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  • Other Sources  (167)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (167)
  • 1980-1984  (167)
  • 1945-1949
  • 1925-1929
  • 1980  (167)
  • 1
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    Performance of entry heat shields on Pioneer Venus probes (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The Pioneer Venus probes approached Venus with high relative velocity. As they entered the atmosphere, they were rapidly decelerated by aerodynamic drag, and a great deal of heat was generated. To protect the probe structure and the scientific instruments, a carbon phenolic heat shield was placed on the front of the probes. Because the design of heat shields for planetary entry is a developing technology, thermocouples were placed in the heat shields so that actual and predicted heat shield performance could be compared. The function of the heat shield is discussed, the probe environments during entry into the Venusian atmosphere are described, and some results from the heat shield experiment are presented. It was found that for the most part, the heat shields performed better than expected.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Geophysical Research; 85; Dec. 30
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  • 2
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    Modelling of environmentally induced discharges in geosynchronous satellites (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The NASCAP computer code is 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 is found to be substantially less than that required to produce discharges in ground simulation studies. A discharge process is postulated involving discharges triggered at edges (or imperfection) followed by discharges to space. The characteristics of such discharges are parametrically varied to evaluate the possible effects on the satellite. It has been found that discharge characteristics inferred from satellite monitors could be caused by predicted space discharges, that single cell discharges to space can reduce surface potential over entire satellite, and that low-density electron trajectory computations indicate that discharge generated electrons may not return to the satellite by long trajectories. Current transients predicted do not agree with the 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
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  • 3
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    Rockets and spacecraft: Sine qua non of space science (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The evolution of the national launch vehicle stable is presented along with lists of launch vehicles used in NASA programs. A partial list of spacecraft used throughout the world is also given. Scientific spacecraft costs are presented along with an historial overview of project development and funding in NASA.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Beyond the Atmosphere: Early Years of Space Sci.; p 133-170
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  • 4
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    Modal damping enhancement in large space structures using AMCD's (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The use of an annular momentum control device (AMCD) is proposed for enhancing the modal damping of large space structures (LSS's) during fine pointing missions. Theoretical and experimental studies proved that an AMCD cannot destabilize the LSS and that the system is asymptotically stable under certain conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance and Control; 3; Sept
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  • 5
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    Space environmental interactions with biased spacecraft surfaces (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Large, high-voltage space power systems are being proposed for future space missions. These systems must operate in the charged-particle environment of space, and interactions between this environment and the high-voltage surfaces are possible. Ground simulation testing has indicated that dielectric surfaces that usually surround biased conductors can influence these interactions. For positive voltages greater than 100 V, it has been found that the dielectrics contribute to discharges. Using these experimental results a large, high-voltage power system operating in geosynchronous orbit was analyzed with the NASCAP code. Results of this analysis indicated that very strong electric fields exist in these power systems. A technology investigation is required to understand the interactions and develop techniques to alleviate any impact on power system performance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 6
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    The Cosmic Background Explorer Satellite (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The Cosmic Background Explorer (COBE) satellite, planned for launch in 1985, will measure the diffuse infrared and microwave radiation of the universe over the entire wavelength range from a few microns to 1.3 cm. It will include three instruments: a set of microwave isotropy radiometers at 23, 31, 53, and 90 GHz, an interferometer spectrometer from 1 to 100/cm, and a filter photometer from 1 to 300 microns. The COBE satellite is designed to reach the sensitivity limits set by foreground sources such as the interstellar and interplanetary dust, starlight, and galactic synchrotron radiation, so that a diffuse residual radiation may be interpreted unambiguously as extragalactic
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 7
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    Optimal member damper controller design for large space structures (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Consideration is given to the selection of velocity feedback gains for individual dampers for the members of a structurally controlled large flexible space structure. The problem is formulated as an optimal output feedback regulator problem, and necessary conditions are derived for minimizing a quadratic performance function. The diagonal nature of the gain matrix is taken into account, along with knowledge of noise covariances. It is pointed out that the method presented offers a systematic approach to the design of a class of controllers for enhancing structural damping, which have significant potential if used in conjunction with a reduced-order optimal controller for rigid-body modes and selected structural modes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance and Control; 3; July-Aug
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  • 8
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    Active Control of Spacecraft Charging (1980)
    In:  Other Sources
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    Publication Date: 2012-04-19
    Description: The concept of active control of spacecraft charging by charged particle emission is described. Active potential control experiments using the ATS-5 and ATS-6 geostationary spacecraft are discussed, and results of these experiments are presented. Previously reported results are summarized, and a guide to reports on these data are provided. Experimental evidence presented indicates that emission of electrons only is not effective in maintaining spacecraft potential near plasma potential for spacecraft with electrically insulating surfaces. Emission of a low energy plasma, however, is effective for this purpose.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 9
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    POLAR 5 - An electron accelerator experiment within an aurora. III - Evidence for significant spacecraft charging by an electron accelerator at ionospheric altitudes (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The POLAR 5 rocket experiment carried an electron accelerator on a 'daughter' payload which injected a 0.1 A beam of 10 keV electrons in a pulsed mode every 410 ms. With spin and precession, injections were made over a wide range of pitch angles. Measurements from a double probe electric field instrument and from particle detectors on the 'mother' payload and from a crude RPA on the 'daughter' payload are interpreted to indicate that the 'daughter' charges to a potential between several hundred volts and 1 kV. The neutralizing return current to the 'daughter' is shown to be asymmetrically distributed with the majority being collected from the direction of the beam. The additional electrons necessary to neutralize the daughter are thought to be produced and heated through beam-plasma interactions postulated by Maehlum et al. (1980) and Grandal et al. (1980) to explain the particle and optical measurements. Significant electric fields emanating from the charged 'daughter' and the beam are seen at distances exceeding 100 m at the 'mother' payload.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Planetary and Space Science; 28; Mar. 198
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  • 10
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    The Infrared Astronomical Satellite - IRAS (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The Infrared Astronomical Satellite (IRAS), to be launched in the autumn of 1981, is expected to reveal much that is new and exciting. The paper discusses the design features and performance of IRAS, illustrates the meaning of this performance in terms of known phenomena, and stipulates how it may extrapolate to the early universe. The ability of IRAS to observe the universe at large redshift is examined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 11
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    Electromagnetic fields produced by simulated spacecraft discharges (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The initial phase of a broader, more complete program for the characterization of electrical breakdowns on spacecraft insulating materials is described which consisted of the development of a discharge simulator and characterization facility and the performance of a limited number of discharge measurements to verify the operation of the laboratory setup and to provide preliminary discharge transient field data. A preliminary model of the electromagnetic characteristics of the discharge was developed. It is based upon the "blow off" current model of discharges, with the underlying assumption of a propagating discharge. The laboratory test facility and discharge characterization instrumentation are discussed and the general results of the "quick look" tests are described on quartz solar reflectors aluminized Kapton and silver coated Teflon are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 894-911
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  • 12
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    Model of coupling discharges into spacecraft structures (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The calculated results of a semiempirical model for electron-caused electromagnetic pulse (ECEMP) are compared to the experimental data for three spacecraft geometries. The appropriateness of certain model assumptions which have been employed in the absence of a microscopic theory for dielectric breakdown and associated electron blowoff is discussed. Results are limited to the exterior response of spacecraft structures, although neither the model nor the experiments were limited to the outside problem. Rationales for model assumptions are provided.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 745-754
