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  • Other Sources  (177)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (167)
  • Inorganic Chemistry
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  • Umweltmedizin
  • ddc:554.3
  • 1980-1984  (169)
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  • 1920-1924  (4)
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  • 1980  (169)
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  • 1980-1984  (169)
  • 1945-1949
  • 1935-1939  (4)
  • 1920-1924  (4)
  • 1915-1919
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  • 101
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    Plasma collection by high voltage spacecraft at low earth orbit (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computer model of the three-dimensional sheath formation and plasma current collection by high voltage spacecraft has been developed. By using new space charge density and plasma collection algorithms, it is practical to perform calculations for large, complex spacecraft. The model uses NASCAP compatible objects and geometries. Results indicate that ion focusing observed in the laboratory during high voltage collection experiments is probably due to voltage gradients on the collecting surfaces.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0042 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 102
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    Modelling of environmentally induced discharges in geosynchronous satellites (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASCAP computer code was used to compute the charging and discharging characteristics of a typical communications satellite in geosynchronous orbit. For the case of a severe substorm satellite surface differential charging in sunlight was found to be substantially less than that required to produce discharges in ground simulation studies. A discharge process was postulated involving discharges triggered at edges (or imperfection) followed by discharges to space. The characteristics of such discharges was parametrically varied to evaluate the possible effects on the satellite. Results indicated that discharge characteristics inferred from satellite monitors could be caused by predicted space discharges, that single cell discharges to space can reduce surface potentially over entire satellite, and that low density electron trajectory computations indicate that discharge generated electrons do not return to the satellite by long trajectories. Current transients predicted do not agree with available ground simulation results indicating that additional work must be done both analytically and experimentally to understand and fully explain these discrepancies.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81598 , E-581 , Ann. Conf. on Nucl. and Space Radiation Effects; Jul 15, 1980 - Jul 18, 1980; Ithaca, NY; United States
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  • 103
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    Analysis of differential and active charging phenomena on ATS-5 and ATS-6 (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft charging on the differential charging and artificial particle emission experiments on ATS 5 and ATS 6 were studied. Differential charging of spacecraft surfaces generated large electrostatic barriers to spacecraft generated electrons, from photoemission, secondary emission, and thermal emitters. The electron emitter could partially or totally discharge the satellite, but the mainframe recharged negatively in a few 10's of seconds. The time dependence of the charging behavior was explained by the relatively large capacitance for differential charging in comparison to the small spacecraft to space capacitance. A daylight charging event on ATS 6 was shown to have a charging behavior suggesting the dominance of differential charging on the absolute potential of the mainframe. Ion engine operations and plasma emission experiments on ATS 6 were shown to be an effective means of controlling the spacecraft potential in eclipse and sunlight. Elimination of barrier effects around the detectors and improving the quality of the particle data are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-163433 , UCSD-CASS-80-1
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  • 104
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    NASCAP modelling computations on large optics spacecraft in geosynchronous substorm environments (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Charging Analyzer Program (NASCAP) is used to evaluate qualitatively the possibility of such enhanced spacecraft contamination on a conceptual version of a large satellite. The evaluation is made by computing surface voltages on the satellite due to encounters with substorm environments and then computing charged particle trajectories in the electric fields around the satellite. Particular attention is paid to the possibility of contaminants reaching a mirror surface inside a dielectric tube because this mirror represents a shielded optical surface in the satellite model used. Deposition of low energy charged particles from other parts of the spacecraft onto the mirror was found to be possible in the assumed moderate substorm environment condition. In the assumed severe substorm environment condition, however, voltage build up on the inside and edges of the dielectric tube in which the mirror is located prevents contaminants from reaching the mirror surface.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81395 , E-305 , Soc. of Photo-Optical Instrumentation Engineers, Los Angeles Technical Symp.; Feb 04, 1980 - Feb 07, 1980; North Hollywood, CA; United States
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  • 105
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    Laboratory simulation of irradiation-induced dielectric breakdown in spacecraft charging (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The discharging of dielectric samples irradiated by a beam of monoenergetic electrons is investigated. The development of a model, or models, which describe the discharge phenomena occuring on the irradiated dielectric targets is discussed. The electrical discharge characteristics of irradiated dielectric samples are discussed and the electrical discharge paths along dielectric surfaces and within the dielectric material are determined. The origin and destination of the surface emitted particles is examined and the charge and energy balance in the system is evaluated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-162762
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  • 106
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    Control systems design for large flexible space structures (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several approaches for the design of reduced-order linear-quadratic-Gaussian type controllers for large space structures were proposed and evaluated using a continuous model of a long free-free beam. Sufficient conditions were derived for the asymptotic stability with this type of controller. A finite-element model of a free-free-free-free square plate was obtained for use in control systems studies. A method was developed for optimal damping enhancement in large space structures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-162582
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  • 107
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    Configuration effects on satellite charging response (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The response of various spacecraft configurations to a charging environment in sunlight was studied using the NASA Charging Analyzer Program code. The configuration features geometry, type of stabilization, and overall size. Results indicate that sunlight charging response is dominated by differential charging effects. Shaded insulation charges negatively result in the formation of potential barriers which suppress photoelectron emission from sunlit surfaces. Sunlight charging occurs relatively slowly: with 30 minutes of charging simulations, in none of the configurations modeled did the most negative surface cell reach half its equilibrium potential in eclipse.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81397 , E-307 , Aerospace Sci. Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA; United States
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  • 108
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    Three dimensional space charge model for large high voltage satellites (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: High power solar arrays for satellite power systems with dimensions of kilometers, and with tens of kilovolts distributed over their surface face many plasma interaction problems that must be properly anticipated. In most cases, the effects cannot be adequately modeled without detailed knowledge of the plasma sheath structure and space charge effects. Two computer programs were developed to provide fully self consistent plasma sheath models in three dimensions as a result of efforts to model the experimental plasma sheath studies at NASA/JSC. Preliminary results indicate that for the conditions considered, the Child-Langmuir diode theory can provide a useful estimate of the plasma sheath thickness. The limitations of this conclusion are discussed. Some of the models presented exhibit the strong ion focusing observed in the JSC experiments.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 957-978
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  • 109
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    Simulation of charging response of SCATHA (P78-2) satellite (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A model of the satellite charging at high altitudes (SCATHA P78-2) satellite was used to simulate the charging response of SCATHA at geosynchronous orbit. The model includes a description of the geometry, currents to exposed surface materials, and electrical connections on the spacecraft. The charging response of the vehicle to that predicted by the NASCAP model for the Day 87, 1979 eclipse charging event, in which the spacecraft charged to several kilovolts negative during a magnetospheric substorm are compared. Double Maxwellian representations of the plasma environment reproduce the charging response observed experimentally.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 580-591
