Probable solar flare doses encountered on an interplanetary mission as calculated by the MCFLARE code
MCFLARE code to calculate probable flare doses encountered on interplanetary mission
Karp, I. M.↗
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Evaluation of effects of high-altitude turbulence encounters on the XB-70 airplane
Evaluating effects of high altitude turbulence encounters on XB-70 airplane
Larson, R. R.↗
NASTRAN Installation: Implementation Steps and Possible Problems Encountered
NASTRAN, from its inception, was designed to operate on several diverse computer system. It is currently installed and operating on the CDC 6600, the IBM 360, and the UNIVAC 1108. This paper discusses the steps found by CSC to be necessary in installing NASTRAN on a computer system and the possible obstacles that might be encountered in undertaking NASTRAN installation. Reference is made to actual problems that arose during installation on the above machines. With a knowledge of what has happened to date in setting up NASTRAN, the future user will be better able to cope with and understand the implications of installing NASTRAN on his computer.
Dielmann, H. E.↗
Maximum discriminability versions of the near- encounter Mariner pictures
Mariner near encounter pictures with maximum discriminability, applying algorithms for contrast and resolution enhancement and noise removal
Collins, S. A.↗
Satellite encounter opportunities of the Grand Tour missions
Multiple outer planets flyby opportunities during 1976-1980 Grand Tour missions launch period, presenting computer generated specific encounter dates and flyby distances
Penzo, P. A.↗
Probable solar flare doses encountered on an interplanetary mission as calculated by the MCFLARE code
The computer program, MCFLARE, uses Monte Carlo methods to simulate solar flare occurrences during an interplanetary space voyage. The total biological dose inside a shielded crew compartment due to the flares encountered during the voyage is determined. The computer program evaluates the doses obtained on a large number of trips having identical trajectories. From these results, a dose D sub p having a probability p of not being exceeded during the voyage can be determined as a function of p for any shield material configuration. To illustrate the use of the code, a trip to Mars and return is calculated, and estimated doses behind several thicknesses of aluminum shield and water shield are presented.
Lahti, G. P.↗
Jupiter radiation test levels and their expected impact on an encounter mission
The upper limit, of electron and proton fluences for a thermoelectric outer planet spacecraft mission in a near-Jupiter environment, for use as radiation design restraints, were extracted from a model of the Jovian trapped radiation belts. Considerations of radiation effects in semiconductor devices were employed to construct simplified radiation test levels based on the design restraints. Corresponding levels, based on the nominal belt models, are one to three orders of magnitude smaller. In terms of expected radiation-induced degradation in semiconductor devices, an encounter with an environment as severe as the design restraints would require hardening the system in order to guarantee high reliability. On the other hand, the nominal levels would only necessitate care in the selection of components and the avoidance of certain semiconductor components.
Barengoltz, J. B.↗
Meteorological parameters versus CAT encountered in the stratosphere by the XB-70 airplane.
Frequency distributions prepared from synoptic meteorological parameters associated with turbulent and nonturbulent conditions encountered by the XB-70 aircraft at altitudes generally between 12 and 20 km in the stratosphere show that turbulence is associated with certain ranges or critical values of the parameters. Certain combinations of the variables are associated with turbulence for at least one-fourth to one-third of the observations.
Scoggins, J. R.↗
Random gravitational encounters and the evolution of spherical systems. III - Halo.
The accumulation of stars in the halo of a spherical stellar system, together with the escape of stars from the system, result from stellar encounters within a dense central core. The resultant halo structure is studied both analytically and numerically for an isolated system. On the assumption that conditions in the central core remain constant with time, a simple steady-state solution is obtained for the outermost halo, or 'fringe', defined as the region from which stars may escape after a few additional orbits through the central core of the system. In this steady-state solution the density in phase space, obtained from a simple integral equation for the fringe region, is found to vary nearly linearly with the total energy of a star per unit mass for energies which are less than the energy of escape.
Spitzer, L., Jr.↗
Gravity thrust Jupiter orbiter trajectories generated by encountering the Galilean satellites.
A trajectory design philosophy is introduced for Jupiter orbiter missions that is based on the gravity thrust concept developed for interplanetary trajectories. This is accomplished by utilizing the moving gravitational fields of the four Galilean satellites. A general theorem, applicable to any existing planetary satellite system, is developed to show how the effects of small satellite perturbations can be magnified by incorporating multiple revolutions between encounters.-
Minovitch, M. A.↗
Magnetic coordinates for the Pioneer 10 Jupiter encounter
The magnetic coordinates of the Pioneer 10 spacecraft and the five innermost satellites are reported for the Jupiter encounter. The D sub 2 offset is used to make the calculations. Magnetic coordinates are needed for the interpretation of the trapped particle measurements, including the absorption effects of the satellites. Contours of constant field magnitude and magnetic latitude are given at the surface of Jupiter for the D sub 2 model. The system 3 longitude of a spacecraft at Jupiter is derived, and formulas given for the relationships between system 1, 2, and 3 longitudes. The longitude of the magnetic dipole increases by about 3 deg per year, due to the inaccurate rotation rate used to define system 3 longitude.