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  • 13
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    P78-2 satellite and payload responses to electron beam operations on March 30, 1979 (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The operating modes of the SC4-1 payload, the resultant charging of the spacecraft frame and sample materials on the spacecraft exterior and recorded transient pulses are reported. Arcing was detected by pulse monitors in several electron beam modes of operation. The ejection of a beam of 6 mA of 3 keV electrons caused three distinct payload failures and created a transient problem in the telemetry system. The exact time, nature, and cause of these failures was determined and component failure and why they failed was identified. Analytical and modeling techniques are used to examine possible spacecraft and payload responses to the electron beam ejection which might have contributed to the arcing and payload failures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 509-559
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  • 14
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    Preliminary analysis of data from SRI international transient pulse monitor on board P78-2 SCATHA satellite (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The satellite charging at high altitudes (SCATHA) program addresses the occurrence of electrostatic discharges causing undesirable effects like deleterious transients in electronic circuits on satellites. The high altitude plasma environment and the effects of the interaction of this environment with the orbiting satellite are studied. The SRI transient pulse monitor (TPM) detects the transient electromagnetic signals induced in selected circuits. As a transient detector the TPM records transient signals, indicates the number of transients observed, and gives peak amplitude of the largest transient during each second's interval. Most of the early data from the TPM contain pulses associated with internal electrical activity and electrostatic charging on the surface of the P78-2 is evidenced. It is found that periods of external discharging do not necessarily coincide with periods in which high potentials are measured on the satellite's surface.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 470-477
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  • 15
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    Review of hot plasma composition near geosynchronous altitude (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The information available on the hot plasma composition at and near the geostationary satellite orbit has increased dramatically during the past four years. At energies below 32 keV, ions of terrestrial origin, 0(+) and He(+) are frequently observed to be significant contributors to the hot plasma density and energy density, and during geomagnetically disturbed periods, 0(+) ions are typically the dominant hot plasma ions. Evidence for a solar cycle dependence to the 0(+) hot plasma densities at the geostationary orbit has been found. Our understanding of the details of the physical processes involved in the entry, acceleration, transport, and loss of the plasma ions, and thus our ability to model them, is still quite limited.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 412-432
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  • 16
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    Effectiveness of spacecraft testing programs (1980)
    In:  CASI
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    Publication Date: 2016-06-07
    Description: The need for testing under simulated mission operational conditions is discussed and the results of such tests are reviewed from the point of view of the user. A brief overview of the usal test sequences for high reliability long life spacecraft is presented and the effectiveness of the testing program is analyzed in terms of the defects which are discovered by such tests. The need for automation, innovative mechanical test procedures, and design for testability is discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: The 11th Space Simulation Conf.; p 13-23
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  • 17
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    Importance of differential charging for controlling both natural and induced vehicle potentials on ATS-5 and ATS-6 (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Three techniques of discharging satellites used on the P78-2 satellite were the ejection of a beam of electrons from an electron gun; the emission of electrons from a heated, biased filament; and the ejection of a plasma containing energetic positive xenon ions and low energy electrons. When the P78-2 satellite ground to plasma potential difference reached several hundred volts, each of the three techniques was able to completely discharge the satellite. The comparative effctiveness of the techniques were clearly shown. Two days later, the satellite charged to -8 keV upon entering eclipse. The electron gun, emitting 1 mA of electrons with 150 eV energy, reduced the difference in potential between satellite ground and the ambient plasma to -1 kV, but could not completely discharge the satellite. The plasma source completely discharged the satellite.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 888-893
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  • 18
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    Simulation of spacecraft charging environments by monoenergetic beams (1980)
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    Publication Date: 2016-06-07
    Description: To simulate the distributed spectra of plasmas in space, the differential current density spectrum of the plasma was divided into a number of energy bands and the beam energy and current were calculated for each band to provide a piecewise reproduction of the distributed spectrum. Beam energies and current densities were chosen to match the velocity moments of the plasma distribution function. The velocity moments are averages related to physical quantities such as particle density, flux, pressure, and energy flux, and have been used extensively to characterize the measured properties of plasmas in space. Combinations of one, two, and three beams were found to match two to six velocity moments of Maxwellian distributions. A computational model was used to compare the charging of a spacecraft by plasmas with distributed spectra and by monoenergetic beams.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 866-886
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  • 19
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    Spacecraft charging technology in the satellite X-ray test facility (1980)
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    Publication Date: 2016-06-07
    Description: A satellite X-ray test facility (SXTF) is planned for studying system generated electromagnetic pulse effects on full scale, operational spacecraft. The environment created by a distant, high altitude nuclear burst can be simulated using pulsed X-ray sources. The facility is to be installed in a thermal vacuum chamber with dimensions greater then 10 m diameter and 20 m height and equipped with solar simulators and equipment for simulating the charging environment of space. The spacecraft charging system consists of several low energy electron and hydrogen ion sources (5-25 keV), one or two medium energy electron accelerators (150-300 keV), an array of vacuum ultraviolet lamps, and geomagnetic field suppression coils. Military, scientific, and commercial spacecraft can be tested before launching into the radiation environment of space. construction of SXTF is scheduled to begin in 1982 and the facility should be available for general use in 1984. Potential users are encouraged to express their needs for specific testing environments in SXTF.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 856-865
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  • 20
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    Meteosat spacecraft charging investigation (1980)
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    Publication Date: 2016-06-07
    Description: A number of phenomena observed on the first orbiting Meteosat satellite attributed to spacecraft charging effects are considered. Design analysis, correlation of anomalies with space environmental data, on ground tests with an engineering model spacecraft, tests on the validity of improvements, and installation of suitable monitors for the second improved flight satellite are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 814-834
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  • 21
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    Electron irradiation tests on European meteorological satellite (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The observation of in orbit anomalies on Meteosat resulted in a test being performed to establish the charging and discharging characteristics of a flight configured engineering model when irradiated with electrons. Surface potentials were measured together with discharge rates and amplitudes. Results indicate that a large number of discharges are possible on the satellite whether or not the external surfaces are grounded. Initial measurements show that there are very high potential gradients around the satellite which obviously contribute largely to the discharging behavior. The time constant for charging is very small, indicating also that equilibrium conditions are achieved very quickly as the local ambient changes in orbit. A.R.H.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 835-855
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  • 22
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    P78-2 SCATHA environmental data atlas (1980)
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    Publication Date: 2016-06-07
    Description: The 100 eV to approximately 1 MeV plasma environment encountered by the P78-2 Spacecraft Charging at High Altitudes (SCATHA) satellite during its initial operation period was studied. Forty-four days of 10 minute averages of the four moments of the electron and ion distribution functions calculated from the SC5 and SC9 energetic particle measurements were analyzed to determine occurrence frequency, local time variation, geomagnetic activity variation, and L shell variation. The single and double Maxwellian parameters derived from the four moments were similarly analyzed. The interrelationships between the moments and derived parameters were computed and the results compared with the ATS-5 and ATS-6 atlas. Results of this analysis establish a baseline range for the SCATHA plasma environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 802-813
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  • 23
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    Military standards and SCATHA program update of MIL-STD-1541 (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The elctromagnetic compatability requirements for space systems, 15 October 1973, to be met by industry contractors for spacecraft launch vehicles and other special space systems, are considered. Deficiencies in the existing standard with respect to spacecraft charge and discharge phenomena, the technical ramifications for generating a new standard, and the upgrading of MIL-STD-1541 with requirements supplied as a result of the SCATHA program are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 768-788