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  • 110
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    Aspect dependence and frequency spectrum of electrical discharges on the P78-2 (SCATHA) satellite (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The satellite charging at high altitudes (SCATHA) P78-2 satellite payload includes a charging electrical effects analyzer (CEEA) which measures the characteristics of electrical discharges in both the frequency and time domain. Pulses are detected in response to commands during electron and ion beam operations and during natural discharge events. The pulse analyzer measures the shape of pulses on four sensors and is the primary CEEA diagnostic for the natural discharges. Only five discharges were found in the data at a time when the pulse analyzer was in mode with sufficient time resolution to resolve the frequency components in the waveform.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 478-492
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  • 111
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    Operation of SC5 rapid scan particle spectrometer on SCATHA satellite (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The SC5 rapid scan particle spectrometer, operating on the SCATHA satellite, is discussed. SC5 in-orbit operation and reduction of electrostatic analyzer (ESA) spectra are addressed. ESA data summaries from ion and electron gun operations are explained. Data from gun operations show how the satellite potential responds and provide information on the various time constants involved.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 386-411
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  • 112
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    Numerical simulation of plasma insulator interactions in space. Part 2: Dielectric effects (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Any process which may be modeled statistically for a simple plasma particle may be modeled by the particle in cell technique. The success of the calculation is then dependent on having a large enough number of particles that the statistical treatment is meaningful. Thus it is possible to include the effects of secondary emission, backscattering, charge sticking and possibly dielectric breakdown, photoemission, and spallation. The first plasma dielectric interaction included in the computer code for simulating plasma insulator interactions is secondary electron emission. A calculated current density vs. voltage curve is presented and compared to an experimental curve.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 946-956
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  • 113
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    Calculation of surface current response to surface flashover of a large sample under grounded and floating conditions (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Results for the electromagnetic response to the discharge of an 80 cm diameter dielectric sample mounted on a 120 cm diameter cylinder are presented. It is assumed that the dielectric is charged with a known potential profile dropping sharply near the edge, and the substrate initially grounded. During the early part of the discharge (approximately 10 ns) there is little difference between the grounded and floating cases. Beyond about 10 ns the grounded experiment is in approximate steady state, continuous to blow off charge until the dielectric is substantially discharged. The floating case, however, shows modestly decreasing emission and response. Eventually, a quasi-steady state is reached in which charge is transported from dielectric to substrate rather than blown off.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 730-744
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  • 114
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    Molecular wake shield gas analyzer (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Techniques for measuring and characterizing the ultrahigh vacuum in the wake of an orbiting spacecraft are studied. A high sensitivity mass spectrometer that contains a double mass analyzer consisting of an open source miniature magnetic sector field neutral gas analyzer and an identical ion analyzer is proposed. These are configured to detect and identify gas and ion species of hydrogen, helium, nitrogen, oxygen, nitric oxide, and carbon dioxide and any other gas or ion species in the 1 to 46 amu mass range. This range covers the normal atmospheric constituents. The sensitivity of the instrument is sufficient to measure ambient gases and ion with a particle density of the order of one per cc. A chemical pump, or getter, is mounted near the entrance aperture of the neutral gas analyzer which integrates the absorption of ambient gases for a selectable period of time for subsequent release and analysis. The sensitivity is realizable for all but rare gases using this technique.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-161926
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  • 115
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    Representation and material charging response of geoplasma environments (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The sensitivity of the charging response to the representation of the measured environments and material properties are discussed. Single and double Maxwellian representations are compared with direct numerical integration of the observed spectra. The effect of anisotropic incident flux distribution is modeled. In addition, the effect of the high energy radiation upon bulk conductivity and hence differential charging is examined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 560-579
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  • 116
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    Flight evidence of spacecraft surface contamination rate enhancement by spacecraft charging obtained with a quartz crystal microbalance (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The significance of the fraction of the mass outgassed by a negatively charged space vehicle which is ionized within the vehicle plasma sheath and electrostatically reattracted to the space vehicle was determined. The ML-12 retarding potential analyzer/temperature controlled quartz crystal microbalances (RPA/TQCMs) distinguishes between charged and neutral molecules and investigates contamination mass transport mechanism. Two long term, quick look flight data sets indicate that on the average a significant fraction of mass arriving at one RPA/TQCM is ionized. It is assumed that vehicle frame charging during these periods was approximately uniformly distributed in degree and frequency. It is shown that electrostatic reattraction of ionized molecules is an important contamination mechanism at and near geosynchronous altitudes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 493-508
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  • 117
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    satellite surface potential survey (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Results of Kapton differential voltage charging of the satellite surface potential monitor Kapton samples are presented for the first 100 days of P78-2 operations. Daily charging occurrences are plotted in magnetic local time and L-shell (altitude and magnetic latitude) space as a function of magnetic activity. Most of the low level charging occurs well into the dawn local time sector whereas the highest voltage levels occur in the premidnight local time sector. The probabilities of differential charging are extremely dependent on the local time sector, the altitude (or L-shell) and of course, the magnetic activity.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 461-469
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  • 118
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    P78-2 engineering overview (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Data from the P78-2 spacecraft are being used in verifying and validating analytical tools being developed for the design of spacecraft, such as NASCAP, for updating Military Standard 1541, for investigation of materials contamination, and for a study of the physics of charging. The analysis of this data has already resulted in changes in laboratory testing procedures, in a better understanding of some properties of materials exposed to the space environment, and in some insight into the EMI caused by discharges on spacecraft in a plasma environment. Some examples of early results from the engineering experiments are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 439-460
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  • 119
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    Electron angular distributions during charging events (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The angular distribution of electrons and ions at times of spacecraft charging were examined for several charging events. Generally it was found that electrons measured perpendicular to the Earth's magnetic field are more intense and more energetic than those measured parallel to the magnetic field during charging events. During the substorm charging injection, the electron spectra harden at all angles to the magnetic field as the evolution of the charging spectra is monitored by the P78-2 satellites. An example of the onset of charging and the changes in the electron distributions is examined. The evolution of the electrons from a 'soft' plasma sheet distribution to a 'hard' charging distribution is compared with the charging of Kapton on the satellite and the spacecraft frame potential. The ions are used to determine the spacecraft potential. Evidence of periodic surface potential variations related to particle anisotropies are presented and discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 370-385
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  • 120
