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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 1,459 records · Page 81
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

The satellite power system - Assessment of the environmental impact on middle atmosphere composition and on climate

Numerical models were developed to calculate the total deposition of watervapor, hydrogen, CO2, CO, SO2, and NO in the middle atmosphere from operation of heavy lift launch vehicles (HLLV) used to build a satellite solar power system (SPS). The effects of the contaminants were examined for their effects on the upper atmosphere. One- and two-dimensional models were formulated for the photochemistry of the upper atmosphere and for rocket plumes and reentry. An SPS scenario of 400 launches per year for 10 yr was considered. The build-up of the contaminants in the atmosphere was projected to have no significant effects, even at the launch latitude. Neither would there by any dangerous ozone depletion. It was found that H, OH, and HO2 species would double in the thermosphere. No measurable changes in climate were foreseen.

Whitten, R. C.↗
NASA NTRS1982

NDE of simulated Space Shuttle tile disbonds

A technique which involves the use of ultrasonic Lamb waves for assaying the structural integrity of adhesive bonds between layered materials on thin metal plates, particularly with regard to the Shuttle TPS, is presented. The Lamb waves are generated by a pulse impact, resulting in surface waves propagating radially at 2.4 mm/microsec. Trials were performed with the sound waves applied to samples, of aluminum similar to the Orbiter external skin, which were coated with Teflon and a RTV silicone screed. The goal was to detect localized debonded areas or potentially debonded areas, which, during reentry, could result in blistering of the aluminum skin. The ultrasonic probes are described, noting the usage of broadband ultrasonic harmonics and a minicomputer processor. The testing system was found to accurately identify weakened bonds by the ratio of high and low frequency component areas of the received signal of the Lamb waves sent across the surface.

Ahlberg, L.↗
NASA NTRS1983

On the flight derived/aerodynamic data base performance comparisons for the NASA Space Shuttle entries during the hypersonic regime

Aerodynamic performance data from the first four Shuttle reentry flights are compared with preflight predictions covering hypersonic longitudinal mode down to Mach 2. The extraction of the flight coefficients, as measured by the spacecraft angular rates and the linear accelerations, derived from the inertial measurement unit, the best estimate trajectory, and the remotely measured atmosphere are discussed. The ground predictions were developed from 30,000 hr of wind tunnel testing. Actual flight data are presented for 80-260 kft, from Mach 2-26, comprising the dynamic pressure, the vehicle air relative attitude angles, control surface deflections, reaction jet activity, and body axis rates and accelerations. The second and fourth flights gave results which deviated from predictions between 230-260 kft. The accuracy limits of the derived atmospheric densities are considered, together with potential data base updates in the light of limitations imposed on the corrections by available flight data.

Findlay, J. T.↗
NASA NTRS1983

An evaluation of Space Shuttle Orbiter forward fuselage surface pressures - Comparison with wind tunnel and theoretical predictions

In order for ground-based pressure distribution techniques to be verified by the actual performance of the Space Shuttle Orbiter in flight, a comparative study of flight pressure data and both wind tunnel and computational data is presented. The flight pressure data, obtained from measurements on the Orbiter's surface during atmospheric reentry, are part of the overall Orbiter flight data system designated Development Flight Instrumentation. Also given is an analysis of the Orbiter pressure data system, including its transducers, their behavior, and their calibration. The two analyses are the bases of an error assessment calculation for the flight data, as well as an explanation of any discrepancies between flight and ground-based data.

Bradley, P. F.↗
NASA NTRS1983

New implicit boundary procedures - Theory and applications

Analytical techniques for the application of implicit boundary conditions for inviscid flows to shock and body boundary layer conditions involving the Euler equations are presented. The theory of characteristics is used to update boundary points with spatial second order accuracy. The method is useful for implicit schemes which feature approximate factorization, and as such is incorporated into an existing PNS code. Examples are provided in terms of flows over a cone, over a maneuverable reentry vehicle, and over a finned vehicle. Improvements in the convergence rate are demonstrated for the conical flow solutions.

Rai, M. M.↗
NASA NTRS1982

The first plants to fly on Shuttle

The methods and results are presented concerning experiments using the first plants to make a journey for scientific purposes in earth orbit on board Space Shuttles 2 and 3. These experiments were conducted in order to validate the culture system planned for use in a Spacelab-1 experiment involving the growth and kinetics of sunflower seedlings. The experimental flight package is described and the preparation steps taken prior to the flights are discussed. The conditions to which the plants were exposed during the flights are examined in detail, focusing on the temperature profile and the gravitational forces during reentry to landing.