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  • 24
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    Analytical modeling of satellites in geosynchronous environment (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Experiences with surface charging of geosynchronous satellites are reviewed and mechanisms leading to discharges on satellite surfaces are considered. It was found that the large differential voltages between the surface and the substrate required to produce massive laboratory discharges do not occur on satellites in space. Analytical modeling predictions supported by dielectric charging data from P78-2, SCATHA (Spacecraft Charging at High Altitudes) flight results are discussed. Ungrounded insulator areas, buried charge layers (due to mid-energy range particles), and positive differential voltages (where structure voltages are less negative than surrounding dielectric surface voltages) are considered as possible mechanisms producing satellite charge up.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Space Charging Technol., 1980; p 717-729
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  • 25
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    NASCAP charging calculations for a synchronous orbit satellite (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The use of the NASA Charging Analyzer Program (NASCAP) for the computation of spacecraft charge up in the energetic plasma environment of geosynchronous orbits is described. Spacecraft modelling, materials parameters, and NASCAP charging analyses are described. The synchronous orbit plasma environment used in the stress analysis employs a two Maxwellian energy distribution to determine the fluxes. Several NASCAP runs performed to determine the location and magnitude of environmentally induced voltage stresses are analyzed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 684-708
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  • 26
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    Dielectric discharge characteristics in a two-electron simulation environment (1980)
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    Publication Date: 2016-06-07
    Description: The results of a series of experiments in which flux levels representative of the space electron environment were used are presented and compared to the results of high flux tests. The simulation approach was to partition the space electron spectrum into two parts, those electrons which do not penetrate a material and therefore contribute to charging and those which completely penetrate the material. The nonpenetrating electrons were simulated using 25 keV electrons and the penetrating electrons by 350 keV electrons. The materials included in this investigation were Kapton, optical solar reflectors (OSRs), and a ground test satellite surface potential monitor which contained Kapton, astroquart, OSRs and teflon.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 4-16
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  • 27
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    Comparison of NASCAP modelling results with lumped circuit analysis (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Engineering design tools that can be used to predict the development of absolute and differential potentials by realistic spacecraft under geomagnetic substorm conditions are described. Two types of analyses are in use: (1) the NASCAP code, which computes quasistatic charging of geometrically complex objects with multiple surface materials in three dimensions; (2) lumped element equivalent circuit models that are used for analyses of particular spacecraft. The equivalent circuit models require very little computation time, however, they cannot account for effects, such as the formation of potential barriers, that are inherently multidimensional. Steady state potentials of structure and insulation are compared with those resulting from the equivalent circuit model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Spacecraft Charging Technol., 1980; p 665-683
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  • 28
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    Analysis of ambient and beam particle characteristics during the ejection of an electron beam from a satellite in near-geosynchronous orbit on March 30, 1979 (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: An electron beam system was operated over a wide range of beam currents and energies for periods both in sunlight and in eclipse. Complex pitch angle modulations of the electron spectra are separately decomposed for each beam operation. When electrons are emitted perpendicular to the magnetic field with an energy of 3 keV and a current of 0.10 mA they return as a coherent beam only to the parallel detector. Throughout the beam operations the pitch angle distributions show electrons with energy less than beam energy streaming along the field line. Analytic expressions for the satellite electric field are constructed and particle trajectories are determined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 642-664
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  • 29
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    Computer simulation of spacecraft charging on SCATHA (1980)
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    Publication Date: 2016-06-07
    Description: Computer simulation to determine spacecraft charging on P78-2 (SCATHA) during a substorm and for modeling the effects of electron beam emission on the P78-2 ground potential for a variety of beam voltages and currents was used. Measured and computed spacecraft potentials are obtained to within several hundred eV. Computation of the electron beam emission effects on the spacecraft ground potential are shown. It is concluded that the spacecraft ground potential can be controlled by emitting an electron beam.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 632-641
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  • 30
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    SCATHA SSPM charging response: NASCAP predictions compared with data (1980)
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    Publication Date: 2016-06-07
    Description: Models for the satellite surface potential monitor (SSPM) units constructed in the NASCAP code and the results of comparing predictions to surface voltage and baseplate current data are reported. Several peculiarities in the test data are noted. Preliminary results from space simulations of a SCATHA model with environments representative of the day 87, 1979, eclipse injection event are presented, and their implications for predicting space response are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Spacecraft Charging Technol., 1980; p 592-607
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  • 31
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    Three-dimensional analysis of charging events on days 87 and 114, 1979, from SCATHA (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Angular distributions of ions and electrons from the Spacecraft Charging at High Altitudes (SCATHA) were investigated for the floating potential and the differential charging of the spacecraft as deduced from Liouville's theorem. The following was found: (1) short time charging events on the spacecraft are associated with short time increases of the intensity of 10 keV to 1 MeV electrons; (2) short time changes of the spacecraft differential potential are associated with simultaneous short time changes of the spacecraft floating potential; (3) solar UV intensities in penumbra anticorrelate with the spacecraft floating potentials; (4) NASCAP predicts correct forms of sunshade asymmetric surface potentials; (5) certain enhancements of the intensity of energetic ions diminishes the absolute value of the spacecraft surface potential; (6) spacecraft discharging events in times shorter than 20 sec did not change in the spectrum of the energetic plasma; (7) partial discharging of the spacecraft occurred upon entry into a magnetically depleted region; and (8) steady state potentials and transient potentials of duration less than 30 seconds are simulated by the NASCAP code.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Tecnol., 1980; p 608-631
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    Agreement for NASA/OAST - USAF/AFSC space interdependency on spacecraft environment interaction (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: A joint AF/NASA comprehensive program on spacecraft environment interactions consists of combined contractual and in house efforts aimed at understanding spacecraft environment ineraction phenomena and relating ground test results to space conditions. Activities include: (1) a concerted effort to identify project related environmental interactions; (2) a materials investigation to measure the basic properties of materials and develop or modify materials as needed; and (3) a ground simulation investigation to evaluate basic plasma interaction phenomena and provide inputs to the analytical modeling investigation. Systems performance is evaluated by both ground tests and analysis. There is an environmental impact investigation to determine the effect of future large spacecraft on the charged particle environment. Space flight investigations are planned to verify the results. The products of this program are test standards and design guidelines which summarize the technology, specify test criteria, and provide techniques to minimize or eliminate system interactions with the charged particle environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Spacecraft Charging Technol., 1980; p 912-930
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    Use of charging control guidelines for geosynchronous satellite design studies (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Several of the principle guidelines from the Spacecraft Charging Design Guidelines Handbook are presented with illustrative examples. Use of the geomagnetic substorm specification to qualify satellite designs, the evaluation of satellite designs by using analytical modelling techniques, the use of selected materials and coatings to minimize charging, the tying of all conducting elements to a common ground, and the use of electrical filtering to protect circuits from discharge induced upsets are discussed. Discharge criteria and SCATHA data are excluded.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Spacecraft Charging Technol., 1980; p 789-801
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    Operational status of the space test program P78-2 spacecraft and payloads (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Operations of the P78-2 spacecraft and its 12 payloads, which attempt to measure the buildup and breakdown of charge on various spacecraft components and to characterize the natural environment at synchronous altitudes, are summarized. Launch procedures, orbit alignment, and eclipse seasons are reviewed. The spacecraft configuration and subsystems are described. Catastrophic payload failures are reported: the SC6 (AFGL Thermal Plasma Analyzer) failed due to an excessive power draw in the electron step generator. The SC7 (NASA/MSFC Light Ion Mass Spectrometer) internal power supply failed. Lesser payload failures, including SC2 probe biasing, SC4-1 pulsed mode, and SC4-2 neutralizer are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 365-369