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    Charging of a large object in low polar Earth orbit (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The charging of a large sphere subject to the environment encountered by the shuttle orbiter as it passes through the auroral regions in its low polar Earth orbit was investigated. The environment consists of a low temperature dense plasma and a relatively intense (200 mu A/sq m) field aligned flux of energetic electrons (approximately 5 to 10 keV). The potential on a sphere in eclipse is presented as a function of the ratio kappa of the charging rate produced by precipitating electrons to the discharging rate produced by ram ions. It was found that a 5 meter conducting sphere charges to potentials of order 1 kilovolt for kappa approximately 2, even though a 0.5 meter sphere charges to less than 100 volts. It is concluded that the natural charging environment can induce large potentials (approximately 1 kilovolt) on the shuttle orbiter.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 979-989
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  • 121
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    Numerical simulation of plasma insulator interactions in space. Part 1: The self consistent calculation (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A computer program is being developed to simulate the interaction of a plasma with a conducting disk partially covered by an insulator. Initial runs consider only charge sticking to the dielectric. Results indicate that the current density drawn by the hole in the dielectric increases approximately linearly with voltage for conductor voltages between 5 volts and 250 volts.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 932-945
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  • 122
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    Disappearance and reappearance of particles of energies 50 keV as seen by P78-2 (SCATHA) near geosynchronous orbit (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The nightside particle environment as observed by the AFGL Rapid Scan Particle Detector on SCATHA showing large, sudden simultaneous changes in the fluxes of electrons and protons with energies above 50 keV (dropouts) is considered. An interesting feature of SCATHA dropouts is the quasiperiodic behavior of the particle flux amplitudes which often vary with a period of the order of 15 minutes both during the dropout and after the return. A flux return during eclipse caused a major spacecraft charging event of several kilovolts. The SCATHA observations are compared with those reported for other geosynchronous satellites. In agreement with ATS-5, a marked dependence in the frequency of occurrence due to an effect of the orbit is found. ATS-5 experienced few dropouts during quiet geomagnetic conditions. However, for an L shell greater than seven, SCATHA particle dropouts occur routinely during quiet conditions. Thus, for SCATHA's orbit, both the orbital position and geomagnetic conditions must be taken into account in evaluating the potential hazard of flux returns.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 755-767
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  • 123
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    SCATHA observations of space plasma composition during a spacecraft charging event (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: During an Earth eclipse of the SCATHA spacecraft, the spacecraft charged to potentials greater than 1KV for about 30 minutes with extended excursions greater than 4KV. The composition of the hot plasma was obtained in the 0.1 to 32 keV energy range with an ion mass spectrometer aboard the spacecraft. Prior to the onset of the charging event, H(+) was the principal plasma ion, and during the event O(+) was the principal ion. The composition was energy dependent and varied significantly on a time scale of 4 minutes. An assumption that the ion flux was all H(+) led to computed number densities that were in error by more than a factor of two for several time intervals during the event.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol. 1980; p 433-438
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  • 124
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    Electrostatic charging characteristics of thermal control paints as function of temperature (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The charging characteristics of paints for various uses on spacecraft under electron bombardment were studied. It was found that there is not a strong temperature dependence of the charging characteristics between -155 C and +30 C; and there is a noticeable hystereis effect as the electron beam energy is varied. Furthermore, all of the paints tested exhibit large secondary yields at low (approx. 1 keV) bombarding electron energies; and surfaces can charge either positively or negatively depending on the conditions and the paint. It was concluded that paints are not simple, will require more detailed study, and will probably act differently in multiple energy electron tests.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 209-319
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  • 125
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    Annual survey of spaceflight safety systems - 10th supplement /Survey period: July 1979-June 1980/ (1980)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The survey summarizes 15 papers whose topics represent significant safety developments reported between July 1979 and June 1980 in connection with spaceflight. The majority of the papers address the Space Shuttle mission (control-system software modification; abort procedures; Vandenberg AFB launch operations; assembly and repair of the Orbiter's Thermal Protection System; flight hardware). One paper describes a procedure aiding Space Transportation System (STS) payload organizations in complying with safety requirements established by NASA. Spacecraft cabin environments, collision avoidance in near-earth space, and intercept and rendezvous charts are other topics of discussion. The survey also includes two papers outlining the European and Chinese approaches to astronaut selection and training.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 80-IAA-16 , International Astronautical Congress; Sept. 22-28, 1980; Tokyo; Japan
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  • 126
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    On the dynamics of large orbiting flexible beams and platforms oriented along the local horizontal (1980)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The dynamics and stability of large orbiting flexible beams and platforms oriented along the local horizontal are treated both analytically and numerically. It is assumed that such structures could be gravitationally stabilized by attaching a rigid lightweight dumbbell at the center of mass by a spring loaded hinge which also could provide viscous damping. For the beam it is seen that the small amplitude inplane pitch motion, dumbbell librational motion, and the anti-symmetric elastic modes are all coupled. The three dimensional equations of motion for a circular flat plate in orbit with a two-degree-of-freedom gimballed dumbbell are also developed and show that only those elastic modes described by a single nodal diameter line are influenced by the dumbbell motion. Stability criteria are developed for both examples and a parametric study of the least damped mode characteristics together with numerically simulated transient responses are carried out.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 80-E-230 , International Astronautical Congress; Sept. 22-28, 1980; Tokyo; Japan
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  • 127
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    NASA low and ultralow temperature cryogenic cooler systems for space missions (1980)
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    Publication Date: 2019-08-27
    Description: The paper describes the NASA research program to provide low and ultralow temperature cryogenic cooler systems for future space missions. These include mechanical, solid cryogen, superfluid helium, helium-3, and helium-3/helium-4 dilution coolers, and all systems must function in the zero gravity environment of space. The temperatures produced range from tens of kelvin down to a few millikelvin; at higher temperatures cooling loads for sensors or detectors and associated sun shields may range up to a few watts. At the ultralow temperature end, cooling loads must be limited to tens of microwatts.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 128
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    Satellite Power Systems /SPS/ - Overview of system studies and critical technology (1980)
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    Publication Date: 2019-08-28
    Description: Systems studies and critical technology issues for the development and evaluation of Satellite Power Systems (SPS) for the photovoltaic generation of electrical energy and its transmission to earth are reviewed. Initial concept studies completed in 1976 and system definition studies initiated in the same year have indicated the technical feasibility of SPS and identified challenging issues to be addressed as part of the SPS Concept Development and Evaluation Program. Systems considered in the study include photovoltaic and solar thermal power conversion configurations employing klystron or solid state microwave generators or lasers for power transmission, and power transmission options, system constructability and in-orbit and ground operations. Technology investigations are being performed in the areas of microwave power transmission, structure/controls interactions and the behavior of key materials in the space/SPS environment. Favorable results have been obtained in the areas of microwave phase distribution and phase control, dc-RF conversion, antenna radiating element, and no insurmountable problems have been discovered in any of the investigations to date.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 80-084 , Goddard Memorial Symposium; March 27, 28, 1980; Washington, D. C.
