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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 469 records · Page 26
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NASA NTRS1984

Sulfur and oxygen escape from Io and a lower limit to atmospheric SO2 at Voyager 1 encounter

Estimates of the abundance of sulfur, sodium and oxygen ions and neutrals observed by Voyager 1 in the plasma torus and neutral cloud associated with the Jovian satellite Io are used to investigate the physical characteristics of the Io atmosphere. Specific attention is given to two questions about the Io atmosphere: the necessity of an atmosphere to account for the supply of sulfur and oxygen observed in the plasma torus, and, if an atmosphere is necessary, the lower limit to such atmosphere. It is found that an SO2 atmosphere is most likely needed on Io as an intermediate buffer so that the sulfur and oxygen can be transported to the plasma torus. The minimum atmosphere needed for this process is calculated to be 1.4 x 10 to the -10th bar with an SO2 column density of about 10 to the 16th per sq cm and an SO2 surface density of about 1.2 x 10 to the 10th per cu cm. A complete list of all the atmospheric escape fluxes for Io is provided.

Kumar, S.↗
NASA NTRS1984

Models of angular momentum input to a circumterrestrial swarm from encounters with heliocentric planetesimals

Preliminary experiments show that heliocentric planetesimals passing through the Earth environment possess significant angular momentum. However it also appears that these same planetesimals impacting a circularized circumterrestrial planetesimal swarm would likely remove angular momentum (though possibly increasing mean kinetic energy), presumably promoting both swarm infall upon the Earth and escape to heliocentric space. Only a distribution of highly eccentric satellite orbits with mean tangential velocities of a few tens of percent of local circular velocity would be immune against angular momentum loss to passing heliocentric planetesimals.

Herbert, F.↗
NASA NTRS1985

Models of Angular Momentum Input to a Circumterrestrial Swarm from Encounters with Heliocentric Planetesimals

Models of lunar origin in which the Moon accretes in orbit about the Earth from material approaching the Earth from heliocentric orbits must overcome a fundamental problem: the approach orbits of such material would be, in the simplest approximation, equally likely to be prograde or retrograde about the Earth, with the result that accretion of such material adds mass but not angular momentum to circumterrestrial satellites. Satellite orbits would then decay due to the resulting drag, ultimately impacting onto the Earth. One possibility for adding both material and angular momentum to Earth orbit is investigated: imbalance in the delivered angular momentum between pro and retrograde Earth passing orbits which arises from the three body dynamics of planetesimals approaching the Earth from heliocentric space. In order to study angular momentum delivery to circumterrestrial satellites, the near Earth velocities were numerically computed as a function of distance from the Earth for a large array of orbits systematically spanning heliocentric phase space.

Davis, D. R.↗
NASA NTRS1985

Three spacecraft measurements of an unusual disturbance in the solar wind - Further evidence for a cometary encounter

It is noted that, while the Pioneer Venus orbiter detected an unusual IMF and solar wind plasma disturbance on Feb. 11, 1982, the Venera 13 and 14 spacecraft were conducting IMF measurements 6 million miles away which exhibit very weak disturbances several hours after the peak of the Pioneer Venus event. It is speculated that, if the event had been a solar-initiated disturbance, it should have been detected in virtually unaltered form by Venera 13 and 14; whose data therefore furnish further evidence for the cometary nature of this event.

Russell, C. T.↗
NASA NTRS1986

Ion composition results during the International Cometary Explorer encounter with Giacobini-Zinner

The International Cometary Explorer spacecraft passed through the coma of comet Giacobini-Zinner about 7800 kilometers antisunward of the nucleus on September 11, 1985. The ion composition instrument was sensitive to ambient ions with mass-to-charge ratios in the ranges 1.4 to 3 atomic mass units per electron charge (amu/e) and 14 to 33 amu/e. Initial interpretation of the measurements indicates the presence of H2O(+), H3O(+), probably CO(+) and HCO(+), and ions in the mass range 23 to 24; possible candidates are Na(+) and Mg(+) and Mg(+). In addition to these heavy ions, measured over the velocity range 80 to 223 kilometers per second, the instruments measured He(2+) of solar wind origin over the range 237 to 463 kilometers per second. The heavy ions have a velocity distribution which indicates that they have been picked up by the motional electric field, whereas the light ions are steadily decelerated as the comet tail axis is approached. These results are in agreement with the picture of a comet primarily consisting of water ice, together with other material, that sublimes, streams away from the nucleus, becomes ionized, and interacts with the solar wind.