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  • 35
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    Accelerated Alpha-s deterioration in a geostationary orbit (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Between the Teflon substrate and the interference filter a 2 micron varnish layer was sandwiched in. The bending radius of the SSM, measured on a cone, decreased from about 13 mm to 6 mm prior to interference filter fracture, due to increased tensile strength of its substrate. These samples, and for comparison samples of the same make but without varnish and a conductive layer were included in the test. Additionally 2 Teflon FEP samples without the protective interference filter, one of them with a conductive layer, were tested. The sample substrate was 125 micron Teflon FEP, with vapor deposited silver reflector and a thin Inconel film for corrosion protection.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 353-364
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  • 36
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    Conduction through punctures in metal-backed dielectrics (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: A theoretical mechanism to explain the main features of experiments with punctured spacecraft-thermal-blanket materials is presented. The model is based on consideration of the electric fields developed about punctures; the focusing of primary electrons toward the punctures; the generation, migration, and cascade of secondary electrons along the surface; and the radiation induced conductivity characteristics of thin dielectric films. Qualitative predictions of the model agree with experiment results
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: in NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 342-352
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  • 37
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    Evaluation of charge control techniques on spacecraft thermal surfaces (electrostatic discharge study) (1980)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The charging and discharging characteristics of various dielectric materials commonly used on spacecraft were tested. The experimental apparatus and the calculations used to analyze the data generated during the testing are described. The test technique, results, and analysis used are presented. Indium tin oxide coated Teflon, Kapton, and quartz do not charge significantly. CTL 15 white paint shows no large charge build up. Pinholes in Teflon and Kapton increase the leakage through the sample and reduce the energy released in an arc. Conductive grids in Teflon and Kapton reduce the arc energy by two orders of magnitude over untreated samples. Extreme low temperatures (-195 C) do not significantly increase the arc energy of the gridded sample.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 320-341
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  • 38
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    Conceptual design study. Science and Applications Space Platform (SASP). Final briefing (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The modularity, shape, and size of the recommended platform concept offers a low investment, early option to demonstrate the system; flexibility to conservative growth; adaptability to great variety of multi or dedicated payload groups; and good dispersion and viewing freedom for payloads. Platform configuration effectively supports 80 to 85% of the NASA/OSS and OSTA payloads. The subsystem approaches recommended are based on cost effective distribution of functions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173520 , NAS 1.26:173520 , MDC-G9300
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  • 39
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    Transmission line model of the interaction of a long metal wire with the ionosphere (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An equivalent electric circuit model is used to study the electrodynamic interactions of long orbiting metallic tethers with the ionospheric plasma and, in particular, to derive current and potential profiles along bare metallic tethers. In contrast with other models, this approach is dynamic, enabling both the transient behavior of the wire and its final equilibrium state to be derived. A comparison with the results of other models indicates the advantage of the present approach, especially in those cases where the internal resistance of the tether plays a major role in determining the current and potential distributions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Radio Science; 15; Nov
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  • 40
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    Modifications to the Flexible Spacecraft Dynamics Program (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Modifications to existing subroutines are briefly described and a detailed description of new subroutines is given. The capability to simulate the Dynamics Explorer-B control system new developed and the formulation for this addition is given. The program variables in new labelled COMMON blocks are described in detail and the modified input and output for the d Flexible Spacecraft Dynamics Program is described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166655
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  • 41
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    Fabrication of titanium multi-wall Thermal Protection System (TPS) test panel arrays (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several arrays were designed and tested. Tests included vibrational and acoustical tests, radiant heating tests, and thermal conductivity tests. A feasible manufacturing technique was established for producing the protection system panels.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-159383
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  • 42
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    Decoupled control of a long flexible beam in orbit (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Control involved commanding changes in pitch attitude as well as nulling initial disturbances in the pitch and flexible modes. Control force requirements were analyzed. Also, the effects of parameter uncertainties on the decoupling process were analyzed and were found to be small. Two methods were investigated: the system was completely coupled and certain actuators were then eliminated, one by one, which resulted in some or all modes not fully controlled; specified modes of the system were excluded from the decoupling control law by employing viewer control actuators than modes in the model. In both methods, adjustments were made in the feedback gains to include the uncontrolled modes in the overall control of the system.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1740 , L-13726
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  • 43
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    Viking '75 spacecraft design and test summary. Volume 3: Engineering test summary (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The engineering test program for the lander and the orbiter are presented. The engineering program was developed to achieve confidence that the design was adequate to survive the expected mission environments and to accomplish the mission objective.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-RP-1027-VOL-3 , L-12087-VOL-3
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  • 44
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    Low thrust vehicle concept study (1980)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: Low thrust chemical (hydrogen-oxygen) propulsion systems configured specifically for low acceleration orbit transfer of large space systems were defined. Results indicate that it is cost effective and least risk to combine the OTV and stowed spacecraft in a single 65 K Shuttle. The study shows that the engine for an optimized low thrust stage (1) does not require very low thrust; (2) 1-3 K thrust range appears optimum; (3) thrust transient is not a concern; (4) throttling probably not worthwhile; and (5) multiple thrusters complicate OTV/LSS design and aggravate LSS loads. Regarding the optimum vehicle for low acceleration missions, the single shuttle launch (LSS and expendable OTV) is most cost effective and least risky. Multiple shuttles increase diameter 20%. The space based radar structure short OTV (which maximizes space available for packaged LSS) favors use of torus tank. Propellant tank pressures/vapor residuals are little affected by engine thrust level or number of burns.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-161594 , GDC-ASP-80-010
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  • 45
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    Viking '75 spacecraft design and test summary. Volume 2: Orbiter design (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design of the Viking orbiter spacecraft is described. System configuration, telecommunications, and guidance and control requirements are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-RP-1027-VOL-2 , L-12087-VOL-2
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  • 46
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    Viking '75 spacecraft design and test summary. Volume 1: Lander design (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Viking Mars program is summarized. The design of the Viking lander spacecraft is described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-RP-1027-VOL-1 , L-12087-VOL-1
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  • 47
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    Design of the annular suspension and pointing system /ASPS/ through decoupling and pole placement (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A decoupling and pole-placement technique has been developed for the Annular Suspension and Pointing System (ASPS) of the Space Shuttle which uses bandwidths as performance criteria. The dynamics of the continuous-data ASPS allows the three degrees of freedom to be totally decoupled by state feedback through constant gains, so that the bandwidth of each degree of freedom can be independently specified without interaction. Although it is found that the digital ASPS cannot be completely decoupled, the bandwidth requirements are satisfied by pole placement and a trial-and-error method based on approximate decoupling.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Computers and Electrical Engineering; 7; Dec. 198
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  • 48
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    Solar flux incident on an orbiting surface after reflection from a planet (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Algorithms describing the solar radiation impinging on an infinitesimal surface after reflection from a gray and diffuse planet are derived. The following conditions apply: only radiation from the sunny half of the planet is taken into account; the radiation must fall on the top of the orbiting surface, and radiation must come from that part of the planet that can be seen from the orbiting body. A simple approximate formula is presented which displays excellent accuracy for all significant situations, with an error which is always less than 5% of the maximum possible reflected flux. Attention is also given to solar albedo flux on a surface directly facing the planet, the influence of solar position on albedo flux, and to solar albedo flux as a function of the surface-planet tilt angle.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA Journal; 18; June 198