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  • 129
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    Without a table of ranks: Presenting the creators of Radio-1 and Radio-2 (1980)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The design and operation of ham radio operator satellites is discussed. Major emphasis is placed on the personalities involved in the project.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Without Tables of Ranks and the Iskra Student Design Bureau (NASA-TM-76277); p 1-23
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  • 130
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    A two-level controller design approach for large space structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A controller design approach is proposed for large space structures (LSS) using an Annular Momentum Control Device (AMCD). The controller consists of a primary attitude controller and a secondary or modal damping enhancement controller. It is proved that the LSS/AMCD system using the proposed damping enhancement controller is stable in the sense of Lyapunov regardless of the number of modes in the model and without the necessity of precise knowledge of the modal frequencies and mode shapes. Numerical results obtained for the secondary controller design for a large thin flat plate indicate that the proposed method can yield satisfactory damping enhancement with small weight penalty.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Joint Automatic Control Conference; Aug 13, 1980 - Aug 15, 1980; San Francisco, CA
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  • 131
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    Design, fabrication and test of graphite/polyimide composite joints and attachments for advanced aerospace vehicles (1980)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Results of an experimental program to develop several types of graphite/polyimide (GR/PI) bonded and bolted joints for lightly loaded flight components for advanced space transportation systems and high speed aircraft are presented. Tasks accomplished include: a literature survey; design of static discriminator specimens; design allowables testing; fabrication of test panels and specimens; small specimen testing; and standard joint testing. Detail designs of static discriminator specimens for each of the four major attachment types are presented. Test results are given for the following: (1) transverse tension of Celion 3000/PMR-15 laminate; (2) net tension of a laminate for both a loaded and unloaded bolt hole; (3) comparative testing of bonded and co-cured doublers along with pull-off tests of single and double bonded angles; (4) single lap shear tests, transverse tension and coefficient of thermal expansion tests of A7F (LARC-13 amide-imide modified) adhesive; and (5) tension tests of standard single lap, double lap, and symmetric step lap bonded joints. Also, included are results of a finite element analysis of a single lap bonded composite joint.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-159113 , QTPR-6
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  • 132
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    On maneuvering large flexible spacecraft using an annular momentum control device (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A scheme for the control and maneuvering of a large flexible spacecraft by means of two flexible AMCD's using noncontacting magnetic suspension is presented. The system consists of a flexible vehicle, two flexible rings and a magnetic suspension and driving assembly. The necessary skewing of the rings for maneuvering of the vehicle is accomplished by moving the pairs of magnets along tracks distributed around the circumference of the vehicle. The equations of motion for each subsystem are derived by the Lagrangian approach. Attitude motions are described in terms of quasi-coordinates. For small vehicle angular rates and rings attitude motions, an ordering scheme can be used to separate the equations of motion according to the magnitude of the terms. The ordered equations of motion lead to a linear time-variant optimal control problem for the maneuvering of the spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1669 , Astrodynamics Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 133
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    Control of a large flexible platform in orbit (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The dynamics and attitude and shape control of a large thin flexible platform in orbit are studied. Attitude and shape control is assumed to result from actuators placed perpendicular to the main surface and one edge and their effect on the rigid body and elastic modes is modelled to first order. The equations of motion are linearized about nominal orientations where the undeformed plate follows either the local vertical or local horizontal. The stability of the uncontrolled system is investigated analytically. Once controllability is established for a set of actuator locations, control law development is based on pole placement, decoupling, and linear optimal control theory.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1668 , Astrodynamics Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 134
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    Stabilization and control of the International Ultraviolet Explorer including a summary of flight performance (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The paper discusses the International Ultraviolet Explorer Mission sequence, spacecraft equipment, and control laws. Flight data from the precision control modes are presented, to illustrate the performance achieved; the subarc second pointing at sources for 60 min periods is accomplished routinely. Two modes of precision control are available: one is of a bright guide star which is in the vicinity of the target source, so that the guidance mode includes a star tracker for position information and a gyro system for rate damping. When a guide star is not available, precision hold is accomplished solely on a well trimmed gyro reference with low frequency updates from a dim source. The three axis maneuvers, the maneuver angle, and the gyro data used are discussed, concluding that these data used in conjunction with star tracker data provide a good source of information for orbital performance evaluation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Automatic control in space; Jul 02, 1979 - Jul 06, 1979; Oxford
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  • 135
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    Large space structures - Fantasies and facts (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A review of large space structures activities from 1973 to 1979 is presented. Long-range studies of space colonies, gigantic solar power stations and projected earth applications revived interest in space activities. Studies suggest opportunities for advanced antenna and platform applications. Matching low-thrust propulsion to large flexible vehicles will be a key technology. Current structures technology investigations include deployable and erectable structures and assembly techniques. Based on orbited structures experience, deployment reliability is a critical issue for deployable structures. For erectable structures, concepts for earth-fabricated and space-fabricated memb
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0674 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
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  • 136
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    Recovered transient load analysis for payload structural systems (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A recovered transient analysis technique is proposed wherein the results of a previous launch vehicle/payload system can be used to obtain the information on a new payload structure to be launched by an identical launch vehicle. The advantage of the proposed method is that the complete analysis can be performed within the payload organization with the same accuracy as that of a full scale, multiorganizational loads analysis. Also, the flight measured interface accelerations can be used as the forcing functions for more realistic representations of the dynamic environments.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0803 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
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  • 137
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    Design integration of aerocapture and aeromaneuver vehicles for a Mars sample return mission (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The concept of using an aerocapture vehicle for Mars and other planetary missions is a technology that yields significant fuel savings. This concept uses the planet's atmosphere to dissipate excess velocity of the entry vehicle allowing it to go into orbit. A conceptual design integration study of two configurations of aerocapture vehicles which can make an aerodynamically controlled entry has been made. The first configuration contains the existing Viking type Lander and an Orbiter. The second spacecraft is more general in payload and could be used to place an Orbiter and a Lander on other planets with a single aeroshell.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0728 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
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  • 138
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    Model error estimation for large space systems (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In-flight estimation of large structure model errors may have to be carried out in order to detect inevitable deficiencies in large structure controller/estimator models. These error estimates can most efficiently be obtained by the minimization of a quadratic functional of the model errors and on the subsequent analysis of the resulting optimal model error estimates. An integral operator approach to estimation leads to a geometrical interpretation of the model error estimation process. One of the significant insights gained with this interpretation is that the actual but unknown model errors can be decomposed as the sum of two distinct components that are orthogonal in some sense. One of these components is a so-called minimal error vector that retains many of the significant dynamics of the actual errors. The basic ideas in the model error estimation approach are first set forth with a two-dimensional analogy that has most of the essential features of the general estimation problem. The generalized results are then established and their application to a reference large structure model illustrated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Joint Automatic Control Conference; Aug 13, 1980 - Aug 15, 1980; San Francisco, CA
