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At least 1,099 records · Page 61
All sourcesNASA NTRSDOE OSTI
NASA NTRS1976

Mercury's rotation axis and period

Recent measurements made from high-resolution Mariner 10 photography of the planet Mercury yield a rotation period of 58.6461 + or 0.005 days, in excellent agreement with the period required for a precise 2/3 resonance with its orbital period (58.6462 days). The axis of rotation of the planet was calculated to be offset about 2 deg from the perpendicular to its orbital plane within a 50% probability error ellipse of + or - 2.6 deg by + or - 6.5 deg. Dynamical considerations make it most likely that the true displacement from the orbit normal is less than 1 deg.

Klaasen, K. P.↗
NASA NTRS1976

Mariner 10 infrared radiometer results - Temperatures and thermal properties of the surface of Mercury

Mariner 10 infrared brightness temperatures of the surface of Mercury at 11 and 45 microns are presented. The data were obtained during the first flyby along a near-equatorial swath extending from 17 hours local time through local midnight to 9 hours local time. For an assumed emissivity of 0.9, derived surface thermal inertias are between 0.0015 and 0.0031 cal/sq cm/sq root sec/K and the implied minimum predawn surface kinetic temperature for the warm pole at longitude 270 deg is near 93 K. Several pronounced thermal inhomogeneities were seen, one of which appears to coincide with a region of high radar reflectivity. The derived thermal properties, the electrical skin depth, and loss tangent fall within the range of values found on the moon.

Chase, S. C., Jr.↗
NASA NTRS1976

Bow shock and magnetosheath waves at Mercury

Mariner 10 measurements at the Mercury bow shock provide examples where the magnetic field is approximately parallel or perpendicular to the bow shock normal. Upstream of a broad irregular parallel shock, left-hand circularly polarized waves are observed which cut off very sharply at about 4 Hz. Upstream of a perpendicular shock, righ-hand circularly polarized waves are observed which persist up to the Nyquist frequency of 12 Hz. Determination of the wave propagation vector as a function of frequency helps to identify conclusively the waves as whistler mode waves propagating from the shock. The magnetosheath downstream of the parallel shock is disturbed more than that downstream of the perpendicular shock, particularly below 1 Hz. In the latter case, regular left-hand-polarized waves observed slightly above the proton gyrofrequency are identified as ion cyclotron waves with wavelengths of about 300 km which have been Doppler shifted up to their observed frequency.

Fairfield, D. H.↗
NASA NTRS1977

Comparison of thermal analytic model with experimental test results for 30-sentimeter-diameter engineering model mercury ion thruster

A thermal analytic model for a 30-cm engineering model mercury-ion thruster was developed and calibrated using the experimental test results of tests of a pre-engineering model 30-cm thruster. A series of tests, performed later, simulated a wide range of thermal environments on an operating 30-cm engineering model thruster, which was instrumented to measure the temperature distribution within it. The modified analytic model is described and analytic and experimental results compared for various operating conditions. Based on the comparisons, it is concluded that the analytic model can be used as a preliminary design tool to predict thruster steady-state temperature distributions for stage and mission studies and to define the thermal interface bewteen the thruster and other elements of a spacecraft.

Oglebay, J. C.↗
NASA NTRS1977

Mariner Venus Mercury 1973 S/X-band experiment

The S/X-band experiment on the Mariner Venus/Mercury 1973 spacecraft constituted a unique opportunity to demonstrate the capability of an X-band downlink coherent with the normal S-band downlink. This was both a technological and scientific experiment, and the results indicated that it was successful in both cases. Analysis of the tracking data shows that the new S/X data type was capable of reducing the miss distance at the planet Mercury by 80% (post-processed data). The use of S/X electron content was demonstrated by comparison with Faraday rotation data. An X-band turnaround telemetry experiment showed the feasibility of a planetary X-band link. In the science area, the model atmospheric environment of Venus was refined. The ionosphere of the planet was measured to a higher accuracy than before, and the value of the dual-frequency link for measuring the scale size of turbulence was demonstrated. The estimate of the scale size was increased from 100 m to above 5 km.

