A plate study associated with reflector dynamics of the Rosman-I antenna
Plate study associated with reflector dynamics of Rosman I antenna
STRUCTURAL DYNAMICS↗
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Scientific Studies in Association with the Halogen Occultation Experiment
This work examines measurements of ozone, NO, NO2, and HCl made by the Halogen Occultation Experiment (HALOE) to track chemical change in the stratosphere. In addition, HALOE observations of two long-lived species, HF and CH4, are used as tracers to distinguish between change due to transport processes and change due to chemistry. The first study investigates the response of NO(x), (NO and NO2) and ozone to the presence of large amounts of sulfate aerosol in the stratosphere following the 1991 eruption of Mount Pinatubo. As the Pinatubo aerosol cleared the atmosphere at 17 mb (about 27-28 km), the partitioning of total reactive nitrogen shifted more toward NO(x), and ozone amounts declined. This trend is opposite that observed at lower altitudes. The second study examines the chemical aftermath of severe ozone depletion over Antarctica in spring. When ozone levels drop to a threshold amount (about 1 ppm near 20 km), the partitioning of the total chlorine family shifts rapidly from reactive species to the reservoir molecule HCl. This sudden repartitioning shuts down further ozone loss and may be significant as filaments of air peel off the polar vortex and mix with mid-latitude air.
Mickley, Lorretta J.↗
Carrier lifetime measurements and recombination characteristics in silicon and studies phenomena associated with radiation induced defect levels
Carrier lifetime measurements and recombination characteristics in silicon and radiation induced defect levels
SILICON↗
Rigidization of a 1.52-meter diameter inflatable solar concentrator in vacuum with associated material studies and fabrication techniques Final report
Foam rigidizing for inflatable paraboloidal solar collector
FOAMED MATERIAL↗
Scientific studies in association with the Shuttle Solar Backscatter Ultraviolet (SSBUV) project
During the past reporting period efforts focused on performing detailed comparisons between measurements made by the SBUV/2 V instruments carried on NOAA-9 and NOAA-11 and the first three flights of the Shuttle Solar Backscatter Ultraviolet (SSBUV) project. The quantities to be compared are the measurables, being the ratio of emergent radiance (I) in the vertical direction to the incoming solar irradiance (F). The backscatter albedo, A(w,j), was defined by: A(w,j) = I(w,j)/F(w,j) where w = 1,2,..., 12 refers to wavelength, and j indicates the instrument and flight on which the data were obtained. The comparisons to be made are NOAA-9 to SSBUV-1, NOAA-11 to SSBUV-2, and NOAA-11 to SSBUV-3. For the comparisons the N-values contained in the data files supplied by GSFC were converted to albedos via: A(w,j) = 10(exp N(w,j)/100). The comparisons described were designed to characterize the differences between the NOAA and SSBUV data sets.
Frederick, John E.↗
Noise Budget for the X-Ray Microcalorimeter Spectrometer (XMS) Core Array
The purpose of this document is to present and archive the noise budget for the XMS detector, in order, at this stage in mission planning, to learn the scale of the requirements placed on the other instrument subsystems. This document mainly concerns the core array, specifically the baseline version that emerged from the trade studies associated with the ESA Phase A study report. Qualitative extension to the Hydra approach to the outer array is included at the end.
Kilbourne, Caroline Anne↗
Rendezvous and Docking Strategy for Crewed Segment of the Asteroid Redirect Mission
This paper will describe the overall rendezvous, proximity operations and docking (RPOD) strategy in support of the Asteroid Redirect Crewed Mission (ARCM), as part of the Asteroid Redirect Mission (ARM). The focus of the paper is on the crewed mission phase of ARM, starting with the establishment of Orion in the Distant Retrograde Orbit (DRO) and ending with docking to the Asteroid Redirect Vechicle (ARV). The paper will detail the sequence of maneuvers required to execute the rendezvous and proximity operations mission phases along with the on-board navigation strategies, including the final approach phase. The trajectories to be considered will include target vehicles in a DRO. The paper will also discuss the sensor requirements for rendezvous and docking and the various trade studies associated with the final sensor selection. Building on the sensor requirements and trade studies, the paper will include a candidate sensor concept of operations, which will drive the selection of the sensor suite; concurrently, it will be driven by higher level requirements on the system, such as crew timeline constraints and vehicle consummables. This paper will address how many of the seemingly competing requirements will have to be addressed to create a complete system and system design. The objective is to determine a sensor suite and trajectories that enable Orion to successfully rendezvous and dock with a target vehicle in trans lunar space. Finally, the paper will report on the status of a NASA action to look for synergy within RPOD, across the crewed and robotic asteroid missions.