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  • 139
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    The control and estimation of large space structures (1980)
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    Publication Date: 2019-07-13
    Description: A shape control or estimation problem for a large space structure can be modeled by a partial differential equation which represents changes in shape with respect to space and time, together with spatially discrete forcing functions or observations which represent the placement of actuators or sensors at discrete points along the structure. The use of Green's functions to convert boundary value problems into integral equations provides a convenient treatment of this mixture of continuous and discrete mathematics. Control and estimation algorithms are developed for the one-dimensional static beam to illustrate this technique.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Joint Automatic Control Conference; Aug 13, 1980 - Aug 15, 1980; San Francisco, CA
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  • 140
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    Automating the process of estimating spacecraft mass (1980)
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    Publication Date: 2019-07-13
    Description: To help prevent the problem of mass reduction late in a spacecraft development program, the process of estimating spacecraft mass has been formulated in algorithmic form and incorporated in software that will allow trained users to interface with the integral design parameters data base interactively. The software will use historical data to extrapolate future values of a given time-dependent parameter and be manipulated by a dynamic graphics configuration builder. Future expansions of this work promise to automate the entire conceptual mission design process.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1382 , Annual Conference of the Society of Allied Weight Engineers; May 12, 1980 - May 14, 1980; St. Louis, MO
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  • 141
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    A case for Large Space Systems Technology (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The NASA Large Space Systems Technology (LSST) program, devoted to the development of Space Shuttle-deployable orbiting structures, is reviewed. The LSST program elements are: antennas, space platforms, assembly equipment and devices, surface sensors and control, control and stabilization, and analysis and design systems. Among the specific prospective applications for this technology base may be counted: multipurpose platforms, materials experimentation facilities, energy satellites, large optical and radio arrays, and communications platforms.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1372 , Annual Conference of the Society of Allied Weight Engineers; May 12, 1980 - May 14, 1980; St. Louis, MO
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  • 142
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    A technology development program for large space antennas (1980)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: The design and application of the offset wrap rib and the maypole (hoop/column) antenna configurations are described. The NASA mission model that generically categorizes the classes of user requirements, as well as the methods used to determine critical technologies and requirements are discussed. Performance estimates for the mesh deployable antenna selected for development are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81902 , IAF-80-A-33 , Intern. Astronautical Congr. of the Intern. Astronautical Federation,; Sep 21, 1980 - Sep 28, 1980; Tokyo; Japan
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  • 143
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    Nonlinear attitude dynamics of satellites (1980)
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    Publication Date: 2019-07-13
    Description: A study of predicting the rotational motion of a rigid body satellite orbiting the earth under the influence of external torques is presented. The attitude motion in response to external torques is formulated as a perturbation from a nominal torque-free case; the equations of motion are parameterized by the ratio of the orbital and attitude frequencies. The independent variable time is extended into a space of higher dimension by using new fast and slow scales. The theory is applied for predicting the attitude dynamics of an asymmetric rigid-body satellite.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: New approaches to nonlinear problems in dynamics; Dec 09, 1979 - Dec 14, 1979; Pacific Grove, CA
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  • 144
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    Large area flexible solar array design for Space Shuttle application (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A large area flexible solar array has been designed for Shuttle power augmentation. The solar array utilizes large area, low cost, weldable solar cells. The paper addresses how the unique requirements of this system are implemented into the design. Economic and reliability issues relating to the optimization of a large area, foldable solar array concomitant to the Shuttle/Orbiter system are reviewed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Energy to the 21st century; Aug 18, 1980 - Aug 22, 1980; Seattle, WA
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  • 145
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    Maneuver reconstruction techniques for open-loop spin-stabilized spacecraft (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Pioneer missions were supported by spin-stabilized spacecraft designs using open-loop control and blow-down propulsion subsystems. Reliable estimates of the ever-changing performance inherent to these subsystems were needed to effectively design and reconstruct trajectory correction maneuver (TCM) strategies. These performance updates were obtained by adjusting model parameters to match independent telemetric and radiometric observations to define the simultaneous changes in attitude, velocity, and spin rate during a maneuver sequence.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1699 , Astrodynamics Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 146
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    Subsonic stability and control flight test results of the Space Shuttle /tail cone off/ (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The subsonic stability and control testing of the Space Shuttle Orbiter in its two test flights in the tailcone-off configuration is discussed, and test results are presented. Flight test maneuvers were designed to maximize the quality and quantity of stability and control data in the minimal time allotted using the Space Shuttle Functional Simulator and the Modified Maximum Likelihood Estimator (MMLE) programs, and coefficients were determined from standard sensor data sets using the MMLE, despite problems encountered in timing due to the different measurement systems used. Results are included for lateral directional and longitudinal maneuvers as well as the Space Shuttle aerodynamic data base obtained using the results of wind tunnel tests. The flight test data are found to permit greater confidence in the data base since the differences found are well within control system capability. It is suggested that the areas of major differences, including lateral directional data with open speedbrake, roll due to rudder and normal force due to elevon, be investigated in any further subsonic flight testing. Improvements in sensor data and data handling techniques for future orbital test flights are indicated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1604 , Atmospheric Flight Mechanics Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 147
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    Passive nutation damping using large appendages with application to Galileo (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The use of large appendages for passive nutation damping is analyzed, and an analytical expression is developed to predict the nutation damping time constants for a large class of spacecraft including Galileo. It is shown that the use of large appendages for nutation damping can significantly degrade spacecraft stability margins and that the final design of the nutation damper must represent a tradeoff between the damping performance and the stability margin for sufficiently large appendages. The time constant derivation is outlined and the Galileo design is presented, including tradeoffs.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1783 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 148
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    Multipulse precession of spinning spacecraft with flexible appendages (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A multipulse precession scheme for spinners with large flexible appendages is described. By choosing the prescribed time delay between pulses as integer (or half integer) multiples of the several incommensurate modal periods it is possible to leave both central spinner and appendages in a final state of negligible nutation. Computer simulations illustrate the several schemes. The results indicate that the proposed method is relatively insensitive to parameter variations such as thruster and inertia uncertainties. Complete equations are presented, including a closed form solution for an important special case: the appendage plane contains the central body mass center.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1782 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 149