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  • 49
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    Development of the reentry flight dynamics simulator for evaluation of space shuttle orbiter entry systems (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A nonlinear, six degree of freedom, digital computer simulation of a vehicle which has constant mass properties and whose attitudes are controlled by both aerodynamic surfaces and reaction control system thrusters was developed. A rotating, oblate Earth model was used to describe the gravitational forces which affect long duration Earth entry trajectories. The program is executed in a nonreal time mode or connected to a simulation cockpit to conduct piloted and autopilot studies. The program guidance and control software used by the space shuttle orbiter for its descent from approximately 121.9 km to touchdown on the runway.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1700 , L-13662
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  • 50
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    Analysis of space shuttle orbiter entry dynamics from Mach 10 to Mach 2.5 with the November 1976 flight control system (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A six-degree-of-freedom simulation analysis was performed for the space shuttle orbiter entry from Mach 10 to Mach 2.5 with realistic off-nominal conditions using the flight control system referred to as the November 1976 Integrated Digital Autopilot. The off-nominal conditions included: (1) aerodynamic uncertainties in extrapolating from wind tunnel of flight characteristics, (2) error in deriving angle of attack from onboard instrumentation, (3) failure of two of the four reaction control-system thrusters on each side (design specification), and (4) lateral center-of-gravity offset. Many combinations of these off-nominal conditions resulted in a loss of the orbiter. Control-system modifications were identified to prevent this possibility.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1667 , L-13344
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  • 51
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    Shape change of Galileo probe models in free-flight tests (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Scale models of the Galileo Probe made of polycarbonate, AXF5Q graphite, carbon-carbon composite, and carbon-phenolic were flown in a free flight range in an ambient gas of air, krypton, or xenon. Mach numbers varied between 14 and 24, Reynolds numbers between 300,000 and 1,000,000, stagnation pressures between 31 and 200 atm, and stagnation point heat transfer rates between 10 and 1,000 kW/sq cm. Shadowgraphs indicate gouging ablation of the aft portion of the frustum; the gouging was moderate in air and severe in the noble gases. The graphite models break in the same region. An explanation of the phenomena is offered in terms of the strong compression and shear caused by the reattachment of a turbulent separated flow. Conditions are calculated for similar tests appropriate for Von Karman Facility of the Arnold Engineering Development Center in which a larger model can be flown in argon.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81209 , A-8223
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  • 52
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    Orbiter Landing Loads Math Model Description and Correlation with ALT Flight Data (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of the space shuttle approach and landing test are examined in order to assess landing gear characteristics and performance and verify landing dynamic analyses. The landing gears were instrumented with load-calibrated strain gages, a wheel-speed sensor, and strut stroke measurement devices. The mathematical procedure used in predicting the shuttle touchdown loads and dynamics is presented together with the comparisons between measured flight data and the analytical predictions. Conclusions from these data are also presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-RP-1056 , JSC-16202 , S-498
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  • 53
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    Environmental protection of the solar power satellite (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: This paper examines theoretically several features of the interactions of the Solar Power Satellite (SPS) with its space environment. The leakage currents through the kapton and sapphire solar cell blankets are calculated. At geosynchronous orbit, this parasitic power loss is only 0.7%, and is easily compensated by oversizing. At low-earth orbit, the power loss is potentially much larger (3%), and anomalous arcing is expected for the high-voltage negative surfaces. Preliminary results of a three-dimensional self-consistent plasma and electric field computer program are presented, confirming the validity of the predictions made from the one-dimensional models. Lastly, the paper proposes magnetic shielding of the satellite, to reduce the power drain and to protect the solar cells from energetic electron and plasma ion bombardment. It is concluded that minor modifications from the baseline SPS design can allow the SPS to operate safely and efficiently in its space environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 54
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    A three-dimensional spacecraft-charging computer code (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A computer code is described which simulates the interaction of the space environment with a satellite at geosynchronous altitude. Employing finite elements, a three-dimensional satellite model has been constructed with more than 1000 surface cells and 15 different surface materials. Free space around the satellite is modeled by nesting grids within grids. Applications of this NASA Spacecraft Charging Analyzer Program (NASCAP) code to the study of a satellite photosheath and the differential charging of the SCATHA (satellite charging at high altitudes) satellite in eclipse and in sunlight are discussed. In order to understand detector response when the satellite is charged, the code is used to trace the trajectories of particles reaching the SCATHA detectors. Particle trajectories from positive and negative emitters on SCATHA also are traced to determine the location of returning particles, to estimate the escaping flux, and to simulate active control of satellite potentials.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AD-A088930 , AFGL-TR-80-0233
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  • 55
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    First results of material charging in the space environment (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A satellite experiment, designed to measure potential charging of typical thermal-control materials at near-geosynchronous altitude, was flown as part of the Spacecraft Charging at High Altitudes program. Direct observations of charging of typical satellite materials in a natural charging event (greater than or equal to 5 keV) are presented. The results show some features which differ significantly from previous laboratory simulations of the environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Applied Physics Letters; 37; Aug. 1
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  • 56
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    The dynamics and control of large flexible space structures, 3. Part A: Shape and orientation control of a platform in orbit using point actuators (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The dynamics, attitude, and shape control of a large thin flexible square platform in orbit are studied. Attitude and shape control are 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 three different nominal orientations: (1) the platform following the local vertical with its major surface perpendicular to the orbital plane; (2) the platform following the local horizontal with its major surface normal to the local vertical; and (3) the platform following the local vertical with its major surface perpendicular to the orbit normal. 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 decoupling, pole placement, and linear optimal control theory. Frequencies and elastic modal shape functions are obtained using a finite element computer algorithm, two different approximate analytical methods, and the results of the three methods compared.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-163253
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  • 57
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    Attitude control study for a large flexible spacecraft using a Solar Electric Propulsion System (SEPS) (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The attitude control performance of the solar electric propulsion system (SEPS) was evaluated. A thrust vector control system for powered flight control was examined along with a gas jet reaction control system, and a reaction wheel system, both of which have been proposed for nonpowered flight control. Comprehensive computer simulations of each control system were made and evaluated using a 30 mode spacecraft model. Results obtained indicate that thrust vector control and reaction wheel systems offer acceptable smooth proportional control. The gas jet control system is shown to be risky for a flexible structure such as SEPS, and is therefore, not recommended as a primary control method.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-162878 , JPL-PUB-80-14
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  • 58
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    An assessment of the readiness of ablative materials for preflight application to the shuttle orbiter (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The shuttle orbiter relies primarily on a reusable surface insulation (RSI) thermal protection system (TPS). The RSI is very efficient in its thermal performance; however, the RSI tile system has shown poor mechanical integrity. The state-of-the-art of the ablative TPS is reviewed, and an assessment made of the ablator's readiness for use on the shuttle orbiter. Unresolved technical issues with regard to the ablative TPS are identified. Short time, highly focused analytical and experimental programs were initiated to: (1) identify candidate ablation materials; (2) assess the data base for these materials; (3) evaluate the need and kind of waterproof coating; (4) calculate thermal and other stresses in an ablator tile; (5) identify an acceptable ablator/RSI tile joint filler; and (6) assess the sensitivity of the ablator to sequential heat pulses. Results from some of these programs are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81823
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  • 59