Brown, A. H.↗
NASA NTRS1982

Short hyperdynamic profiles influence primate temperature regulation

Primates have been shown to be sensitive to hyperdynamic fields. That is, when exposed to + 2Gz, body temperature falls. The purpose of this study was to examine the relative sensitivity of these animals to short centrifugation profiles which mimic the gravitational envelope seen on the Space Shuttle during launch (8 minutes, 2.9 Gz max) and re-entry (19 min, 1.7 Gz max). Four loosely restrained squirrel monkeys, isolated from additional external stimuli, were exposed to these profiles. During launch simulation, the temperatures never fell markedly below control levels. However, subsequent to return to 1G, the recovery phase showed decreases in body temperature in all four animals averaging 0.4 C over the next 10 to 15 minutes. The two animals exposed to the reentry profile showed decreases in body temperature within five minutes of the onset of centrifugation. Maximum fall in body temperature was reached by the end of the centrifugation phase and averaged 0.7 C. Thus, the temperature regulation system of this primate is sensitive to short hyperdynamic field exposures.

Fuller, C. A.↗
NASA NTRS1983

Effects of nonequilibrium and surface catalysis on Shuttle heat transfer - A review

It is pointed out that the Space Shuttle Orbiter is a hypersonic glide reentry vehicle which spends much of its entry time at relatively tenuous altitudes in which chemical nonequilibrium predominates in the shock layer. On the windward side, dissociation nonequilibrium exists in the inviscid layer and recombination nonequilibrium exists in the boundary layer. The present investigation is concerned with an evaluation of various flowfield predictions, taking into account a comparison of equilibrium and nonequilibrium flowfields coupled with reacting axisymmetric analog boundary-layer solutions and the results of viscous-shock-layer solutions with flight temperature/heat-flux measurements near the windward centerline for the Shuttle flights STS-2, STS-3, and STS-5.

Scott, C. D.↗
NASA NTRS1983

Atmospheric determination for Shuttle aerodynamic studies

Evaluation of the aerodynamic performance of the Shuttle during atmospheric reentry requires a determination of the free-stream atmospheric properties along the entry path. This determination must be of the best possible accuracy in order to fully utilize the Shuttle as an aerodynamic flight research vehicle. To accomplish this, two Shuttle Orbiter experiments, the Shuttle Upper Atmosphere Mass Spectrometer (SUMS) and the Shuttle Entry Air Data System (SEADS), are being developed to provide onboard measurements. SUMS will measure freestream parameters in the high altitude (above 90 km), high Mach number (M above 20) regions where conventional static pressure measurements are not available. SEADS will provide research quality data below about 90 km. Since these two experiments were not installed for the Shuttle developmental flights, an alternate method was needed to determine the freestream atmospheric properties along the entry trajectory. The method which was developed is described with a discussion of the results from the first five Shuttle flights.

Price, J. M.↗
NASA NTRS1983

Developing mass spectrometric techniques for boundary layer measurement in hypersonic high enthalpy test facilities

Thermodynamic flow properties of gases in the boundary layer or the flowfield have been mainly deduced from pressures and temperatures measured on a model. However, further progress with respect to an understanding of these properties requires a more complete characterization of the layer including determination of the gas composition and chemistry. Most attempts to measure boundary layer chemistry involve the employment of a mass spectrometer and an associated gas sampling system. The three major limiting factors which must be addressed for species measurement in aerothermodynamic investigations on models at reentry stream velocities, are gas sampling effects, instrument limitations, and problems with data acquisition. The present investigation is concerned with a concentrated effort to quantitatively identify and correct for instrument and sampling system effects, and to develop a miniaturized high performance mass spectrometer for on-model real-time analysis of the boundary layer and its associated atmosphere.

Wood, G. M., Jr.↗
NASA NTRS1983

Research on the adaptation of skeletal muscle to hypogravity Past and future directions

The results of previous research on the cellular effects of microgravity on rat tissue are reviewed and areas of future necessary research are identified. The rats were flown on board Cosmos 605, 782, and 936. Postflight tissue analyses revealed increases in connective tissue cells and focal disruption of muscle fibers due to the microgravity environment of space. Evidence has been found for muscular and neural changes occurring as a result of reentry stresses. It is suggested that a data base be established for quantizing muscle function with electromyography, measurements of force output, and length measurement. The data can serve as a reference for comparisons with data obtained in orbiting laboratories such as the Spacelab. The experiments will have a goal of defining and preventing the mechanism of neuromuscular atrophy.

Riley, D. A.↗
NASA NTRS1983

Etiological factors in space motion sickness

The human susceptibility to motion sickness during exposure to sudden-stop stimulation as a function of gravitoinertial force level is studied. It is determined that susceptibility is greatly enhanced, both with eyes-closed and eyes-open, for zero-g and 2-g conditions in parabolic flight compared with 1-g test conditions. It is argued that this change in susceptibility is related to alterations in vestibulo-occular function which result from variations in gravitoinertial force level, the altered patterns of otolithic activity resulting during variations in gravitoinertial force level, and the altered canal-otolith response synergies that result during exposure to gravitoinertial force levels greater or less than terrestrial levels. These factors are found to be related to the etiology of space motion sickness and to the alterations in performance and vestibular function that are experienced by astronauts during reentry. An explanation is presented for the decrease in susceptibility to motion sickness exhibited by the Skylab astronauts inflight and for some period postflight during exposure to cross-coupled angular accelerations.

