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  • Spacecraft Design, Testing and Performance  (6)
  • Geophysics  (5)
  • AERODYNAMICS
  • Mice
  • 1995-1999  (12)
  • 1
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    Regulated delivery of therapeutic proteins after in vivo somatic cell gene transfer (1999)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 1999
    Description: Stable delivery of a therapeutic protein under pharmacologic control was achieved through in vivo somatic gene transfer. This system was based on the expression of two chimeric, human-derived proteins that were reconstituted by rapamycin into a transcription factor complex. A mixture of two adeno-associated virus vectors, one expressing the transcription factor chimeras and one containing erythropoietin (Epo) under the control of a promoter responsive to the transcription factor, was injected into skeletal muscle of immune-competent mice. Administration of rapamycin resulted in 200-fold induction of plasma Epo. Stable engraftment of this humanized system in immune-competent mice was achieved for 6 months with similar results for at least 3 months in a rhesus monkey.〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Ye, X -- Rivera, V M -- Zoltick, P -- Cerasoli, F Jr -- Schnell, M A -- Gao, G -- Hughes, J V -- Gilman, M -- Wilson, J M -- P01 AR/NS43648-03/AR/NIAMS NIH HHS/ -- P30 DK47757-05/DK/NIDDK NIH HHS/ -- New York, N.Y. -- Science. 1999 Jan 1;283(5398):88-91.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Institute for Human Gene Therapy, University of Pennsylvania, Philadelphia, PA 19104, USA.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/9872748" target="_blank"〉PubMed〈/a〉
    Keywords: Animals ; Cytomegalovirus/genetics ; Dependovirus/genetics ; Erythropoietin/administration & dosage/blood/*genetics ; Female ; Gene Expression Regulation ; *Gene Transfer Techniques ; Genetic Therapy/*methods ; Genetic Vectors ; Hematocrit ; Injections, Intramuscular ; Macaca mulatta ; Male ; Mice ; Mice, Inbred BALB C ; Mice, Nude ; Muscle, Skeletal ; Promoter Regions, Genetic ; Recombinant Fusion Proteins ; Recombinant Proteins ; Sirolimus/*pharmacology ; Transcription Factors/*genetics
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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    PAPER CURRENT
  • 2
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    Innovative Contamination Certification of Multi-Mission Flight Hardware (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Maintaining contamination certification of multi-mission flight hardware is an innovative approach to controlling mission costs. Methods for assessing ground induced degradation between missions have been employed by the Hubble Space Telescope (HST) Project for the multi-mission (servicing) hardware. By maintaining the cleanliness of the hardware between missions, and by controlling the materials added to the hardware during modification and refurbishment both project funding for contamination recertification and schedule have been significantly reduced. These methods will be discussed and HST hardware data will be presented.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 20th Space Simulation Conference: The Changing Testing Paradigm; 1-13; NASA/CP-1999-208598
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Influence of Shock-Induced Ionospheric Conductivity Enhancements on Storm Main Phase Intensities (1999)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Keywords: Geophysics
    Type: International Union of Geodesy and Geophysics (IUGG) '99; Birmingham; United Kingdom
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Interball substorm observations: Christmas for space scientists (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Observational results from the Interball Tail Probe spacecraft are presented. One of the main objectives of the Interball project is to study the dynamic processes in the magnetosphere. Three events observed by the spacecraft's instruments are investigated: a pseudobreakup during which earthward streaming ions were observed in the vicinity of a thin current sheet; a substorm in which the magnetic signatures in the lobe and on the ground were preceeded by northward re-orientation of the interplanetary magnetic field Bz component; and a magnetic storm at the beginning of which extreme deformation of the magnetotail was observed.
    Keywords: Geophysics
    Type: ; 497-506
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Statistical Treatment of Earth Observing System Pyroshock Separation Test Data (1998)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The Earth Observing System (EOS) AM-1 spacecraft for NASA's Mission to Planet Earth is scheduled to be launched on an Atlas IIAS vehicle in June of 1998. One concern is that the instruments on the EOS spacecraft are sensitive to the shock-induced vibration produced when the spacecraft separates from the launch vehicle. By employing unique statistical analysis to the available ground test shock data, the NASA Lewis Research Center found that shock-induced vibrations would not be as great as the previously specified levels of Lockheed Martin. The EOS pyroshock separation testing, which was completed in 1997, produced a large quantity of accelerometer data to characterize the shock response levels at the launch vehicle/spacecraft interface. Thirteen pyroshock separation firings of the EOS and payload adapter configuration yielded 78 total measurements at the interface. The multiple firings were necessary to qualify the newly developed Lockheed Martin six-hardpoint separation system. Because of the unusually large amount of data acquired, Lewis developed a statistical methodology to predict the maximum expected shock levels at the interface between the EOS spacecraft and the launch vehicle. Then, this methodology, which is based on six shear plate accelerometer measurements per test firing at the spacecraft/launch vehicle interface, was used to determine the shock endurance specification for EOS. Each pyroshock separation test of the EOS spacecraft simulator produced its own set of interface accelerometer data. Probability distributions, histograms, the median, and higher order moments (skew and kurtosis) were analyzed. The data were found to be lognormally distributed, which is consistent with NASA pyroshock standards. Each set of lognormally transformed test data produced was analyzed to determine if the data should be combined statistically. Statistical testing of the data's standard deviations and means (F and t testing, respectively) determined if data sets were significantly different at a 95-percent confidence level. If two data sets were found to be significantly different, these families of data were not combined for statistical purposes. This methodology produced three separate statistical data families of shear plate data. For each population, a P99.1/50 (probability/confidence) per-separation-nut firing level was calculated. By using the binomial distribution, Lewis researchers determined that this pernut firing level was equivalent to a P95/50 per-flight confidence level. The overall envelope of the per-flight P95/50 levels led to Lewis' recommended EOS interface shock endurance specification. A similar methodology was used to develop Lewis' recommended EOS mission assurance levels. The available test data for the EOS mission are significantly larger than for a normal mission, thus increasing the confidence level in the calculated expected shock environment. Lewis significantly affected the EOS mission by properly employing statistical analysis to the data. This analysis prevented a costly requalification of the spacecraft's instruments, which otherwise would have been exposed to significantly higher test levels.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Research and Technology 1997; NASA/TM-1998-206312