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    ATM-CMG control system stability (1980)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Stability analyses and simulation data and results are presented for an initial Control Moment Gyroscope system proposed for the Apollo Telescope Mount cluster (later named Skylab) using momentum vector feedback. A compensation filtering technique is presented which significantly improved analytical and simulation performance of the system. This technique is quite similar to the complementary filtering technique and represents an early NASA application.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81827
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  • 60
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    Orbiter/shuttle carrier aircraft separation: Wind tunnel, simulation, and flight test overview and results (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A summary of the approach and landing test phase of the space shuttle program is given from the orbiter/shuttle carrier aircraft separation point of view. The data and analyses used during the wind tunnel testing, simulation, and flight test phases in preparation for the orbiter approach and landing tests are reported.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-58223
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  • 61
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    Orbit-averaged behavior of magnetic control laws for momentum unloading (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Analytical formulas are derived for orbit-averaged behavior of magnetic control laws for unloading the excess angular momentum of a spacecraft reaction wheel control system in the presence of secular environmental torques. The specific example of an axially symmetric spacecraft with an inertially fixed attitude for which the dominant environmental torque is the gravity-gradient torque is treated in detail, but extensions of the general approach to other inertially fixed and earth-pointing spacecraft are discussed. The analytical formulas are compared to detailed simulations performed for the Solar Maximum Mission spacecraft, and agreement to within 10% is found. The analytical formulas can be used in place of detailed simulations for preliminary studies, and can be used to find selected cases giving the most stringent tests of momentum unloading capability for which detailed simulations may be performed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance and Control; 3; Nov
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  • 62
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    Finite element structural model of a large, thin, completely free, flat plate (1980)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: A finite element structural model of a 30.48 m x 30.48 m x 2.54 mm completely free aluminum plate is described and modal frequencies and mode shape data for the first 44 modes are presented. An explanation of the procedure for using the data is also presented. The model should prove useful for the investigation of controller design approaches for large flexible space structures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81887
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  • 63
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    Recent advances in structural technology for large deployable and erectable spacecraft (1980)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Ultra-low mass deployable and erectable truss structure designs for spacecraft are identified using computerized structural sizing techniques. Extremely slender strut proportions are shown to characterize minimum mass spacecraft which are designed for Shuttle transport to orbit. Analytical results are presented which demonstrate discrete element effects using a recently developed buckling theory for periodic lattice type structures. An analysis of fabrication imperfection effects on the surface accuracy of four different antenna reflector structures is summarized. This study shows the tetrahedral truss to have the greatest potential of the structures examined for application to accurate or large reflectors. A deployable module which can be efficiently transported is identified and shown to have significant potential for application to future antenna requirements. Recent investigations of erectable structure assembly are reviewed. Initial experiments simulating astronaut assembly by extra-vehicular activity (EVA) show that a pair of astronauts can achieve assembly times of 2-5 min/strut. Studies indicate that an automated assembler can achieve times of less than 1 min/strut on an around-the-clock basis.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 80-A-27 , International Astronautical Congress; Sept. 22-28, 1980; Tokyo; Japan
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  • 64
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    Stability and control of flexible satellites. II - Control (1980)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: It is demonstrated that by monitoring the deformations of the flexible elements of a satellite, the effectiveness of the satellite control system can be increased considerably. A simple model of a flexible satellite was analyzed in the first part of this work. The same model is used here for digital computer simulations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 80-E-235 , International Astronautical Congress; Sept. 22-28, 1980; Tokyo; Japan
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  • 65
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    Orbital transfer of large space structures with nuclear electric rockets (1980)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: This paper discusses the potential application of electric propulsion for orbit transfer of a large spacecraft structure from low earth orbit to geosynchronous altitude in a deployed configuration. The electric power was provided by the spacecraft nuclear reactor space power system on a shared basis during transfer operations. Factors considered with respect to system effectiveness included nuclear power source sizing, electric propulsion thruster concept, spacecraft deployment constraints, and orbital operations and safety. It is shown that the favorable total impulse capability inherent in electric propulsion provides a potential economic advantage over chemical propulsion orbit transfer vehicles by reducing the number of Space Shuttle flights in ground-to-orbit transportation requirements.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 80-083 , Goddard Memorial Symposium; March 27, 28, 1980; Washington, D. C.
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  • 66
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    On-orbit evaluation of the control system/structural mode interactions on OSO-8 (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The Orbiting Solar Observatory-8 experienced severe structural mode/control loop interaction problems during the spacecraft development. Extensive analytical studies, using the hybrid coordinate modeling approach, and comprehensive ground testing were carried out in order to achieve the system's precision pointing performance requirements. A recent series of flight tests were conducted with the spacecraft in which a wide bandwidth, high resolution telemetry system was utilized to evaluate the on-orbit flexible dynamics characteristics of the vehicle along with the control system performance. This paper describes the results of these tests, reviewing the basic design problem, analytical approach taken, ground test philosophy, and on-orbit testing. Data from the tests was used to determine the primary mode frequency, damping, and servo coupling dynamics for the on-orbit condition. Additionally, the test results have verified analytically predicted differences between the on-orbit and ground test environments. The test results have led to a validation of both the analytical modeling and servo design techniques used during the development of the control system, and also verified the approach taken to vehicle and servo ground testing.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance and Control; 3; May-June
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  • 67
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    Dynamics of rotationally periodic large space structure (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The analysis of large area rotationally periodic space structures presented in the paper combines the finite element method, transfer matrix procedures, approximation methods, and periodic structure analysis to obtain computational efficiency. The computations used in the analysis indicate that additive damping mechanisms can be evaluated from the frequency response of the structure. The transient response can also be obtained from the frequency response to complete the dynamic analysis.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Sound and Vibration; 68; Feb. 8
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  • 68
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    Voyager spacecraft electrostatic discharge testing (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The program of environmental testing undergone by the Voyager spacecraft in order to simulate the transient voltage effects of electrostatic discharges expected in the energetic plasma environment of Jupiter is reported. The testing consists of studies of the electrostatic discharge characteristics of spacecraft dielectrics in a vacuum-chamber-electron beam facility, brief piece part sensitivity tests on such items as a MOSFET multiplexer and the grounding of the thermal blanket, and assembly tests of the magnetometer boom and the science boom. In addition, testing of a complete spacecraft was performed using two arc sources to simulate long and short duration discharge sources for successive spacecraft shielding and grounding improvements. Due to the testing program, both Voyager 1 and Voyager 2 experienced tolerable electrostatic discharge-caused transient anomalies in science and engineering subsystems, however, a closer duplication of the spacecraft environment is necessary to predict and design actual spacecraft responses more accurately.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 69
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    Dual-spin spacecraft nutation control using articulated payloads (1980)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A technique is presented for achieving active control of nutation on a dual-spin spacecraft with an articulated payload through use of the payload's control system. Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servo-design parameters. The design techniques presented are verified through a series of on-orbit tests recently conducted on the OSO-8 spacecraft.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-16; Jan. 198
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  • 70
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    Orbiter thermal pressure drop characteristics for shuttle orbiter thermal protection system components: High density tile, low density tile, densified low density tile, and strain isolation pad (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure drop tests were conducted on available samples of low and high density tile, densified low density tile, and strain isolation pads. The results are presented in terms of pressure drop, material thickness and volume flow rate. Although the test apparatus was only capable of a small part of the range of conditions to be encountered in a Shuttle Orbiter flight, the data serve to determine the type of flow characteristics to be expected for each material type tested; the measured quantities also should serve as input for initial venting and flow through analysis.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81891