Hinkel, Heather D.↗
Training Space Surgeons for Missions to the Moon and Mars
Over a period of 4 years, several working groups reviewed the provisions for medical care in low earth orbit and for future flights such as to the Moon and Mars. More than 60 medical experts representing a wide variety of clinical backgrounds participated in the working groups. They concluded that NASA medical training for long-duration missions, while critical to success, is currently aimed at short-term skill retention. They noted that several studies have shown that skills and knowledge deteriorate rapidly in the absence of adequate sustainment training. American Heart Association studies have shown that typically less than twenty-five percent of learned skills remain after 6 to 8 months. In addition to identifying the current training deficiencies, the working groups identified additional skill and knowledge sets required for missions to the Moon and Mars and curricula were developed to address inadequacies. Space medicine care providers may be categorized into 4 types based on health care responsibilities and level of education required. The first 2 types are currently recognized positions within the flight crew: crew medical officers and astronaut-physician. The crew medical officer (CMO), a non-medically trained astronaut crewmember, is given limited emergency medical technician-like training to provide medical care on orbit. Many of hidher duties are carried out under the direction of a ground-based flight surgeon in mission control. Second is the astronaut- physician whose primary focus is on mission specialist duties and training, and who has very limited ability to maintain medical proficiency. Two new categories are recommended to complete the 4 types of care providers primarily to address the needs of those who will travel to the Moon and Mars. Physician astronaut - a physician, who in addition to being a mission specialist, will be required to maintain and enhance hidher medical proficiency while serving as an astronaut. Space surgeon - a physician astronaut given special training to address the unique health care requirements envisioned for expeditions such as those to Mars.
Pool, S. L.↗
Generic hypersonic inlet module analysis
A computational study associated with an internal inlet drag analysis was performed for a generic hypersonic inlet module. The purpose of this study was to determine the feasibility of computing the internal drag force for a generic scramjet engine module using computational methods. The computational study consisted of obtaining two-dimensional (2D) and three-dimensional (3D) computational fluid dynamics (CFD) solutions using the Euler and parabolized Navier-Stokes (PNS) equations. The solution accuracy was assessed by comparisons with experimenal pitot pressure data. The CFD analysis indicates that the 3D PNS solutions show the best agreement with experimental pitot pressure data. The internal inlet drag analysis consisted of obtaining drag force predictions based on experimental data and 3D CFD solutions. A comparative assessment of each of the drag prediction methods is made and the sensitivity of CFD drag values to computational procedures is documented. The analysis indicates that the CFD drag predictions are highly sensitive to the computational procedure used.
Cockrell, Charles E., Jr.↗
Generic Hypersonic Inlet Module Analysis
A computational study associated with an internal inlet drag analysis was performed for a generic hypersonic inlet module. The purpose of this study was to determine the feasibility of computing the internal drag force for a generic scramjet engine module using computational methods. The computational study consisted of obtaining two-dimensional (2D) and three-dimensional (3D) computational fluid dynamics (CFD) solutions using the Euler and parabolized Navier-Stokes (PNS) equations. The solution accuracy was assessed by comparisons with experimental pitot pressure data. The CFD analysis indicates that the 3D PNS solutions show the best agreement with experimental pitot pressure data. The internal inlet drag analysis consisted of obtaining drag force predictions based on experimental data and 3D CFD solutions. A comparative assessment of each of the drag prediction methods is made and the sensitivity of CFD drag values to computational procedures is documented. The analysis indicates that the CFD drag predictions are highly sensitive to the computational procedure used.
Cockrell, Chares E., Jr.↗
NACA/NASA supersonic flight research
The use of experimental and testbed vehicles and their contributions to fundamental problem solving and overall vehicle characteristics are presented. A chronological description of aircraft from the first supersonic flight in the X-1 through the development of the F-100 series, the X-15, and the B-1 is given. One of the early significant contributions made was the development of the all-moving stabilizer that solved the problem associated with high-speed tuck and the trim requirements of entry into the supersonic regime. Some wind tunnel/flight drag characteristics studies associated with the B-1 bomber involving flexibility effects and wind tunnel effects are shown. Finally, the evolution of digital systems to enhance maintainability and reliability and to reduce the work load in the cockpit are described.