    Format: application/pdf
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  • 6
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    Acoustic Testing of the Cassini Spacecraft and Titan 4 Payload Fairing (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA Lewis Research Center recently led a multi-organizational acoustic test program. This testing consisted of acoustically exciting a Cassini spacecraft simulator in a full scale 60 foot high Titan 4 payload fairing with various acoustic blanket designs and configurations in a large reverberant acoustic chamber. The primary purpose of this test program was to measure the fairing's internal acoustics and spacecraft vibration, especially the Radioisotope Thermoelectric Generators (RTG) vibration, and to quantify the mitigation efforts in reducing these levels. Key to this reduction effort was the utilization of new acoustic blanket designs. This paper will provide the background and rationale for performing this test program, state the test program's primary and secondary objectives and describe the test matrix, hardware and instrumentation. A second part companion paper will provide the test results and data analysis.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-TM-107474 , NAS 1.15:107474 , E-10763 , Shock and Vibration; Nov 18, 1996 - Nov 22, 1996; Monterey, CA; United States
    Format: application/pdf
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  • 7
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    Acoustic Testing of the Cassini Spacecraft and Titan IV Payload Fairing (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A Cassini spacecraft simulator in a full scale 60 foot high Titan 4 payload fairing with various acoustic blanket designs and configurations was recently tested in a large reverberant acoustic chamber. A first part companion paper provides the test configuration details and other background information. This paper addresses the results obtained from this test program. Emphasis will be on the effects of the new blanket designs on reducing the payload fairing's internal acoustics and the vibration response of the spacecraft's Radioisotope Thermoelectric Generators. Other results discussed include: the effect of blankets on fairing vibration, the effect of partial blanket coverage on acoustics and vibration and the effect of tuned vibration absorbers.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-TM-107475 , NAS 1.15:107475 , E-10764 , Shock and Vibration; Nov 18, 1996 - Nov 22, 1996; Monterey, CA; United States
    Format: application/pdf
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  • 8
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    A Statistical Study of the Global Structure of the Ring Current (1997)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: In this paper we derive the average configuration of the ring current as a function of the state of the magnetosphere as indicated by the Dst index. We sort magnetic field data from the Combined Release and Radiation Effects Satellite (CRRES) by spatial location and by the Dst index in order to produce magnetic field maps. From these maps we calculate local current systems by taking the curl of the magnetic field. NN7e find both the westward (outer) and the eastward (inner) components of the ring current. We find that the ring current intensity varies linearly with D.St as expected, and that the ring current is asymmetric for all Dst values. The azimuthal peak of the ring current is located in the afternoon sector for quiet conditions, and near midnight for disturbed conditions. The ring current also moves closer to the Earth during disturbed conditions. We are able to recreate the Dst index by integrating the magnetic perturbations caused by the ring current. We find that we needed to apply a 20 nT offset to Dst, and assume a perfectly conducting Earth to obtain an optimal agreement between the computed and the observed Dst. We interpret the 20 nT offset as the magnetic field generated by the quiet time ring current used as baseline in computing Dst.
    Keywords: Geophysics
    Format: application/pdf
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  • 9
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    Innovative Contamination Certification of Multi-Mission Flight Hardware (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Maintaining contamination certification of multi-mission flight hardware is an innovative approach to controlling mission costs. Methods for assessing ground induced degradation between missions have been employed by the Hubble Space Telescope (HST) Project for the multi-mission (servicing) hardware. By maintaining the cleanliness of the hardware between missions, and by controlling the materials added to the hardware during modification and refurbishment both project funding for contamination recertification and schedule have been significantly reduced. These methods will be discussed and HST hardware data will be presented.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Space Simulation; Oct 27, 1998 - Oct 29, 1998; Annapolis, MD; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Automation of satellite operations: Experiences and future directions at NASA GSFC (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The current state of satellite operation automation at the NASA Goddard Space Flight Center (GSFC), MD, is described, discussing the short term future and presenting a vision of how automation should be used in future systems. The automation practices currently applied in several current programs are surveyed. The rapidly evolving level of spacecraft autonomy is considered, reviewing how future onboard capabilities will affect ground based automation efforts. The optimum role of automation is discussed and automation principles are presented that can be used to identify favorable opportunities for simplifying and reducing the operating cost of spaceborne science missions.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Paper-SO96.8.007 , The Fourth International Symposium on Space Mission Operations and Ground Data Systems; 3; 1262-1269; ESA-SP-394-Vol-3
    Format: text
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