Research Center, Volume 2; p 93-97
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  • 18
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    Interface issues for on-board propulsion systems (1994)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Integration issues associated with the use of new chemical and electric propulsion technologies are a primary concern to the user community. Experience indicates that integration impacts must be addressed to the satisfaction of both spacecraft builders and operators prior to the acceptance of new propulsion systems. The NASA Lewis Research Center (LeRC) conducts an aggressive program to develop and transfer new propulsion technologies and this includes a major effort to identify and address integration issues associated with their use. This paper provides an overview of integration issues followed by a brief description of the spacecraft integration program at LeRC.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Pennsylvania State Univ., NASA Propulsion Engineering Research Center, Volume 2; p 88-92
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  • 19
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    Performance testing of a fixed configuration microwave arcjet thruster (1994)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The microwave arcjet thruster uses microwave energy to create a free-floating plasma discharge within a microwave resonant cavity. This discharge typically absorbs 99% of the input power and converts it to thermal energy which is then transferred to the flowing propellant gas. Recent modifications have allowed the thruster to be operated in a fixed configuration where neither the cavity geometry nor the tuning mechanisms are adjusted. The prototype has demonstrated its ability to operate in this fixed configuration using a variety of propellant gases, i.e., nitrogen, helium, ammonia, and hydrogen. The current design is capable of efficient operation over a wide range of power levels (250 W to over 6000 W). Current work is focused on obtaining LIF velocimetry data of the velocity profile at the exit plane of the nozzle.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA Propulsion Engineering Research Center, Volume 2; p 75-79
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  • 20
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    Orbital maneuvering and reaction control systems (1994)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Orbital maneuvering systems (OMS) and reaction control systems (RCS) provide capabilities to spacecraft that include orbit circularization, rendezvous maneuvers, attitude control, and re-entry delta velocity. The mission and vehicle requirements can place severe demands on the orbital maneuvering and reaction control systems. In order to perform proper trade studies and to design these systems, the mission and vehicle configuration must be well defined. In the absence of a clearly defined mission and vehicle configuration, the research and development of basic technologies must support future design efforts by providing a range of options and data from which to select. This paper describes the key OMS and RCS requirements and technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Pennsylvania State Univ., NASA Propulsion Engineering Research Center, Volume 2; p 80-84
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