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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 325 records · Page 18
All sourcesNASA NTRSDOE OSTI
DOE OSTI2017

Discovery of Extended Main-sequence Turnoffs in Four Young Massive Clusters in the Magellanic Clouds

An increasing number of young massive clusters (YMCs) in the Magellanic Clouds have been found to exhibit bimodal or extended main sequences (MSs) in their color–magnitude diagrams (CMDs). These features are usually interpreted in terms of a coeval stellar population with different stellar rotational rates, where the blue and red MS stars are populated by non- (or slowly) and rapidly rotating stellar populations, respectively. However, some studies have shown that an age spread of several million years is required to reproduce the observed wide turnoff regions in some YMCs. Here we present the ultraviolet–visual CMDs of four Large and Small Magellanic Cloud YMCs, NGC 330, NGC 1805, NGC 1818, and NGC 2164, based on high-precision Hubble Space Telescope photometry. We show that they all exhibit extended main-sequence turnoffs (MSTOs). The importance of age spreads and stellar rotation in reproducing the observations is investigated. The observed extended MSTOs cannot be explained by stellar rotation alone. Adopting an age spread of 35–50 Myr can alleviate this difficulty. We conclude that stars in these clusters are characterized by ranges in both their ages and rotation properties, but the origin of the age spread in these clusters remains unknown.

79 ASTRONOMY AND ASTROPHYSICS↗
DOE OSTI2017

Extended Main-sequence Turn-offs in Intermediate-age Star Clusters: Stellar Rotation Diminishes, but Does Not Eliminate, Age Spreads

Extended main-sequence turn-off (eMSTO) regions are a common feature in color–magnitude diagrams of young- and intermediate-age star clusters in the Magellanic Clouds. The nature of eMSTOs remains debated in the literature. The currently most popular scenarios are extended star formation activity and ranges of stellar rotation rates. Here we study details of differences in main-sequence turn-off (MSTO) morphology expected from spreads in age versus spreads in rotation rates, using Monte Carlo simulations with the Geneva syclist isochrone models that include the effects of stellar rotation. We confirm a recent finding of Niederhofer et al. that a distribution of stellar rotation velocities yields an MSTO extent that is proportional to the cluster age, as observed. However, we find that stellar rotation yields MSTO crosscut widths that are generally smaller than observed ones at a given age. We compare the simulations with high-quality Hubble Space Telescope data of NGC 1987 and NGC 2249, which are the two only relatively massive star clusters with an age of ∼1 Gyr for which such data is available. We find that the distribution of stars across the eMSTOs of these clusters cannot be explained solely by a distribution of stellar rotation velocities, unless the orientations of rapidly rotating stars are heavily biased toward an equator-on configuration. Under the assumption of random viewing angles, stellar rotation can account for ∼60% and ∼40% of the observed FWHM widths of the eMSTOs of NGC 1987 and NGC 2249, respectively. In contrast, a combination of distributions of stellar rotation velocities and stellar ages fits the observed eMSTO morphologies very well.

79 ASTRONOMY AND ASTROPHYSICS↗
DOE OSTI2022

Iron isotope evidence of an impact origin for main-group pallasites

Despite decades of work, the origin of pallasite meteorites has remained enigmatic. Long thought to be samples of the core-mantle boundary of differentiated asteroids, more recent studies have suggested a range of mechanisms for pallasite formation. These include olivine-metal mixing during a planetesimal collision and the intrusion of over-pressured core liquids into a planetesimal mantle. Establishing if the olivine and metal that comprise pallasites were once equilibrated at high temperature remains key to discriminating between these hypotheses. We determined the iron isotope compositions of olivine and metal in eleven main-group pallasites and found, in all cases, that olivine is isotopically lighter than metal. To interpret these data, we constrained the olivine-metal equilibrium Fe isotope fractionation with ab initio calculations and high temperature experiments. These independent approaches show that olivine preferentially incorporates the heavy isotopes of iron relative to metal. Our results demonstrate that pallasitic olivine and metal never achieved isotopic equilibrium with respect to iron. This precludes extended cooling at high temperature and is best reconciled with an impact origin for the main-group pallasites.

58 GEOSCIENCES↗
NASA NTRS1971

Apollo 14 mission: Inability to disconnect main bus A

During entry, the Apollo 14 spacecraft busses should have de-energized when the main bus-tie motor switches were switched to the off position. One motor switch did not transfer and main bus A remained energized until the battery bus-tie circuit breakers were opened after landing. Analysis revealed that residual catalyst caused the terminal pin seals to revert to a gummy state. Resulting reversion products then migrated to the motor commutator and caused brush degradation, increased and erratic commutator resistance, and reduced motor torque. The motor stalled when available motor torque was reduced below that required to drive through the maximum torque point of the switch.