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    Minimum energy trap states of dual-spin spacecraft (1980)
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    Publication Date: 2019-07-13
    Description: The general solution to the bearing axis motor torque required to escape a minimum energy trap state is presented for oblate dual-spin spacecraft. A simplified, reduced order analysis of the bearing torque is then obtained for the case of small static imbalances, dynamic imbalances, and asymmetries on the rotor and the stator. This analysis is extended to include large asymmetry on one of the bodies. The results are applied to the design of the Galileo spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1780 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 150
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    ASPS performance with large payloads onboard the Shuttle Orbiter (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A high fidelity digital computer simulation was used to establish the viability of the Annular Suspension and Pointing System (ASPS) for satisfying the pointing and stability requirements of facility class payloads, such as the Solar Optical Telescope, when subjected to the Orbiter disturbance environment. The ASPS and its payload were subjected to disturbances resulting from crew motions in the Orbiter aft flight deck and VRCS thruster firings. Worst case pointing errors of 0.005 arc seconds were experienced under the disturbance environment simulated; this is well within the 0.08 arc seconds requirement specified by the payload.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1779 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 151
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    Spin-Down and Active Nutation Controller /SDANC/ for the Galileo project (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Spin-Down and Active Nutation Controller stabilizes the Galileo spacecraft during spin-down from approximately 70 to 1 rpm. Angular motion of the spacecraft is sensed through a pair of accelerometers and a sun sensor which is needed only at low spin rates. Spin and nutation information is derived by a set of 'loosely coupled' spin and transverse rate estimators. Spin rate is reduced by two spin-down thrusters. The transverse angular rate is compared with a variable threshold; exceeding the threshold activates axial thrusters which impart appropriate transverse torque to reduce the nutation. The scheme was verified by extensive computer simulations and has been demonstrated over a wide range of initial conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1734 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 152
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    Attitude determination of Galileo spacecraft from star data (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An entirely autonomous attitude determination algorithm has been developed for the dual spin Galileo spacecraft in its mission to Jupiter. A batch mode process is established which identifies three stars within the scanner's field-of-view based on the criteria of intensity and geometry. This is followed by a continuous star acquisition procedure which provides star transit times and a spacecraft spin rate estimate. A least-squares estimator then sequentially determines the spacecraft's attitude from successive star crossings by minimizing an error derived using the necessary condition of star and scanner slit normal orthogonality. Simulation results are presented, showing successful star identification and attitude convergence in the presence of nutation and star transit time uncertainty.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1732 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 153
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    Delta V errors due to attitude correction maneuvers of a spinning spacecraft (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A statistical error analysis has been performed to evaluate the change in velocity of a spin stabilized spacecraft due to thruster induced attitude correction maneuvers. Analytical expressions were developed to determine the mean and variance of the velocity in terms of the nominal values and uncertainties of key spacecraft parameters. These parameters include thrust, thruster timing, thruster alignment, plume impingement force and estimated spacecraft mass. Typical values of these parameters and their uncertainties for NASA's Galileo spacecraft were used to evaluate these expressions. The results of the analysis allow the effect of attitude correction maneuvers to be evaluated with respect to the functional requirements on nongravitational acceleration. Other results include the identification of major sources of delta V error and studies of the sensitivity of delta V to variations in the error sources.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1698 , Astrodynamics Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
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  • 154
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    Low thrust transfer of Large Space Systems (1980)
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    Publication Date: 2019-07-13
    Description: A study which defined an optimized low-thrust orbit transfer vehicle (OTV) is presented. The objectives of this NASA study were to (1) characterize missions which require or benefit from low-orbit transfer; (2) evaluate and compare candidate low-thrust liquid propulsion orbit transfer vehicle concepts; (3) determine propulsion/system characteristics which have the greatest influence on system suitability/capability; and (4) identify and describe propulsion technology requirements. A computerized optimization procedure was developed to determine the effect of thrust level and transients, number of burns, and payload structure material; a baseline hydrogen/oxygen low thrust OTV configured specifically for orbit transfer of large space systems was defined. Finally, the requirements for the engine for an optimized low thrust stage and the optimum vehicle for low acceleration missions were specified.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1265 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 155
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    Free convection in enclosures exposed to compressive heating (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An experimental study of heat transfer in a vertical annulus and a three-dimensional gap used to establish the influence of compressive heating on the convective process in enclosures is presented. Test runs were made using helium gas with compressive rates of 6, 15, and 30 psi/min. Temperature and pressure histories were reduced to film coefficients based on nodal modeling of the test geometries. The data are correlated in terms of free convection parameters. The heat transfer correlations show virtually no influence of compression rate and only a slight dependence on geometry. The correlations will be applied to the design of a vented Galileo mission descent module parachuting into the Jupiter atmosphere.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1536 , Thermophysics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 156
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    Thermophysical and system integration considerations in aerobraking design (1980)
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    Publication Date: 2019-07-13
    Description: The aerobraking concept for decelerating spacecraft into low-energy orbits is summarized. Data and comparisons are given for aerobraking approaches to Venus, Earth, Mars, and Titan. Calculations are based on adaption of a craft similar to the Venus Orbiting Imaging Radar vehicle to an aerobraking configuration. Special attention is given to integration of the aerobraking parts into the system and protection of the craft from heat loads due to the aerobraking maneuvers.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1492 , Thermophysics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 157
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    Comparison of quick-look plume heating calculations and Monte Carlo direct simulation (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A quick-look method has been developed for estimating convective heat flux due to plume impingement in the transition flow regime on a concave surface surrounding a rocket nozzle. Comparison with the flowfield and heat fluxes computed by the Monte Carlo Direct Simulation Method show the quick-look method to be conservative. Assumptions regarding the nature of the flowfield based on engineering judgment were shown to be essentially valid. Further, the assumption of free molecular impingement was shown to be non-conservative for portions of the surface. Potential refinements of the quick-look method are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1516 , Thermophysics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 158
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    Verification of the Space Shuttle ascent flight control (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The unique avionics design features of the Space Shuttle ascent flight control are described, along with the test article, test equipment, and test techniques used to verify the ascent flight control prior to commitment to the first orbital flight test. The ascent mission profiles are described, noting that upon ignition of the solid rocket boosters the Shuttle vehicle will rise vertically until achieving tower clearance. The Space Shuttle vehicle uses an integrated avionics system with the Orbiter avionics providing the command, control, and monitoring for the total mated Shuttle vehicle. The sensors and the actuator systems are discussed; the method of ascent flight control system verification is described, and it is concluded that the need for an advanced avionics integration and verification laboratory was recognized early in the program to provide maximum support to all program requirements.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Automatic control in space; Jul 02, 1979 - Jul 06, 1979; Oxford
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  • 159
