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  • Other Sources  (303)
  • SPACECRAFT PROPULSION AND POWER  (281)
  • Chemical Engineering
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  • 1990-1994  (286)
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  • 11
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    Concurrent engineering (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The following subject areas are covered: issues (liquid rocket propulsion - current development approach, current certification process, and costs of engineering changes); state of the art (DICE information management system, key government participants, project development strategy, quality management, and numerical propulsion system simulation); needs identified; and proposed program.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington, Space Transportation Propulsion Technology Symposium. Volume 3: Panel Session Summaries and Presentations; p 973-988
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Radiation resistance of Ge, Ge0.93Si0.07, GaAs and Al0.08Ga0.92 as solar cells (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Solar cells made of Ge, Ge(0.93)Si(0.07) alloys, GaAs and Al(0.08)Ga(0.92)As were irradiated in two experiments with 1-meV electrons at fluences as great as 1 x 10(exp 16) cm(exp-2). Several general trends have emerged. Low-band-gap Ge and Ge(0.93)Si(0.07) cells show substantial resistance to radiation-induced damage. The two experiments showed that degradation is less for Al(0.08)Ga(0.92)As cells than for similarly irradiated GaAs cells. Compared to homojunctions, cells with graded-band-gap emitters did not show the additional resistance to damage in the second experiment that had been seen in the first. The thickness of the emitter is a key parameter to limit the degradation in GaAs devices.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Space Photovoltaic Research and Technology Conference; 10 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Propulsion system filter sizing considerations for the Galileo spacecraft (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Filtration capacity of the Galileo propulsion system has been investigated. Ground testing of flight spare components has been conducted to determine the representative number and size distribution of particulate matter collected in flow tests. For these tests and for filter qualification tests, a number of effects were examined. The influence of gravitational particle settling on ground test results vs the flight environment was considered. Centrifugal effects inherent in the test apparatus and/or the propulsion system could have an influence. Variability among particle sizing techniques was explored. The influence of size distribution, particle shape, and density in the choice of a particulate test material was studied. Characteristics for AC Coarse Dust (an industry standard filter test media), microscopic polymer beads, and aluminum oxide particulate test matter are listed. Filtration tests were conducted using AC Coarse Dust and mixtures containing components of AC Coarse Dust. These results are expected to be useful data for filter sizing of future spacecraft.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-1941
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Arcing of negatively biased solar cells in a plasma environment. I - Experimental observations (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A variety of experiments have been performed which identify key factors contributing to the arcing of negatively biased high voltage solar cells operating in a low earth orbit plasma environment. These efforts have led to a reduction of greater than a factor of 100 in the arc frequency of a single cells following proper remeditation procedures. Experiments naturally led to and focused on the adhesive/encapsulating that is used to bond the protective cover slip to the solar cell. An image-intensified CCD camera system recorded UV emission from arc events which occurred exclusively along the interfacial edge between the cover slip and the solar cell. Microscopic inspection of this interfacial region showed a bead of encapsulant along this entire edge. Elimination of this encapsulant bead reduced the arc frequency by two orders of magnitude.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-2990
    Format: text
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    NASA TECHNICAL REPORTS
  • 15
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    Experimental determination of convective heat transfer coefficients in the separated flow region of the Space Shuttle Solid Rocket Motor (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A series of cold flow heat transfer tests was conducted with a 7.5-percent scale model of the Space Shuttle Rocket Motor (SRM) to measure the heat transfer coefficients in the separated flow region around the nose of the submerged nozzle. Modifications were made to an existing 7.5 percent scale model of the internal geometry of the aft end of the SRM, including the gimballed nozzle in order to accomplish the measurements. The model nozzle nose was fitted with a stainless steel shell with numerous thermocouples welded to the backside of the thin wall. A transient 'thin skin' experimental technique was used to measure the local heat transfer coefficients. The effects of Reynolds number, nozzle gimbal angle, and model location were correlated with a Stanton number versus Reynolds number correlation which may be used to determine the convective heating rates for the full scale Space Shuttle Solid Rocket Motor nozzle.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-0043