Source record↗
NASA NTRS1972

Apollo 16 mission. Holes in canopy of main parachute

The occurrence of an anomaly during the Apollo 16 flight is discussed. The canopy of one of the recovered main parachutes had numerous small burn holes. An analysis of events following main parachute deployment which could cause the anomaly is presented. It is concluded that the burn holes in the parachute were the result of oxidizer being expelled when the plus-yaw engines were fired as the spacecraft was in the final phase of descent.

Source record↗
NASA NTRS1974

Turbopump configuration selection for the Space Shuttle main engine

Studies to define the optimum turbopump configurations for the Space Shuttle propulsion system are reported. For each propellant, two turbopumps - one low-pressure and one high-pressure - are needed to generate the high discharge pressures required for engine operation. The optimization of the four pumps resulted in the selection of an axial inducer type for both low-pressure pumps and in a three-stage centrifugal pump for the high-pressure hydrogen turbopump; meanwhile the oxygen pump features a double inlet main impeller. This impeller feeds the thrust chamber injector, as well as a preburner pump, which boosts the main impeller discharge pressure to the required preburner pressure. The interaction between engine performance and obtainable turbopump performance is discussed, and the reasons for the final selection of the turbine and pump types are presented.

Rothe, K.↗
NASA NTRS1975

Investigation of the Centaur boost pump overspeed condition at main engine shutdown on the Titan Centaur TC-2 flight

An investigation was conducted to evaluate a potential boost pump overspeed condition which could exist on the Titan/Centaur launch vehicle after main engine shut-off. Preliminary analyses indicated that the acceleration imparted to the unloaded boost pump-turbine assembly, caused by purging residual hydrogen peroxide from the turbine supply lines, could result in a pump-turbine overspeed. Previous test experience indicated that turbine damage occurs at speeds in excess of 75,000 rpm. Detailed theoretical analyses, in conjunction with pump tests, were conducted to establish the maximum pump-turbine speed at main engine shut-off. The analyses predicted a maximum speed of 68,000 rpm. Testing showed the pump-turbine speed to be 66,700 rpm in the overspeed condition. Inasmuch as both the analysis and tests showed the overspeed to be sufficiently less than the speed at which damage could occur, it was concluded that no corrective action would be required for the launch vehicle.

Baud, K. W.↗
NASA NTRS1976

F sub 2 peak electron densities in the main trough region of the ionosphere

A study of the main trough in the F2 region was made using observations from Alouette I and II. Parameters needed to predict the occurrence of the trough were determined from the many observations. These parameters were used to develop a modification factor for use with C.E.I.R. model of predicted MmF2. This modification factor reduced the C.E.I.R. model predicted NmF2 to more representative values of MmF2 in the main trough region.

Halcrow, B. W.↗
NASA NTRS1975

Space shuttle three main engine return to launch site abort

A Return-to-Launch-Site (RTLS) abort with three Space Shuttle Main Engines (SSME) operational was examined. The results are trajectories and main engine cutoff conditions that are approximately the same as for a two SSME case. Requiring the three SSME solution to match the two SSME abort eliminates additional crew training and is accomplished with negligible software impact.

Carter, J. F.↗
NASA NTRS1976

Design of the HEAO main bus shunt regulator

The High Energy Astronomy Observatory (HEAO) is being built for NASA by an American company. The general requirements concerning the HEAO main bus regulator are examined. The bus regulated voltage is 33 V, the maximum shunt current is 45 A, and the regulator output impedance is to be less than 0.5 Ohm from dc to 100 kHz. Loop gain design considerations for the main bus regulator are discussed and a description is given of the general device configuration. Attention is also given to regulator loop design and performance.

Middlebrook, R. D.↗
NASA NTRS1977

Space Shuttle Main Engine

Significant features of the Space Shuttle Main Engine (SSME) include a staged combustion power cycle, high area ratio nozzle expansion, throttling capability, and a computer operated control system. These main design features are discussed along with development test results.

Thompson, J. R., Jr.↗
NASA NTRS1977

Booster engines derived from the Space Shuttle Main Engine

Current vehicle studies of post-Space Shuttle vehicles have identified the potential need for a high-pressure booster engine using liquid oxygen/hydrocarbon fuel (RP-1) as propellants. Recent studies of the possibility of using Space Shuttle Main Engine (SSME) components for a high pressure LOX/RP-1 engine have resulted in several engine configurations which are based largely on SSME components. The current SSME thrust chamber is regeneratively cooled with hydrogen using a relatively low percentage of the total hydrogen flow. For a LOX/RP-1 application the SSME thrust chamber can be run at high pressures and be cooled with a relatively low hydrogen flow. In addition, the SSME oxygen pump, valves, and main injector components may be utilized for the booster engine. By using a majority of the current SSME engine components for the LOX/RE-1 booster engine, engine development time and cost can be significantly reduced compared to the development of a new engine.