Mead, G. D.↗
Analysis of vortex wake encounter upsets
The problem of an airplane being upset by encountering the vortex wake of a large transport on takeoff or landing is currently receiving considerable attention. This report describes the technique and results of a study to assess the effectiveness of automatic control systems in alleviating vortex wake upsets. A six-degree-of-freedom nonlinear digital simulation was used for this purpose. The analysis included establishing the disturbance input due to penetrating a vortex wake from an arbitrary position and angle. Simulations were computed for both a general aviation airplane and a commercial jet transport. Dynamic responses were obtained for the penetrating aircraft with no augmentation, and with various command augmentation systems, as well as with human pilot control. The results of this preliminary study indicate that attitude command augmentation systems can provide significant alleviation of vortex wake upsets; and can do it better than a human pilot.
Johnson, W. A.↗
Pioneer 10 mission - Summary of scientific results from the encounter with Jupiter
Data on the Jovian atmosphere and radiation environment transmitted by Pioneer 10 as it passed by Jupiter are discussed. The presence of a strong magnetic field, of energetic electron precursers, and of flat disk-shaped particle distribution is noted at a distance of 360 Jovian radii from the planet. Previously available data on Jovian satellites are augmented from Pioneer 10 data. The normal operation of the data collecting and transmitting systems of the mission after encounter with Jupiter is noted.
Opp, A. G.↗
Preliminary Pioneer 10 encounter results from the Ames Research Center plasma analyzer experiment
Preliminary results from the Ames Research Center plasma analyzer experiment for the Pioneer 10 Jupiter encounter indicate that Jupiter has a detached bow shock and magnetopause similar to the case at Earth but much larger in spatial extent. In contrast to Earth, Jupiter's outer magnetosphere appears to be highly inflated by thermal plasma and therefore highly responsive in size to changes in solar wind dynamic pressure.
Wolfe, J. H.↗
Observations at Venus encounter by the plasma science experiment on Mariner 10
Preliminary results from the rearward-looking electrostatic analyzer of the plasma science experiment during the Mariner 10 encounter with Venus are described. They show that the solar-wind interaction with the planet probably involves a bow shock rather than an extended exosphere, but that this is not a thin boundary at the point where it was crossed by Mariner 10. An observed reduction in the flux of electrons with energies greater than 100 electron volts is interpreted as evidence for some direct interaction with the exosphere. Unusual intermittent features observed downstream of the planet indicate the presence of a comet-like tail hundreds of scale lengths in length.
Bridge, H. S.↗
Observations at Mercury encounter by the plasma science experiment on Mariner 10
A fully developed bow shock and magnetosheath were observed near Mercury, providing unambiguous evidence for a strong interaction between Mercury and the solar wind. Inside the sheath there is a distinct region analogous to the magnetosphere or magnetotail of earth, populated by electrons with lower density and higher temperature than the electrons observed in the solar wind or magnetosheath. At the time of encounter, conditions were such that a perpendicular shock was observed on the inbound leg and a parallel shock was observed on the outbound leg of the trajectory, and energetic plasma electron events were detected upstream from the outbound shock crossing. The interaction is most likely not atmospheric, but the data clearly indicate that the obstacle to solar wind flow is magnetic, either intrinsic or induced.
Ogilvie, K. W.↗
Magnetic coordinates for the Pioneer 10 Jupiter encounter
The magnetic coordinates of the Pioneer 10 spacecraft and the five innermost satellites are given around the time of Jupiter encounter, Dec. 1-8, 1973. The D sub 2 offset dipole model of Smith et al. (1974) is used to make the calculations. Magnetic coordinates are needed for the interpretation of the trapped particle measurements, including the absorption effects of the satellites. Contours of constant field magnitude and magnetic latitude are given at the surface of Jupiter for the D sub 2 model. The system III longitude of a spacecraft at Jupiter is derived, and formulas are given for the relationships between system I, II, and III longitudes. The longitude of the magnetic dipole increases by about 3 deg/yr, owing to the inaccurate rotation rate used to define system III longitude.
Mead, G. D.↗
Preliminary interpretation of plasma electron observations at the third encounter of Mariner 10 with Mercury
Plasma electron count observations made during the first and third encounters of Mariner 10 with Mercury (i.e., during Mercury I and III) are reported. They provide detailed information on the magnetosphere of Mercury, especially those from Mercury III. A low-flux region was observed about closest approach (CA) of Mercury III, whereas no such region was detected by the lower-latitude Mercury I; a hot plasma sheet was measured on the outgoing (and near-equator) trajectory of Mercury I, while only cool plasma sheets were observed in the magnetosphere by Mercury III. Findings are similar, on a reduced scale, to models of the earth's magnetosphere and magnetosheath.
Hartle, R. E.↗