Ogilvie, K. W.↗
NASA NTRS1986

International Cometary Explorer encounter with Giacobini-Zinner - Magnetic field observations

The vector helium magnetometer on the International Cometary Explorer observed the magnetic fields induced by the interaction of comet Giacobini-Zinner with the solar wind. A magnetic tail was penetrated about 7800 kilometers downstream from the comet and was found to be 10,000 kilometers wide. It consisted of two lobes, containing oppositely directed fields with strengths up to 60 nanoteslas, separated by a plasma sheet about 1000 kilometers thick containing a thin current sheet. The magnetotail was enclosed in an extended ionosheath characterized by intense hydromagnetic turbulence and interplanetary fields draped around the comet. A distant bow wave, which may or may not have been a bow shock, was observed at both edges of the ionoshpeath. Weak turbulence was observed well upstream of the bow wave.

Smith, E. J.↗
NASA NTRS1986

The Voyager 2 encounter with the Uranian system

Discoveries which have occurred due to the success of the Voyager 2 flyby of Uranus and its moons are summarized, along with techniques used to maximize the data collected and minimize the demands on the spacecraft. The 11 spacecraft science packages, including photopolarimeters, spectrometers, a magnetometer, radios and a charged particle detector gathered information on the ring system, the scattering, emitting and reflecting characteristics of the Uranian atmosphere, and the five major satellites. The data revealed 10 minor satellites between Miranda and Uranus and the similarities between the Uranus, Saturn and Jupiter atmospheres. Extensive tabular data are provided for the physical dimensions of the nine rings and the 15 satellites. Finally, data on the magnetosphere and upper atmosphere environment of Uranus and imagery of the major moons are discussed.

Stone, E. C.↗
NASA NTRS1986

Optimal control laws for microburst encounter

Simplified structures for longitudinal control laws that reduce an aircraft's response to the strong head-tailwind and downdraft variations associated with microbursts are presented. They are based on non-zero-set-point linear-quadratic regulators that command throttle setting and angle of attack as functions of velocity and flight path angle, and they can incorporate direct measurements of the wind profile if available. Selection of cost functions to be minimized by feedback control has been aided by a prior study of classical control laws and exact nonlinear-optimal flight paths through realistic microburst wind profiles. The resulting optimal control laws have an adaptive, dual-mode structure that can be implemented either in flight-director logic or in an autopilot.

Stengel, R. F.↗
NASA NTRS1987

Predicting Close Satellite Encounters

Method for predicting probabilities of collisions between nominally geosynchronous satellites gives results without large computer resources. Realistically assesses possibility of collision between expired, drifting satellite and active, station-keeping satellite. Mathematical techniques in paper useful in analysis of such terrestrial risks as floods and nuclear accidents.

Mccormick, B. R.↗
NASA NTRS1987

Investigation of transonic region of high dynamic response encountered on an elastic supercritical wing

Unsteady aerodynamic data were measured on an aspect ratio 10.3 elastic supercritical wing while undergoing high dynamic response above a Mach number of 0.90. These tests were conducted in the NASA Langley Transonic Dynamics Tunnel. A previous test of this wing predicted an unusual instability boundary based on subcritical response data. During the present test no instability was found, but an angle of attack dependent narrow Mach number region of high dynamic wing response was observed over a wide range of dynamic pressures. The effect on dynamic wing response of wing angle of attack, static outbound control surface deflection and a lower surface spanwise fence located near the 60 percent local chordline was investigated. The driving mechanism of the dynamic wing response appears to be related to chordwise shock movement in conjunction with flow separation and reattachment on both the upper and lower surfaces.

Seidel, David A.↗
NASA NTRS1987

Unresolved issues in wind shear encounters

Much remains to be learned about the hazards of low altitude wind shear to aviation. New research should be conducted on the nature of the atmospheric environment, on aircraft performance, and on guidance and control aids. In conducting this research, it is important to distinguish between near-term and far-term objectives, between basic and applied research, and between uses of results for aircraft design or for real-time implementation. Advances in on-board electronics can be applied to assuring that aircraft of all classes have near optimal protection against wind shear hazards.