Sobin, A. J.↗
NASA NTRS1979

Preflight status of the External Tank portion of the Space Shuttle Main Propulsion System

The development progress of the External Tank (ET) of the Shuttle Main Propulsion System (MPS) is described. 87% of ET propulsion components have satisfactorily completed qualification tests in preparation for the first Shuttle flight and their performance has been verified in the Main Propulsion Test Article (MPTA) firings of up to 100 seconds duration. The design changes in the LH2 tank pressurant diffuser, the LO2 feed system, and the ground test LO2 tank are discussed. Propellant loading information from MPTA tests may be used to predict loading operations and performance at KSC and VAFB, while ullage pressure profiles and boil-off rates during loading, chilldown rates, and final bulk density data have been obtained with geyser suppression evaluated and loading procedures established and verified. The MPTA test experience provided data to evaluate pressurization system and ET to Orbiter interface propellant performance noting thus that the fluid interface requirements will be satisfied for the first Shuttle flight. The Intertank inerting system was found to be effective in minimizing hazardous gas mixtures and full scale separation tests of the ET to Ground Umbilical Carrier Plate system were successfully completed.

Norquist, L.↗
NASA NTRS1979

Electrodeposition applications for the Space Shuttle Main Engine

Electrodeposition processes play a key role in the fabrication and in-service performance of the Space Shuttle Main Engine. Applications range from the electroforming of the main combustion chamber to the deposition of high-purity copper or gold for hydrogen embrittlement protection of susceptible materials of construction, or nickel for mechanical protection of foam insulated propellant ducts. Techniques for controlling electrolyte purity, verification of deposit integrity, and deposit profile and thickness are reported. The use of in-situ techniques (cell-plating) for localized plating and repair of damaged substrate materials are summarized.

Otousa, J. E.↗
NASA NTRS1979

Stellar evolution from the zero-age main sequence

A consistent set of 247 evolutionary sequences extending from the ZAMS to the red-giant branch is presented for Y from 0.10 to 0.40, Z from 0.00001 to 0.10, and masses of 0.55 to 6.90 solar masses. Each sequence is started from a homogeneous ZAMS model, and almost all are evolved to the base of the red-giant branch. It is shown that: (1) the relative position of the main sequence can be determined as a function of composition; (2) theoretical luminosity functions can be derived from the relative evolutionary time scales; (3) a dip in luminosity sometimes occurs at the base of the red-giant branch and is most pronounced at larger Z values; (4) metal-poor stars evolve farther up along the main sequence before turning off toward the red-giant branch; and (5) the onset of helium burning halts the evolution across the Hertzsprung gap for the most massive and most metal-poor models, so that the star remains blue during its phase of core-helium burning.

Mengel, J. G.↗
NASA NTRS1980

Space Shuttle Main Engine development /May 1980/

The Space Shuttle Main Engine is the most advanced liquid propellant rocket engine ever developed. During the last year, significant progess has been made toward the identification and solution of several design weaknesses. The initial two test series to certify the engine's readiness for manned flight have been completed, and additional test series are in progress. Operation of the total propulsion system has been demonstrated by a successful series of flight-simulation tests using the three-engine cluster Main Propulsion Test Article. The first set of flight engines has been acceptance tested for use in Shuttle Orbiter 102 (Columbia) for the first manned orbital flight in late 1980 or early 1981. Engine development is continuing with initial demonstrations of full-power level (109%) operation capability.

Sanchini, D. J.↗
NASA NTRS1981

Compensating linkage for main rotor control

A compensating linkage for the rotor control system on rotary wing aircraft is described. The main rotor and transmission are isolated from the airframe structure by clastic suspension. The compensating linkage prevents unwanted signal inputs to the rotor control system caused by relative motion of the airframe structure and the main rotor and transmission.

Jeffery, P. A. E.↗
NASA NTRS1981

Total main rotor isolation system analysis

Requirements, preliminary design, and verification procedures for a total main rotor isolation system at n/rev are presented. The fuselage is isolated from the vibration inducing main rotor at one frequency in all degrees of freedom by four antiresonant isolation units. Effects of parametric variations on isolation system performance are evaluated.

Sankewitsch, V.↗