Ayers, T. G.↗
Progress of Space Studies of the Earth Surface, Meteorology, and Climate 1992- 1993
This report briefly summarizes the progress made by satellite-dependent systems that are necessary to accomplish global earth monitoring and associated studies of the interactions between the earth's atmosphere, land surface, and ocean.
Halpern, D.↗
An Open-Science Approach to Address Individual Response to Simulated GCR In Genetically Diverse Populations of Mice and Humans
This project addresses the challenge of understanding and predicting individual radiation sensitivity by integrating genetics, demographics and biomarker characteristics across species (mice and humans). We hypothesize that ex vivo DNA repair response to GCR components is a central determinant of cancer risk from space radiation and can serve as a biomarker of radiation risk in combination with genetics. Automated image quantification of 53BP1+ radiation-induced foci (RIF) during the first 4-48 h post-irradiation was performed as a function of dose and LET in non-immortalized primary skin fibroblasts derived from 76 mice across 15 strains (5 inbred reference strains and 10 collaborative-cross strains) exposed to X rays (0.1, 1 and 4 Gy), 350 MeV/n 40Ar and 600 MeV/n 56Fe (1.1 and 3 particles/100sq. μm), as well as in peripheral blood mononuclear cells (PBMCs) from 768 healthy donors (matched ethnicity, 50/50 male/female, 18-70 years old) exposed to gamma rays (0.1 and 1 Gy), 350 MeV/n 28Si, 350 MeV/n 40Ar and 600 MeV/n 56Fe (1.1 and 3 particles/100sq. μm). A genome-wide association study (GWAS) was performed on the mouse strains between DNA damage responses to space radiation and single nucleotide polymorphisms (SNPs). We found SNPs, which were significantly associated to the RIF phenotype, mapped to genes and pathways that are functionally linked to health hazards for deep space exploration (e.g. carcinogenesis, nervous system damage and immune dysfunction). Some of these SNPs were located within protein coding regions, potentially interfering with protein functions and providing promising genetic targets for countermeasures. We also found correlations between both spontaneous and radiation-induced DNA damage and SNPs mapped to pathways associated with cellular metabolism. GWAS is undergoing for the human data. All data have been made available via the NASA Space Biology Open-Science database (genelab.nasa.gov) and we will discuss how various genomic and transcriptomic datasets can be accessed for modeling and integrated using machine learning methods for discovering new radiation biology.
Sylvain V Costes↗
Methods for Characterizing Fine Particulate Matter Using Satellite Remote-Sensing Data and Ground Observations: Potential Use for Environmental Public Health Surveillance
This study describes and demonstrates different techniques for surfacing daily environmental / hazards data of particulate matter with aerodynamic diameter less than or equal to 2.5 micrometers (PM2.5) for the purpose of integrating respiratory health and environmental data for the Centers for Disease Control and Prevention (CDC s) pilot study of Health and Environment Linked for Information Exchange (HELIX)-Atlanta. It described a methodology for estimating ground-level continuous PM2.5 concentrations using B-Spline and inverse distance weighting (IDW) surfacing techniques and leveraging National Aeronautics and Space Administration (NASA) Moderate Resolution Imaging Spectrometer (MODIS) data to complement The Environmental Protection Agency (EPA) ground observation data. The study used measurements of ambient PM2.5 from the EPA database for the year 2003 as well as PM2.5 estimates derived from NASA s satellite data. Hazard data have been processed to derive the surrogate exposure PM2.5 estimates. The paper has shown that merging MODIS remote sensing data with surface observations of PM2.5 not only provides a more complete daily representation of PM2.5 than either data set alone would allow, but it also reduces the errors in the PM2.5 estimated surfaces. The results of this paper have shown that the daily IDW PM2.5 surfaces had smaller errors, with respect to observations, than those of the B-Spline surfaces in the year studied. However the IDW mean annual composite surface had more numerical artifacts, which could be due to the interpolating nature of the IDW that assumes that the maxima and minima can occur only at the observation points. Finally, the methods discussed in this paper improve temporal and spatial resolutions and establish a foundation for environmental public health linkage and association studies for which determining the concentrations of an environmental hazard such as PM2.5 with good accuracy levels is critical.