Levy, G. S.↗
NASA NTRS1976

Progress Report on Project Mercury

Progress on Project Mercury, program for manned orbital space flight, is briefly reviewed. The original aims and concepts of the project are recounted. Various types of launch apparatus are mentioned along with safety factors.

Donlan, C. J.↗
NASA NTRS1977

From Wallops Island to Project Mercury, 1945 - 1958: A memoir

Research is described which was conducted at the Wallops Island Missile Range (operated by the old National Advisory Committee for Aeronautics). These early beginnings are shown to be the base from which the Mercury Project evolved.

Gilruth, R. R.↗
NASA NTRS1976

High power operation of a 30-cm mercury bombardment ion thruster

The nominal input power of a 30-cm mercury bombardment ion thruster is 2.5 kW. A representative 30-cm thruster has been operated at higher power levels by increasing either the ion beam voltage or current. Initial results indicate that higher voltage (high specific impulse) operation requires only minor modifications in thruster design. Higher current (low specific impulse) operation, on the other hand, requires improvements in the capabilities of the discharge chamber and ion optics assembly designs to meet lifetime and/or performance specifications. Experimental data is presented and considerations for high power operation (up to 10 kW) are discussed.

Poeschel, R. L.↗
NASA NTRS1976

The occultation of Mariner 10 by Mercury

Analysis of Mariner 10 dual-frequency radio-occultation recordings has yielded new information on the radius and atmosphere of Mercury. The ingress measurements, which were conducted near 1.1 deg north latitude and 67.4 deg east longitude on the night side of the planet, gave a value for the radius of 2439.5 + or - 1 km. Egress near 67.6 deg north latitude and 258.4 deg east longitude on the sunlit side yielded a radius of 2439.0 + or - 1 km. The atmospheric measurements showed the electron density to be less than 1000 per cu cm on both sides of the planet. From the latter result one may infer an upper limit to the dayside surface gas density of 1 million molecules per cu cm.

Fjeldbo, G.↗
NASA NTRS1977

Observations at the planet Mercury by the plasma electron experiment - Mariner 10

Two nightside encounters with Mercury's magnetosphere by Mariner 10 revealed bow shock and magnetosheath signatures in the plasma electron data that are entirely consistent with the geometry expected for an interaction between a planet-centered magnetic dipole and the solar wind. The geometrically determined distance between the planet's center and the solar wind stagnation point is 1.4 plus or minus 0.1 R sub M. Both diffuse and sharp shock crossings were observed on the two magnetosphere encounters.

Ogilvie, K. W.↗
NASA NTRS1976

Martian crater depth/diameter relationships - Comparison with the moon and Mercury

New Martian topographic data from Mariner 9 ultraviolet spectrometer (UVS) profiles provide depth data for 139 Martian craters of all degrees of degradation, between the diameters of 15 and 201 km. The population of Martian craters, including morphologically fresh examples, is shallower than both lunar and Mercurian fresh crater populations. Because the surface gravities of Mercury and Mars are identical within 5%, these differences in fresh crater depths suggest that factors other than gravity may play important roles in determining initial crater depths (e.g., differences in impact velocity, substrate variations, and Martian atmospheric effects during the crater-forming event). Degraded Martian craters are, on the average, no shallower than lunar pre-Imbrian craters of similar sizes. If the early bombardment of Mars was as significant a degradational agent as it was on the moon, then major levels of crater degradation and crater shallowing on Mars were associated with this mechanism. Continued eolian infilling, although locally significant, may be a less significant cause of morphometric degradation of large old Martian craters.

Cintala, M. J.↗
NASA NTRS1976

Comparison of large crater and multiringed basin populations on Mars, Mercury, and the moon

The maximum regional areal densities of large impact craters on Mars, Mercury, and the moon appear to be inversely proportional to the surface areas of the planets. This would not be expected if the objects impacting the planetary surfaces came from common sources and were moving with high velocities relative to the planets; rather, a uniform areal density would be anticipated. Another way of stating the observation is that each planet was bombarded by the same number of objects. Two speculative explanations for the observation are that: (1) all planets underwent a uniform bombardment but were resurfaced by processes proportional to planetary surface area, or (2) equally populated families of objects, moving about the sun in orbits similar to those of the planets, were independently depopulated by the respective planets.