    Format: application/pdf
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  • 71
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    Spacecraft radiators for advanced mission requirements (1980)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: Design requirements for spacecraft heat rejection systems are identified, and their impact on the construction of conventional pumped fluid and hybrid heat pipe/pumped fluid radiators is evaluated. Heat rejection systems to improve the performance or reduce the cost of the spacecraft are proposed. Heat rejection requirements which are large compared to those of existing systems and mission durations which are relatively long, are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-160589 , REPT-2-30320/9R-52212
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  • 72
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    Interplanetary monitoring platform engineering history and achievements (1980)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: In the fall of 1979, last of ten Interplanetary Monitoring Platform Satellite (IMP) missions ended a ten year series of flights dedicated to obtaining new knowledge of the radiation effects in outer space and of solar phenomena during a period of maximum solar flare activity. The technological achievements and scientific accomplishments from the IMP program are described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-80758
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  • 73
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    An improved output feedback control of flexible large space structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A special output feedback control design technique for flexible large space structures is proposed. It is shown that the technique will increase both the damping and frequency of selected modes for more effective control. It is also able to effect integrated control of elastic and rigid-body modes and, in particular, closed-loop system stability and robustness to modal truncation and parameter variation. The technique is seen as marking an improvement over previous work concerning large space structures output feedback control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Conference on Decision and Control; Dec 10, 1980 - Dec 12, 1980; Albuquerque, NM
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  • 74
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    Closed-loop stability of large space structures via singular and regular perturbation techniques - New results (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Large Space Structures are treated as a special class of highly oscillatory distributed parameter systems. Practical controllers will need to be finite dimensional; however, this calls the closed-loop stability into question due to spillover interactions. Recent results, obtained using regular and singular perturbations theory, give stability bounds for closed-loop control of this type of distributed parameter system; this paper surveys these results and their implications for large space structures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Conference on Decision and Control; Dec 10, 1980 - Dec 12, 1980; Albuquerque, NM
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  • 75
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    Damping enhancement and attitude control of large space structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Enhancement of modal damping in large space structures (LSS) is highly desirable and sometimes essential for the stability of the primary attitude control system. This paper considers the use of a number of Annular Momentum Control Devices (AMCD's) for damping enhancement in LSS. It is proved that the closed-loop system is stable in the sense of Lyapunov. Sufficient conditions for asymptotic stability are also obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Conference on Decision and Control; Dec 10, 1980 - Dec 12, 1980; Albuquerque, NM
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  • 76
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    Hypervelocity impacts on Skylab IV/Apollo windows (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A description is presented of some new observations of crater morphology on the Skylab IV/Apollo windows. Aluminum is detected as the only foreign component in six of the seven lined glassy pit craters so far examined by EDS analysis. The most probable source is from aluminum oxide spherules, exhaust effluent of solid fuel rocket motors. The seventh crater contains titanium which may have been derived from an impact of a chip of thermal paint. The size distribution of the lined glassy pit craters appears to be compatible with an origin by hypervelocity impacts of aluminum spherules. If the aluminum oxide spherules are in earth orbit, impact velocities largely in the range of 7 to 10 km/s should be expected. Thus, the impact velocities are well below those expected for most impacts by micrometeorites and these lower velocities may be significant in the development of the lined glassy pit craters. The results indicate that there is a significant population of man-induced micro-debris in earth orbit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Lunar and Planetary Science Conference; Mar 17, 1980 - Mar 21, 1980; Houston, TX
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  • 77
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    Spacecraft loads methodology - Transient vs. shock spectra method (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The methodology for the establishment of spacecraft loads is strongly influenced by project constraints which include the cost, schedule and allowable weight. The most rigorous approach is the transient loads analysis which requires a composite mathematical model of the spacecraft and launch vehicle. The structural member loads for the entire composite structure are computed by applying the forcing functions, which represent various dynamic environments during the mission, to the composite model. Although this method ideally leads to a lightweight design, it is costly and time consuming due to complex interfaces involving many organizations. To reduce complexity and cost a shock spectra method has been used to design spacecraft structures. This method utilizes envelopes of shock spectra of launch vehicle accelerations obtained from analysis and/or flight measurements. Since only limited information on the launch vehicle model is involved in this process the design loads iteration cycle can be rapidly performed within the payload organization. In the present paper, these two methods will be evaluated by comparing the loads for several spacecraft. Flight measured loads will also be used in the evaluation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Emerging technologies in aerospace structures, design, structural dynamics and materials; Aug 13, 1980 - Aug 15, 1980; San Francisco, CA
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  • 78
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    Finite element models and feedback control of flexible aerospace structures (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Large flexible aerospace structures, such as the solar power satellite, are distributed parameter systems with very complex continuum descriptions. This paper investigates the use of finite element methods to produce reduced-order models and finite dimensional feedback controllers for these structures. The main results give conditions under which stable control of the finite element model will produce stable control of the actual structure.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Joint Automatic Control Conference; Aug 13, 1980 - Aug 15, 1980; San Francisco, CA
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  • 79
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    Adaptive/learning control of large space structures - System identification techniques (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Techniques developed for the control of aircraft under changing operating conditions are used to develop a learning control system structure for a multi-configuration, flexible space vehicle. A configuration identification subsystem that is to be used with a learning algorithm and a memory and control process subsystem is developed. Adaptive gain adjustments can be achieved by this learning approach without prestoring of large blocks of parameter data and without dither signal inputs which will be suppressed during operations for which they are not compatible. The Space Shuttle Solar Electric Propulsion (SEP) experiment is used as a sample problem for the testing of adaptive/learning control system algorithms.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Joint Automatic Control Conference; Aug 13, 1980 - Aug 15, 1980; San Francisco, CA
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  • 80
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    Deployable and erectable concepts for large spacecraft (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The structural proportions of minimum-mass tetrahedral truss platforms designed for low earth and geosynchronous orbit are determined by means of computerized sizing techniques, taking into account multiple design requirements and constraints. Strut dimensions characterizing minimum mass designs are found to be significantly more slender than those used for conventional structural applications. It is also shown that the number of shuttle flights required by deployable trusses becomes excessive above certain critical stiffness values, and that an automated assembler can achieve rates of 1 min/strut, by comparison with 2-5 min/strut for two astronauts using manual labor.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1374 , Annual Conference of the Society of Allied Weight Engineers; May 12, 1980 - May 14, 1980; St. Louis, MO
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  • 81
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    Planetary spacecraft - SEPS interface design (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The interactions between a spacecraft which would rendezvous with the comet Tempel II, the stage, and the mission design are summarized along with solar electric propulsion system design issues. Attention is given to data communication, the spacecraft pointing control system, spacecraft power, plasma interactions, the release of a probe to study the comet Halley, and thruster usage. It was concluded that for a planetary mission design using a low-thrust stage, the control of the mission should reside in the payload spacecraft and that the power should be provided by the stage; the NASA standard 28 VDC bus is recommended.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1227 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 82