Al-Hamdan, Mohammad Z.↗
A History of Collapse Factor Modeling and Empirical Data for Cryogenic Propellant Tanks
One of the major technical problems associated with cryogenic liquid propellant systems used to supply rocket engines and their subassemblies and components is the phenomenon of propellant tank pressurant and ullage gas collapse. This collapse is mainly caused by heat transfer from ullage gas to tank walls and interfacing propellant, which are both at temperatures well below those of this gas. Mass transfer between ullage gas and cryogenic propellant can also occur and have minor to significant secondary effects that can increase or decrease ullage gas collapse. Pressurant gas is supplied into cryogenic propellant tanks in order to initially pressurize these tanks and then maintain required pressures as propellant is expelled from these tanks. The net effect of pressurant and ullage gas collapse is increased total mass and mass flow rate requirements of pressurant gases. For flight vehicles this leads to significant and undesirable weight penalties. For rocket engine component and subassembly ground test facilities this results in significantly increased facility hardware, construction, and operational costs. "Collapse Factor" is a parameter used to quantify the pressurant and ullage gas collapse. Accurate prediction of collapse factors, through analytical methods and modeling tools, and collection and evaluation of collapse factor data has evolved over the years since the start of space exploration programs in the 1950 s. Through the years, numerous documents have been published to preserve results of studies associated with the collapse factor phenomenon. This paper presents a summary and selected details of prior literature that document the aforementioned studies. Additionally other literature that present studies and results of heat and mass transfer processes, related to or providing important insights or analytical methods for the studies of collapse factor, are presented.
deQuay, Laurence↗
A comparison between conventional and LANDSAT based hydrologic modeling: The Four Mile Run case study
Models designed to support the hydrologic studies associated with urban water resources planning require input parameters that are defined in terms of land cover. Estimating the land cover is a difficult and expensive task when drainage areas larger than a few sq. km are involved. Conventional and LANDSAT based methods for estimating the land cover based input parameters required by hydrologic planning models were compared in a case study of the 50.5 sq. km (19.5 sq. mi) Four Mile Run Watershed in Virginia. Results of the study indicate that the LANDSAT based approach is highly cost effective for planning model studies. The conventional approach to define inputs was based on 1:3600 aerial photos, required 110 man-days and a total cost of $14,000. The LANDSAT based approach required 6.9 man-days and cost $2,350. The conventional and LANDSAT based models gave similar results relative to discharges and estimated annual damages expected from no flood control, channelization, and detention storage alternatives.
Ragan, R. M.↗
LOTUS Highlights on Ozone Trend Analyses and Phase 3 Direction
LOTUS (Long-term Ozone Trends and Uncertainties in the Stratosphere) is a SPARC (Stratosphere-troposphere Processes And their Role in Climate)-sponsored effort to foster collaboration between established and early career scientists around the world, with expertise in ozone observations, modeling, and trend tools, with an aim toward innovating new climate research that meets the needs of the ozone trends community and provides vital contributions to the WMO Assessment in an organized and cohesive way. Here we will summarize recent studies associated with the LOTUS effort that perform trend analyses on both total column and vertical profiles of ozone. The main findings of the derived trends from both observations and chemistry climate models have important implications for the status of the ozone layer as they pertain to the efficacy of the Montreal Protocol. These results also present new questions and knowledge gaps that will be outlined as areas of future study in Phase 3 of the LOTUS effort over the next few years to inform the next Assessment.
LOTUS↗
Systems simulation for an airport trailing vortex warning system
The approach, development, and limited system studies associated with a system simulation for an Airport Trailing Vortex Warning System are documented. The usefulness is shown of a systems engineering approach to the problem of developing a system, as dictated by aircraft vortices, which will increase air-traffic flow in the takeoff/landing corridors of busy airports while maintaining the required safety factor for each operation. The simulation program has been developed in a modular form which permits new, more sophisticated component models, when they become available and are required, to be incorporated into the program with a minimum of program modifications. This report documents a limited system study that has been performed using this Total System Simulation Model. The resulting preliminary system requirements, conclusions, and recommendations are given.
Jeffreys, H. B.↗