Lackner, J. R.↗
NASA NTRS1983

Orbit keeping attitude control for space station

It is pointed out that on-orbit configuration variability is expected to be a characteristic of a space station. The implementation of such a chracteristic will present reboost and thruster control system designers with a number of new challenges. The primary requirement for the space station orbit reboost (or orbit keeping) system is to ensure system viability for extended duration and prevent an uncontrolled reentry as with Skylab. For a station in a low earth orbit, earodynamic drag will be sufficient to cause relatively quick orbit altitude decay. A propulsion system is, therefore, needed to counteract the aerodynamic drag forces and to boost the vehicle to the desired orbit altitudes. A description is given of a typical reboost operational procedure and propellant requirements. Attention is given to thruster control systems, and aspects of reboost guidance.

Barrows, D.↗
NASA NTRS1983

Effects of weightlessness on body composition in the rat

The effects of weightlessness on the body composition of rats were investigated using 5 male rats exposed to 18.5 days of weightlessness on the COSMOS 1129 biosatellite and killed after reentry. The animals were immediately dissected and the three major body divisions (musculoskeletal system, skin, and pooled viscera) were analyzed for fat, water, solids, and six elements. These results were determined as percentages of the fat-free body or its components and then compared with two groups of terrestrial controls, one of which was subjected to a flight simulation in a spacecraft mock-up while the other was under standard vivarium conditions. Compared with the control groups, the flight group was found to exhibit a reduced fraction of total body water, a net shift of body water from skin to viscera, a marked diminution in the fraction of extracellular water in the fat-free body, a marked reduction in the fraction of bone mineral, no change in the quantity of stored fat or adrenal masses, and a net increase in total muscle mass as indicated by total body creatine, protein, and body cell mass.

Pitts, G. C.↗
NASA NTRS1983

Trends in shuttle entry heating from the correction of flight test maneuvers

A new technique was developed to systematically expand the aerothermodynamic envelope of the Space Shuttle Protection System (TPS). The technique required transient flight test maneuvers which were performed on the second, fourth, and fifth Shuttle reentries. Kalman filtering and parameter estimation were used for the reduction of embedded thermocouple data to obtain best estimates of aerothermal parameters. Difficulties in reducing the data were overcome or minimized. Thermal parameters were estimated to minimize uncertainties, and heating rate parameters were estimated to correlate with angle of attack, sideslip, deflection angle, and Reynolds number changes. Heating trends from the maneuvers allow for rapid and safe envelope expansion needed for future missions, except for some local areas.

Hodge, J. K.↗
NASA NTRS1983

Orbit determination and prediction study for Dynamic Explorer 2

Definitive orbit determination accuracy and orbit prediction accuracy for the Dynamic Explorer-2 (DE-2) are studied using the trajectory determination system for the period within six weeks of spacecraft reentry. Baseline accuracies using standard orbit determination models and methods are established. A promising general technique for improving the orbit determination accuracy of high drag orbits, estimation of random drag variations at perigee passages, is investigated. This technique improved the fit to the tracking data by a factor of five and improved the solution overlap consistency by a factor of two during a period in which the spacecraft perigee altitude was below 200 kilometers. The results of the DE-2 orbit predictions showed that improvement in short term prediction accuracy reduces to the problem of predicting future drag scale factors: the smoothness of the solar 10.7 centimeter flux density suggests that this may be feasible.

Smith, R. L.↗
NASA NTRS1983

Evaluation of non-intrusive flow measurement techniques for a re-entry flight experiment

This study evaluates various non-intrusive techniques for the measurement of the flow field on the windward side of the Space Shuttle orbiter or a similar reentry vehicle. Included are linear (Rayleigh, Raman, Mie, Laser Doppler Velocimetry, Resonant Doppler Velocimetry) and nonlinear (Coherent Anti-Stokes Raman, Laser-Induced Fluorescence) light scattering, electron-beam fluorescence, thermal emission, and mass spectroscopy. Flow-field properties were taken from a nonequilibrium flow model by Shinn, Moss, and Simmonds at the NASA Langley Research Center. Conclusions are, when possible, based on quantitative scaling of known laboratory results to the conditions projected. Detailed discussion with researchers in the field contributed further to these conclusions and provided valuable insights regarding the experimental feasibility of each of the techniques.

Miles, R. B.↗
NASA NTRS1984

Effect of space exposure of some epoxy matrix composites on their thermal expansion and mechanical properties (A0138-8)

This experiment has three objectives. The first and main objective is to detect a possible variation in the coefficient of thermal expansion of composite samples during a 1-year exposure to the near-Earth orbital environment. A second objective is to detect a possible change in the mechanical integrity of composite products, both simple elements and honeycomb sandwich assemblies. A third objective is to compare the behavior of two epoxy resins commonly used in space structural production. The experimental approach is to passively expose samples of epoxy matrix composite materials to the space environment and to compare preflight and postflight measurements of mechanical properties. The experiment will be located in one of the three FRECOPA (French cooperative payload) boxes in a 12-in.-deep peripheral tray that contains nine other experiments from France. The FRECOPA box will protect the samples from contamination during the launch and reentry phases of the mission. The coefficients of thermal expansion are measured on Earth before and after space exposure.

Elberg, R.↗