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  • Other Sources  (220)
  • AERODYNAMICS
  • Ertrag
  • Forst
  • Seismicity
  • Spacecraft Propulsion and Power
  • 2000-2004
  • 1995-1999  (220)
  • 1940-1944
  • 1995  (220)
  • 1
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    Hypersonic aerodynamics test facility using the external propulsion accelerator (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The use of the External propulsion Accelerator (EPA) for launching models of hypersonic aerodynamic configurations into an instrumented ballistic range is discussed. The aerodynamic model is encased inside an axisymmetric projectile designed to be accelerated to high speed in the EPA. Accelerator lengths required to achieve hypersonic speeds are estimated to vary from 10 meters for Mach 7, 40 meters for Mach 10, 150 meters for Mach 15, and 700 meters for Mach 30, assuming a limit of 50,000 g's acceleration. For a model span of 10 cm to 25 cm, the launch tube diameters are 40 cm and 100 cm, respectively. Using this EPA launcher will enable exact simulation of hypersonic flight in ground facilities where both the gas composition and pressure can be controlled in the ballistic range.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 95-6138 , AIAA, Aerospace Planes and Hypersonics Technologies Conference; Apr 03, 1995 - Apr 07, 1995; Chattanooga, TN; United States|; 5 p.
    Format: text
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  • 2
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    Scramjet thrust measurement in a shock tunnel (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: This note reports tests in a shock tunnel in which a fully integrated scamjet configuration produced net thrust. The experiments not only showed that impluse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/s, and shock tunnels offer a means of generating high Mach number flows at such speeds.
    Keywords: AERODYNAMICS
    Type: Aeronautical Journal (ISSN 0001-9240); 99; 984; p. 161-163
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  • 3
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    Planetary and Deep Space Requirements for Photovoltaic Solar Arrays (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: In the past 25 years, the majority of interplanetary spacecraft have been powered by nuclear sources. However, as the emphasis on smaller, low cost missions gains momentum, more deep space missions now being planned have baselined photovoltaic solar arrays due to the low power requirements (usually significantly less than 100 W) needed for engineering and science payloads. This will present challenges to the solar array builders, inasmuch as planetary requirements usually differ from earth orbital requirements. In addition, these requirements often differ greatly, depending on the specific mission; for example, inner planets vs. outer planets, orbiters vs. flybys, spacecraft vs. landers, and so on. Also, the likelihood of electric propulsion missions will influence the requirements placed on solar array developers. This paper will discuss representative requirements for a range of planetary and deep space science missions now in the planning stages. We have divided the requirements into three categories: Inner planets and the sun; outer planets (greater than 3 AU); and Mars, cometary, and asteroid landers and probes. Requirements for Mercury and Ganymede landers will be covered in the Inner and Outer Planets sections with their respective orbiters. We will also discuss special requirements associated with solar electric propulsion (SEP). New technology developments will be needed to meet the demanding environments presented by these future applications as many of the technologies envisioned have not yet been demonstrated. In addition, new technologies that will be needed reside not only in the photovoltaic solar array, but also in other spacecraft systems that are key to operating the spacecraft reliably with the photovoltaics.
    Keywords: Spacecraft Propulsion and Power
    Type: Space Photovoltaic Research and Technology 1995; 2-9; NASA-CP-10180
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  • 4
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    Metallographic Analysis of Brush Bristle and Integrity Testing of Brush Seal in Shroud Ring of T-700 Engine (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Post-test investigation of a T-700 engine brush seal found regions void of bristles ('yanked out'), regions of bent-over bristles near the inlet, some 'snapped' bristles near the fence, and a more uniform 'smeared' bristle interface between the first and last axial rows of bristles. Several bristles were cut from the brush seal, wax mounted, polished, and analyzed. Metallographic analysis of the bristles near the rub tip showed tungsten-rich phases uniformly distributed throughout the bristle with no apparent change within 1 to 2 micron of the interface except for possibly a small amount of titanium, which would represent a transfer from the rotor. Analysis of the bristle wear face showed nonuniform tungsten, which is indicative of material resolidification. The cut end contained oxides and internal fractures; the worn end was covered with oxide scale. Material losses due to wear and elastoplastic deformation within the shear zone and third-body lubrication effects in the contact zone are discussed.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-106361 , ARL-MR-119 , E-8155 , NAS 1.15:106361 , International Symposium on Transport Phenomena and Dynamics of Rotating Machinery; May 08, 1994 - May 11, 1994; Kaanapali, Maui, HI; United States
    Format: application/pdf
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  • 5
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    EPOP Diagnostics and Data Acquisition (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This paper describes the diagnostics that have been selected for the first flight of the Electric Propulsion Orbital Platform (EPOP-1), in which a 1.8 kW hydrazine arcjet will be flown and tested on the Wake Shield Facility. These diagnostics are: Langmuir probe measurements and video of the arcjet plume; three types of electromagnetic noise measurements; measurement of the voltage-current characteristic of the arc at different feed pressures; and measurement of other performance parameters such as pressures and temperatures of arcjet system components, thrust, and specific impulse. Also, the approach to data acquisition and control of the experiment is described.