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    Active damping of modal vibrations by force apportioning (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The theory and numerical simulation of active structural damping is described which requires few discrete control thrusters positioned on the structure. A particular apportioning of coherently phased control forces is applied for each vibration mode which is to be damped; this strongly affects the damped vibration mode, while minimally exciting all other modes. The force apportioning used is that which would tune a target mode if the structure was being shaken in a model vibration test. In contrast to model testing, the forces are varied temporally so as to dampen, rather than excite, the target mode(s).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0806 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
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  • 160
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    Design, fabrication and test of graphite/polyimide composite joints and attachments for advanced aerospace vehicles (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Bonded and bolted designs are presented for each of four major attachment types. Prepreg processing problems are discussed and quality control data are given for lots 2W4604, 2W4632 and 2W4643. Preliminary design allowables test results for tension tests and compression tests of laminates are included. The final small specimen test matrix is defined and the configuration of symmetric step-lap joint specimens are shown. Finite element modeling studies of a double lap joint were performed to evaluate the number of elements required through the adhesive thickness to assess effects of various joint parameters on stress distributions. Results of finite element analyses assessing the effect of an adhesive fillet on the stress distribution in a double lap joint are examined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-159111 , QTPR-4
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  • 161
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    Preliminary investigations into the active control of large space structures: Solution of the Timoshenko beam equations by the method of characteristics (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An algorithm was developed and incorporated into a computer program for solving the damped, Timoshenko beam equations with free-free boundary conditions and prescribed initial data. A number of special cases are considered and, where appropriate, comparisons are made with known results.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-163408
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  • 162
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    Discussion meeting on Gossamer spacecraft (ultralightweight spacecraft) (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Concepts, technology, and application of ultralightweight structures in space are examined. Gossamer spacecraft represented a generic class of space vehicles or structures characterized by a low mass per unit area (approximately 50g/m2). Gossamer concepts include the solar sail, the space tether, and various two and three dimensional large lightweight structures that were deployed or assembled in space. The Gossamer Spacecraft had a high potential for use as a transportation device (solar sail), as a science instrument (reflecting or occulting antenna), or as a large structural component for an enclosure, manned platform, or other human habitats. Inflatable structures were one possible building element for large ultralightweight structures in space.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-163275 , JPL-PUB-80-26 , Dec 19, 1979 - Dec 20, 1979; Pasadena, CA; United States
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  • 163
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    Accuracy potentials for large space antenna structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The relationships among materials selection, truss design, and manufacturing techniques in the interest of surface accuracies for large space antennas are discussed. Among the antenna configurations considered are: tetrahedral truss, pretensioned truss, and geodesic dome and radial rib structures. Comparisons are made of the accuracy achievable by truss and dome structure types for a wide variety of diameters, focal lengths, and wavelength of radiated signal, taking into account such deforming influences as solar heating-caused thermal transients and thermal gradients.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1375 , Annual Conference of the Society of Allied Weight Engineers; May 12, 1980 - May 14, 1980; St. Louis, MO
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  • 164
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    Modular space structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Extendable Tetrahedral Truss orbiting antenna concept, comprising the use of prefabricated, automatically deployable lattice structures and their subsequent assembly into larger structures suitable for microwave antenna use, is described. It is assumed that the Space Shuttle Orbiter payload bay will be able to accommodate only modular portions of the structural system required, and that the Space Shuttle crew will furnish the manual labor entailed by orbital assembly. It is concluded that a deployable beam module system may be a more elegant design solution than the alternative triangular-module system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1371 , Annual Conference of the Society of Allied Weight Engineers; May 12, 1980 - May 14, 1980; St. Louis, MO
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  • 165
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    Closed loop performance of a brushless dc motor powered electromechanical actuator for flight control applications (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A comprehensive digital model for the analysis and possible optimization of the closed loop dynamic (instantaneous) performance of a power conditioner fed, brushless dc motor powered, electromechanical actuator system (EMA) is presented. This model was developed for the simulation of the dynamic performance of an actual prototype EMA built for NASA-JSC as a possible alternative to hydraulic actuators for consideration in Space Shuttle Orbiter applications. Excellent correlation was achieved between numerical model simulation and experimental test results obtained from the actual hardware. These results include: various current and voltage waveforms in the machine-power conditioner (MPC) unit, flap position as well as other control loop variables in response to step commands of change of flap position. These results with consequent conclusions are detailed in the paper.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NAECON 1980; National Aerospace and Electronics Conference; May 20, 1980 - May 22, 1980; Dayton, OH
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  • 166
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    Pointing control for the International Comet Mission (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The design of the pointing control system for the proposed International Comet Mission, intended to fly by Comet Halley and rendezvous with Comet Tempel-2 is presented. Following a review of mission objectives and the spacecraft configuration, design constraints on the pointing control system controlling the two-axis gimballed scan platform supporting the science instruments are discussed in relation to the scientific requirements of the mission. The primary design options considered for the pointing control system design for the baseline spacecraft are summarized, and the design selected, which employs a target-referenced, inertially stabilized control system, is described in detail. The four basic modes of operation of the pointing control subsystem (target acquisition, inertial hold, target track and slew) are discussed as they relate to operations at Halley and Tempel-2. It is pointed that the pointing control system design represents a significant advance in the state of the art of pointing controls for planetary missions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-021 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 167
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    Attitude and articulation control solutions for Project Galileo (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Design problems and the solutions adopted for them in the attitude and articulation control subsystem for the Galileo spacecraft are discussed as an illustration of the application of dual-spin control to an interplanetary spacecraft. Following a review of the baseline design of the Galileo system and mission, consideration is given to problems encountered in the areas of autonomous attitude determination, attitude control, spacecraft dynamics and software margins. Design issues raised by subsequent changes in spacecraft configuration are also indicated. It is pointed out that although difficulties associated with control system complexity in a dual-spin interplanetary spacecraft have been satisfactorily resolved for the Galileo mission, the future application of dual spin in interplanetary flight is in doubt.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-019 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 168
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    Attitude control fault protection - The Voyager experience (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The length of the Voyager mission and the communication delay caused by the distances involved made fault protection a necessary part of the Voyager Attitude and Articulation Control Subsystem (AACS) design. An overview of the Voyager attitude control fault protection is given and flight experiences relating to fault protection are provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-018 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 169