Malin, M. C.↗
NASA NTRS1977

Mercury ion thruster research, 1977

The measured ion beam divergence characteristics of two and three-grid, multiaperture accelerator systems are presented. The effects of perveance, geometry, net-to-total accelerating voltage, discharge voltage and propellant are examined. The applicability of a model describing doubly-charged ion densities in mercury thrusters is demonstrated for an 8-cm diameter thruster. The results of detailed Langmuir probing of the interior of an operating cathode are given and used to determine the ionization fraction as a function of position upstream of the cathode orifice. A mathematical model of discharge chamber electron diffusion and collection processes is presented along with scaling laws useful in estimating performance of large diameter and/or high specific impluse thrusters. A model describing the production of ionized molecular nitrogen in ion thrusters is included.

Wilbur, P. J.↗
NASA NTRS1978

Evolution of the 1-mlb mercury ion thruster subsystem

The developmental history, performance, and major lifetests of each component of the present 1-mlb (4.5 mN) thruster system are traced over the past 10 years. The 1-mlb thruster subsystem consists of an 8 cm diameter ion thruster mounted on 2 axis gimbals, a mercury propellant tank, a power electronics unit, a controller/digital interface unit, and necessary electrical harnesses plus propellant tankage and feed lines.

Kerslake, W. R.↗
NASA NTRS1978

Planned flight test of a mercury ion auxiliary propulsion system. 1: Objectives, systems descriptions, and mission operations

A planned flight test of an 8 cm diameter, electron-bombardment mercury ion thruster system is described. The primary objective of the test is to flight qualify the 5 mN (1 mlb.) thruster system for auxiliary propulsion applications. A seven year north-south stationkeeping mission was selected as the basis for the flight test operating profile. The flight test, which will employ two thruster systems, will also generate thruster system space performance data, measure thruster-spacecraft interactions, and demonstrate thruster operation in a number of operating modes. The flight test is designated as SAMSO-601 and will be flown aboard the shuttle-launched Air Force space test program P80-1 satellite in 1981. The spacecraft will be 3- axis stabilized in its final 740 km circular orbit, which will have an inclination of approximately greater than 73 degrees. The spacecraft design lifetime is three years.

Power, J. C.↗
NASA NTRS1978

Constrained sloshing of liquid mercury in a flexible spherical tank

The mercury propellant tank system developed for use with solar electric propulsion was studied to analytically determine the resonant frequencies of the tank system and compare them with the anticipated control natural frequency of the spacecraft. The system consisted of a stainless steel spherical shell and a hemispherical elastometric diaphragm. The major analytical tool used was the NASTRAN program. Six mathematical models were developed. Resonant frequencies for six harmonics were obtained for each of the six models considered. The results show that the lowest resonant frequency for the tank system is about an order of magnitude greater than the anticipated control frequency of the spacecraft.

Lestingi, J.↗
NASA NTRS1978

A 30-cm mercury ion thruster performance with a 1 kW capacitor-diode voltage multiplier beam supply

A 1 kW solar array and capacitor-diode voltage multiplier converter (S/A-CDVM) was successfully integrated with a 30 cm diameter mercury ion thruster system to provide ion beam power. Measurements were made to compare steady state and transient response performance of a conventional bridge converter with the S/A-CDVM converter used for the ion beam supply. The ability to recover from screen to accelerator arcs and promptly re-establish stable thruster performance was demonstrated. Solar array transient response to thruster arcing was measured.

Terdan, F. F.↗
NASA NTRS1977

Rayed craters on the moon and Mercury

Systems of bright rays are exhibited by many fresh craters on the moon and Mercury. Diameter/density distributions suggest that lunar-rayed craters represent the Class 1 craters, and that Mercurian rayed craters represent post-Caloris craters. Photogeological analyses of lunar imagery indicate that the ray systems are composed of finely divided material from the primary crater along with locally derived ejecta from secondary and tertiary craters. The primary ray material probably occurs in moderately thick (0.1-1 meter) deposits. The rate of darkening may depend more on the thickness of the ray material than on the rates of various darkening processes. Darkening rate may also be a function of crater size. It is observed that rays of craters more than 1 b.y. old remain bright, whereas those older than Class 1 generally fade to imperceptibility.

Allen, C. C.↗