    Keywords: Spacecraft Propulsion and Power
    Type: CSTAR Third Annual Technical Symposium; 74-82
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  • 6
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    Electric Propulsion: Experimental Research (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: This paper describes experimental electric propulsion research which was carried out at the University of Tennessee Space Institute with support from the Center for Space Transportation and Applied Research. Specifically, a multiplexed LIF technique for obtaining vector velocities, Doppler temperatures, and relative number densities in the exhaust plumes form electric propulsion devices is described, and results are presented that were obtained on a low power argon arcjet. Also, preliminary Langmuir probe measurements on an ion source are described, and an update on the vacuum facility is presented.
    Keywords: Spacecraft Propulsion and Power
    Type: CSTAR Third Annual Technical Symposium; 83-90
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  • 7
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    Magnetic Annual Arc (MAARC) (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Electromagnetic propulsion systems offer high specific impulses (greater than 1500) and high thrust-density as compared to conventional chemical rocket propulsion system. Understanding and simulating the physical processes in electromagnetic propulsion devices (as well as testing with refined diagnostic equipment) hold the key to improved performance and longevity of these devices. This in turn is an essential requirement for a practical application in future space endevors.
    Keywords: Spacecraft Propulsion and Power
    Type: Center for Advanced Space Propulsion; 98-99; NASA-CR-199689
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  • 8
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    Advanced high area ratio nozzles (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The objective is to develop computational techniques for the design of high-area-ratio nozzles and to validate these models by comparison with experiments and computations using other codes. Progress was made in two areas during the past year. First, performance computations were added to the PARC2D code and the performance of the SSME nozzle was computed for inviscid, laminar and turbulent flow assuming a perfect gas with gamma = 1.2. Second, the PARC2D code was modified in a non-CASP project to compute equilibrium flow about hypersonic blunt bodies. Progress has been made toward modifying this code to compute equilibrium H2/O2 flow through the SSME and related nozzles.
    Keywords: Spacecraft Propulsion and Power
    Type: Center for Advanced Space Propulsion; 33-35; NASA-CR-199689
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  • 9
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    Triggering of longitudinal combustion instabilities in solid rocket motors: Nonlinear combustion response (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-08-15
    Description: Pulsed oscillations in solid rocket motors are investigated with emphasis on nonlinear combustion response. The study employs a wave equation governing the unsteady motions in a two-phase flow, and a solution technique based on spatial- and time-averaging. A wide class of combustion response functions is studied to second-order in fluctuation amplitude to determine if, when, and how triggered instabilities arise. Conditions for triggering are derived from analysis of limit cycles, and regions of triggering are found in parametric space. Based on the behavior of model dynamical systems, introduction of linear cross-coupling and quadratic self-coupling among the acoustic modes appears to be the manner in which the nonlinear combustion response produces triggering to a stable limit cycle. Regions of initial conditions corresponding to stable pulses were found, suggesting that stability depends on initial phase angle and harmonic content, as well as the composite amplitude, of the pulse.
    Keywords: Spacecraft Propulsion and Power
    Type: 32nd JANNAF Combustion Subcommittee Meeting; 197-208; CPIA-631-VOL-1
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  • 10
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    SSME propellant path leak detection (1995)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The primary objective of this phase of the investigation is the experimental validation of techniques for detecting and analyzing propellant path external leaks which have a high probability of occurring on the SSME. The selection of candidate detection methods requires a good analytic model for leak plumes which would develop from external leaks and an understanding of radiation transfer through the leak plume. One advanced propellant path leak detection technique is obtained by using state-of-art technology of infrared (IR) thermal imaging systems combined with computer, digital image processing and expert systems for the engine protection. The feasibility of the IR leak plume detection will be evaluated on subscale simulated laboratory plumes to determine sensitivity, signal to noise, and general suitability for the application. The theoretical analysis was undertaken with the objective of developing and testing simple, easy-to-use models to predict the amount of radiation coming from a radiation source, background plate (BP), which can be absorbed, emitted and scattered by the gas leaks.
    Keywords: Spacecraft Propulsion and Power
    Type: Center for Advanced Space Propulsion; 42-44; NASA-CR-199689
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