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    Planetary spacecraft pointing and control - The next 20 years (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Pointing and control systems recommended for NASA planetary exploration missions of the next twenty years are discussed. The functional and operational requirements and design constraints imposed on the driving control system by the mission and science goals of the spacecraft are examined. Criteria for the selection of a pointing and control system type (spin, dual-spin, three-axis active or momentum bias) are outlined, including payload functional characteristics, orbital characteristics, vehicle configuration and mission duration, and candidate system types proposed for preliminary survey, detailed remote observation, deep space close scrutiny, near-sun close scrutiny and sample return missions are indicated. Trends in control system design are discussed, and key enabling technology areas that will require additional or new development are considered, with particular emphasis on laser and fiber optics gyros, CCD arrays and DMA signal/power transmission, bearings and motor technologies, directed at three-axis active and dual-spin implementations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-017 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 170
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    Pointing and control for planetary spacecraft - The first twenty years (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The evolution of guidance and control systems for United States planetary and unmanned lunar spacecraft over the last 20 years is traced. The characteristics of the guidance and control systems used on spacecraft from the Range lunar impactor to the planned Galileo Jupiter orbiter and entry probe are surveyed, with attention given to the uses of three-axis stabilized, spin-stabilized and dual-spin designs. System performance trends that have evolved to meet the increasing science and mission requirements of the spacecraft are considered in the areas of attitude references, control consumables, dynamics and system modeling, thrust vector control, optical navigation, manuever turns, maneuver velocity control, instrument pointing, and antenna pointing. Hardware trends in optical sensors, inertial sensors, processing electronics, electromechanical devices, and system testing and reliability are also reviewed. The achievements represented by these advances are emphasized, and it is predicted that future developments will be in the areas of increased control system autonomy and performance requirements.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-016 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 171
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    Attitude control challenges for earth orbiters of the 1980's (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Experience gained in designing attitude control systems for orbiting spacecraft of the late 1980's is related. Implications for satellite attitude control design of the guidance capabilities, rendezvous and recovery requirements, use of multiple-use spacecraft and the development of large spacecraft associated with the advent of the Space Shuttle are considered. Attention is then given to satellite attitude control requirements posed by the Tracking and Data Relay Satellite System, the Global Positioning System, the NASA End-to-End Data System, and Shuttle-associated subsatellites. The anticipated completion and launch of the Space Telescope, which will provide one of the first experiences with the new generation of attitude control, is also pointed out.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-006 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 172
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    Torque equilibrium attitude control for Skylab reentry (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The method of torque equilibrium attitude control used to control the reentry of Skylab to an altitude below 150 km without the use of thruster fuel once the attitude was established is discussed. The Skylab attitude and pointing control system, which included rate gyros, sun sensors, star tracker, the Apollo telescope mount digital computer, control moment gyros and cold-gas attitude thrusters, is presented. The 12 torque equilibrium attitudes found at which aerodynamic, gravity gradient and gyroscopic torques would balance are indicated, and the three of those at which the solar power supply would be adequate for attitude control are illustrated. The equilibrium seeking method employed is then examined, and the operation and performance of the torque equilibrium attitude control system during the three weeks prior to Skylab reentry are discussed. It is concluded that the torque equilibrium attitude control method developed for Skylab was successful in performing its assigned mission, and will be valuable for the design of future, low-altitude spacecraft or tethered vehicles.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-005 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
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  • 173
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    A liquid hydrogen experiment as a Shuttle payload (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The paper describes the cryogenic fluid management experiment (CFME) as a Shuttle payload. The experiment includes a liquid hydrogen tank containing a fine-mesh screen acquisition device, and a thermal control system consisting of a thermodynamic vent system to intercept heat leak to the hydrogen tank and control tank pressure. Engineering data obtained will be used to establish design criteria for subcritical cryogenic storage and supply tankage.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1096 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 174
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    Space radiator trade studies for the 25 kW Power System (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Advanced radiator designs which will survive the meteoroid hazard of near earth orbit for five years are evaluated for the 25 kW Power System. Weight comparisons of heat pipe radiators and pumped fluid radiators incorporating meteoroid bumpers are presented for the initial 25 kW Power System and growth versions to 250 kW. The heat pipe concept is enhanced by a new design of the thermal interface between the heat pipe and coolant loop. The results show small weight differences between the advanced heat pipe and pumped fluid concepts for heat loads up to about 50 kW. The heat pipe panels have a weight advantage for larger heat loads.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME PAPER 80-ENAS-27 , Intersociety Environmental Systems Conference; Jul 14, 1980 - Jul 17, 1980; San Diego, CA
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  • 175
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    NASCAP modelling computations on large optics spacecraft in geosynchronous substorm environments (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Satellites in geosynchronous orbits have been found to be charged to significant negative voltages during encounters with geomagnetic substorms. When satellite surfaces are charged, there is a probability of enhanced contamination from charged particles attracted back to the satellite by electrostatic forces. This could be particularly disturbing to large satellites using sensitive optical systems. In this study the NASA Charging Analyzer Program (NASCAP) is used to evaluate qualitatively the possibility of such enhanced contamination on a conceptual version of a large satellite. The evaluation is made by computing surface voltages on the satellite due to encounters with substorm environments and then computing charged-particle trajectories in the electric fields around the satellite. Particular attention is paid to the possibility of contaminants reaching a mirror surface inside a dielectric tube because this mirror represents a shielded optical surface in the satellite model used. Deposition of low energy charged particles from other parts of the spacecraft onto the mirror was found to be possible in the assumed moderate substorm environment condition. In the assumed severe substorm environment condition, however, voltage build up on the inside and edges of the dielectric tube in which the mirror is located prevents contaminants from reaching the mirror surface.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Los Angeles Technical Symposium; Feb 04, 1980 - Feb 07, 1980; North Hollywood, CA
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  • 176
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    SKB Iskra (1980)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The design and construction of small size man made Earth satellites for scientific research and scholarly purposes is reviewed. All stages of the work organization, from design to launching of a satellite, are covered.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Without Tables of Ranks and the Iskra Student Design Bureau (NASA-TM-76277); p 13-16
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  • 177
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    Spacecraft for flight in the atmosphere of Venus (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Possible configurations of space vehicles which would be delivered to Venus by rocket system in order to autonomously carry out flights in an automatic (and possibly piloted) mode are considered with respect to mission and flight altitude. Base (high altitude) vehicles, operating at pressure, sendity, and temperature corresponding to those on Earth at sea level, will have little maneuverability, will serve as carriers for equipment, scientific devices, and other cargo, and will study the gas composition of the Venus atmosphere from above. Low altitude vehicles will explore the planet from flight altitude in the vicinity of the planet's surface, as well as land on it. Analogous to deep submergence vehicles such as the bathyscaphe and the bathyplane, they will have a certain amount of maneuverability and will study the atmospheric boundary layer from below. The advantages of aerostats in this environment are discussed. Drawings of the aerostatic base station, the variable-length aerostatic sing vehicle, and the hybrid aerostatic vehicle with attached wings are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-75932
    Format: application/pdf
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