Stengel, Robert F.↗
NASA NTRS1987

An electrically conductive thermal control surface for spacecraft encountering Low-Earth Orbit (LEO) atomic oxygen indium tin oxide-coated thermal blankets

An organic black thermal blanket material was coated with indium tin oxide (ITO) to prevent blanket degradation in the low Earth orbit (LEO) atomic oxygen environment. The blankets were designed for the Galileo spacecraft. Galileo was initially intended for space shuttle launch and would, therefore, have been exposed to atomic oxygen in LEO for between 10 and 25 hours. Two processes for depositing ITO are described. Thermooptical, electrical, and chemical properties of the ITO film are presented as a function of the deposition process. Results of exposure of the ITO film to atomic oxygen (from a shuttle flight) and radiation exposure (simulated Jovian environment) are also presented. It is shown that the ITO-protected thermal blankets would resist the anticipated LEO oxygen and Jovian radiation yet provide adequate thermooptical and electrical resistance. Reference is made to the ESA Ulysses spacecraft, which also used ITO protection on thermal control surfaces.

Bauer, J. L.↗
NASA NTRS1986

Plasma-tail activity at the time of the Vega encounters

Physical associations are sought between Halley's plasma tail activity seen in ground-based imagery and near-comet, solar wind/IMF measurements obtained by the Vega spacecraft. Disconnection Events (DE's) and the sector boundary/frontside magnetic reconnection model (Niedner and Brandt, 1978) of their origin are discussed. Strong support for the model comes from 2 DE's: a major event whose onset, on March 7 to 8, is strongly correlated with a reversal of the comet's magnetic barrier observed by Vega-1 and Vega-2 and with an IMF sector boundary observed by Vega-1; and a minor event on March 7 which may be associated with the two-polarity (possibly reconnecting) magnetic barrier seen by Vega-1 on March 6, when the solar-wind density was low.

Niedner, Malcolm B., Jr.↗
NASA NTRS1986

Studying flight crew behavior: A social psychologist encounters the real world

Considerable social psychological research has been conducted on the relationship between personality and performance in various occupational settings. Of special interest are situations where the performer is under pressure or the consequences of poor performance can be serious, as in aircraft operation. Some significant findings are summarized, including those related to Type A personality factors, achievement motivation factors, and attitude factors. Future research should focus on group behavior.

Helmreich, Robert L.↗
NASA NTRS1986

Engineering Voyager 2's encounter with Uranus

Changes made by radio control from the ground in the Voyager 2 spacecraft as it approached Uranus are described. Reduced power required that subsystems and heaters had to be switched on and off in carefully synchronized fashion. Low light levels required increased exposure times, so the jiggling of the spacecraft had to be minimized. Coding changes were made and image data were compressed to cope with the reduced bit rate at larger distances. Successful efforts to cope with failures in the primary radio receiver and in the computer instructions for image compression are described, as are changes made on the ground in the spacecraft navigation.

Laeser, Richard P.↗
NASA NTRS1986

The spacecraft encounters of Comet Halley

The characteristics of the Comet Halley spacecraft 'fleet' (VEGA 1 and VEGA 2, Giotto, Suisei, and Sakigake) are presented. The major aims of these missions were (1) to discover and characterize the nucleus, (2) to characterize the atmosphere and ionosphere, (3) to characterize the dust, and (4) to characterize the nature of the large-scale comet-solar wind interaction. While the VEGA and Giotto missions were designed to study all four areas, Suisei addressed the second and fourth. Sakigake was designed to study the solar wind conditions upstream of the comet. It is noted that NASA's Deep Space Network played an important role in spacecraft tracking.

Asoka Mendis, D.↗
NASA NTRS1987

Investigation of transonic region of high dynamic response encountered on an elastic supercritical wing

Unsteady aerodynamic data were measured on an aspect ratio 10.3 elastic supercritical wing while undergoing high dynamic response above Mach number of 0.90. These tests were conducted in the NASA Langley Transonic Dynamics Tunnel. A previous test of this wing predicted an unusual instability boundary based upon subcritical response data. During the present test no instability was found, but an angle of attack dependent narrow Mach number region of high dynamic wing response was observed over a wide range of dynamic pressures. The effect on dynamic wing response of wing angle of attack, static outboard control surface deflection and a lower surface spanwise fence located near the 60 percent local chordline was investigated. The driving mechanism of the dynamic wing response appears to be related to chordwise shock movement in conjunction with flow separation and reattachment on both the upper and lower surfaces.

Seidel, David A.↗