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    SRB Environment Evaluation and Analysis. Volume 3: ASRB Plume Induced Environments (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Contract NAS8-37891 was expanded in late 1989 to initiate analysis of Shuttle plume induced environments as a result of the substitution of the Advanced Solid Rocket Booster (ASRB) for the Redesigned Solid Rocket Booster (RSRB). To support this analysis, REMTECH became involved in subscale and full-scale solid rocket motor test programs which further expanded the scope of work. Later contract modifications included additional tasks to produce initial design cycle environments and to specify development flight instrumentation. Volume 3 of the final report describes these analyses and contains a summary of reports resulting from various studies.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-192519 , NAS 1.26:192519 , RTR-213-01-VOL-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Computational Fluid Dynamic Modeling of Rocket Based Combined Cycle Engine Flowfields (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Computational Fluid Dynamic techniques are used to study the flowfield of a fixed geometry Rocket Based Combined Cycle engine operating in rocket ejector mode. Heat addition resulting from the combustion of injected fuel causes the subsonic engine flow to choke and go supersonic in the slightly divergent combustor-mixer section. Reacting flow computations are undertaken to predict the characteristics of solutions where the heat addition is determined by the flowfield. Here, adaptive gridding is used to improve resolution in the shear layers. Results show that the sonic speed is reached in the unheated portions of the flow first, while the heated portions become supersonic later. Comparison with results from another code show reasonable agreement. The coupled solutions show that the character of the combustion-based thermal choking phenomenon can be controlled reasonably well such that there is opportunity to optimize the length and expansion ratio of the combustor-mixer.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA Propulsion Engineering Research Center, Volume 2; p 182-188
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Disposal modes for Mars transfer nuclear propulsion (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A managed disposal approach is proposed that would place the nuclear stage or vehicle in a highly stable orbit at modest cost to mission performance. The approach requires only a small increase in initial mass in LEO, but should be included in preliminary trajectory design and performance calculations. The mass penalty is expected to be larger for all-up flight profiles, or in cases of high-thrust propulsion systems for the cargo vehicle.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-3410
    Format: text
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    NASA TECHNICAL REPORTS
  • 19
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    Anode arc motion in high power arcjets (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The long-term operational lifetime of most medium to high power arcjets is currently limited by the rapid deterioration of the arcjet electrodes. To a large extent, the rate of this deterioration is related to the motion of the arc discharge on the electrode surfaces. This paper details a series of experiments aimed at studying the temporal behavior of dc arcs on a water-cooled radially-segmented 30 kW class arcjet anode. The experimental anode used for these tests was made of copper, and was divided into four equivalent radial segments which were electrically isolated with aluminum oxide gaskets. The current carried by each segment was measured independently using four calibrated resistive shunts, and was analyzed by digital computer. The tests were limited to nitrogen propellant over a current range of 100-250 A dc. Results show that for the range of total currents considered here, the current distribution in the segmented arcjet anode is generally asymmetric, exhibiting random fluctuations over a wide range of frequencies.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3838
    Format: text
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    NASA TECHNICAL REPORTS
  • 20
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    Physical model and experimental results of cathode erosion related to power supply ripple (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: This paper discusses the physical effects of power supply ripple on cathode erosion and cathode arc attachment in a water-cooled, 30 kW nitrogen arcjet. Experimental results are presented for 2 percent thoriated tungsten, which show that the long-term cathode erosion rate is a decreasing function of current ripple over the range 1-13 percent. Above this range, the cathode discharge becomes unstable, and the erosion rate rapidly increases. A qualitative model of this effect is given in terms of a magnetically induced radial motion of the arc column, and an overall increase in the cathode spot radius due to the higher peak current associated with higher ripple. The most important effect of power supply ripple is therefore shown to be its ability to collectively drive the cathode attachment away from the cathode center. This leads to an increase in the cathode attachment area, and a subsequent decrease in the cathode erosion rate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3837
    Format: text
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    NASA TECHNICAL REPORTS
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