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    An automated approach to design of solid rockets utilizing a special internal ballistics model (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A pattern search technique is presented, which is utilized in a computer program that minimizes the sum of the squares of the differences, at various times, between a desired thrust-time trace and that calculated with a special mathematical internal ballistics model of a solid propellant rocket motor. The program is demonstrated by matching the thrust-time trace obtained from static tests of the first Space Shuttle SRM starting with input values of 10 variables which are, in general, 10% different from the as-built SRM. It is concluded that an excellent match is obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1135 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
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  • 83
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    Atmospheric perturbation and control of a shuttle/tethered satellite (1980)
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    Publication Date: 2019-07-13
    Description: A simplified model of the strong atmospheric perturbation of a small satellite attached to the orbiter by a long, rigid tether predicts undesirable uncontrolled libration motions similar to those from sophisticated models. The simplified model is used to compare performance limitations of two simple control systems that rely only on tether tension for three-dimensional control. Because the effects on libration of both the changing kinematic and atmospheric drag torques caused by changing length are largely predictable, the controller that models these changes has substantially better performance. In particular, the altitude variation of the tethered satellite above an oblate earth can be controlled substantially better with a controller that uses a length command adapted to these predictable changes than one that only reacts to tension changes. Also, small amplitude out-of-plane librations, that are coupled only to second-order with changing length, can be damped substantially faster by the controller that periodically commands properly phased length changes than by the controller that only reacts to the second-order changes in tension.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Automatic control in space; Jul 02, 1979 - Jul 06, 1979; Oxford
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  • 84
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    Galileo probe forebody entry thermal protection - Aerothermal environments and heat shielding requirements (1980)
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    Publication Date: 2019-07-13
    Description: Solutions are presented for the aerothermal heating environments and the material thermal response for the forebody heatshield on the candidate 242 kg Galileo probe entering the modeled nominal and cold-dense Jovian atmospheres. In the flowfield analysis, a finite difference procedure was employed to obtain benchmark predictions of pressure, radiation and convective heating rates (both laminar and turbulent) and the corresponding wall blowing obtained under the steady state approximation. The fluxes over the probe flank were found to be in a range where spallation is an important mass loss mechanism. The predicted heating rates were also used as boundary conditions for a charring materials ablation which was used to predict thermochemical based surface recession, mass loss and bondline temperatures. The contingency factor of 30% currently employed by NASA was found to be insufficient for entry into the cold-dense atmosphere.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME PAPER 80-ENAS-24 , Intersociety Environmental Systems Conference; Jul 14, 1980 - Jul 17, 1980; San Diego, CA
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  • 85
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    Structural sizing considerations for large space platforms (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Structural optimization studies are made using mathematical programming techniques to examine minimum mass structural proportions of deployable and erectable tetrahedral truss platforms subject to the integrated effects of practical design requirements. Considerations integrated into the optimization process are: 1) lowest natural frequencies of the platform and individual platform components (struts); 2) packaging constraints imposed by the Shuttle cargo bay capacity; 3) initial curvature of the struts; 4) column buckling of the struts due to gravity gradient, orbital transfer, strut length tolerance, or design loads; and 5) practical lower limits for strut diameter and wall thickness. Ultra-low mass designs are shown to be possible with strut proportions much more slender than those conventionally used for earthbound application.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0680 , Structures, Structural Dynamics, and Materials Conference; May 12, 1980 - May 14, 1980; Seattle, WA
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  • 86
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    Dynamics of the AMCD ring (1980)
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    Publication Date: 2019-07-13
    Description: The derivation of the force-free equations of motion of a spinning flexible ring via Lagrange's equations is presented. Closed-form expressions for the natural frequencies are obtained for the most general motion of the ring. Numerical results for rings of different radii and spin rates are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Dynamics and control of large flexible spacecraft; Jun 21, 1979 - Jun 23, 1979; Blacksburg, VA
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  • 87
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    Configuration effects on satellite charging response (1980)
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    Publication Date: 2019-07-13
    Description: The paper presents a computer study of the response of various spacecraft configurations to a charging environment in sunlight using the NASCAP code. Configuration features considered include geometry, type of stabilization, and overall size. The most striking configuration effect observed is that type of stabilization. A spinning spacecraft is expected to exhibit slower charging of its structure but to develop larger electric field stresses across shaded insulation than is an identical spacecraft which is three-axis stabilized. Data from the ATS-5 and ATS-6 spacecraft are presented and discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0040 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 88
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    Material problems in solar sail development (1980)
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    Publication Date: 2019-07-13
    Description: The paper considers the solar sail principle as an effective means of space propulsion. The heliogyro configuration is discussed including the hub structures, the flap-hinge brace assembly, and the blade. The material requirements of the sail film made of metallized polymers, the tendons produced from a polymer-graphite fiber composite, and battens constructed of graphite/epoxy tubings are considered, noting that not all of these materials were readily available. It was concluded that the primary material problems are the environmental degradation of polymer films, the meteoroid hazard, and the production capacity for large polymer film quantities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0315 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 89
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    Development of thermal energy storage units for spacecraft cryogenic coolers (1980)
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    Publication Date: 2019-07-13
    Description: Thermal Energy Storage Units were developed for storing thermal energy required for operating Vuilleumier cryogenic space coolers. In the course of the development work the thermal characteristics of thermal energy storage material was investigated. By three distinctly different methods it was established that ternary salts did not release fusion energy as determined by ideality at the melting point of the eutectic salt. Phase change energy was released over a relatively wide range of temperature with a large change in volume. This strongly affects the amount of thermal energy that is available to the Vuilleumier cryogenic cooler at its operating temperature range and the amount of thermal energy that can be stored and released during a single storage cycle.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0145 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 90
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    Thermal convection in an enclosure due to vibrations aboard spacecraft (1980)
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    Publication Date: 2019-07-13
    Description: The paper discusses thermal convection in an enclosure induced by spacecraft vibrations (g-jitter). Under normal circumstances (no maneuvers, no intentional spinning of the spacecraft) the g-jitter generates predominantly oscillatory velocity and temperature fields with zero time-mean values. The g-jitter can also generate secondary flows with non-zero mean, but they are of much smaller order. Some implications of the g-jitter on materials processing in space are discussed
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0314 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
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  • 91
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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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  • 92
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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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  • 93
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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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  • 94
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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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  • 95
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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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  • 96
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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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  • 97
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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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  • 98
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    Three dimensional space charge model for large high voltage satellites (1980)
    In:  Other Sources
    Details
    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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  • 99
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    Simulation of charging response of SCATHA (P78-2) satellite (1980)
    In:  Other Sources
    Details
    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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  • 100
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    Aspect dependence and frequency spectrum of electrical discharges on the P78-2 (SCATHA) satellite (1980)
    In:  Other Sources
    Details
    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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