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This report covers technical progress during the first quarter of the second year of NASA Sun-Earth Connections Theory Program (SECTP). SAIC and the University of California, Irvine (UCI) have conducted research into theoretical modeling of active regions, the solar corona, and the inner heliosphere, using the MHD model.
The VACCG team is comprised of engineers at Virginia Tech who specialize in the subject areas of combustion physics, chemical kinetics, dynamics and controls, and signal processing. Currently, the team's work on this NRA research grant is designed to determine key factors that influence combustion control performance through a blend of theoretical and experimental investigations targeting design and demonstration of active control for three different combustors. To validiate the accuracy of conclusions about control effectiveness, a sequence of experimental verifications on increasingly complex lean, direct injection combustors is underway. During the work period January 1, 2002 through October 15, 2002, work has focused on two different laboratory-scale combustors that allow access for a wide variety of measurements. As the grant work proceeds, one key goal will be to obtain certain knowledge about a particular combustor process using a minimum of sophisticated measurements, due to the practical limitations of measurements on full-scale combustors. In the second year, results obtained in the first year will be validated on test combustors to be identified in the first quarter of that year. In the third year, it is proposed to validate the results at more realistic pressure and power levels by utilizing the facilities at the Glenn Research Center.
The Gamma Ray Large Area Space Telescope (GLAST), currently set for launch in the first quarter of 2007, will consist of two instruments, the GLAST Burst Monitor (GBM) and the Large Area Telescope (LAT). One of the goals of the GBM is to identify and locate gamma-ray bursts using on-board software. The GLAST observatory can then be re-oriented to allow observations by the LAT. A Bayesian analysis will be used to distinguish gamma-ray bursts from other triggering events, such as solar flares, magnetospheric particle precipitation, soft gamma repeaters (SGRs), and Cygnus X-1 flaring. The trigger parameters used in the analysis are the burst celestial coordinates, angle from the Earth's horizon, spectral hardness, and the spacecraft geomagnetic latitude. The algorithm will be described and the results of testing will be presented.
This is the First Quarterly Report for the newly reconstituted Aerospace Safety Advisory Panel (ASAP). The NASA Administrator rechartered the Panel on November 18,2003, to provide an independent, vigilant, and long-term oversight of NASA's safety policies and programs well beyond Return to Flight of the Space Shuttle. The charter was revised to be consistent with the original intent of Congress in enacting the statute establishing ASAP in 1967 to focus on NASA's safety and quality systems, including industrial and systems safety, risk-management and trend analysis, and the management of these activities.The charter also was revised to provide more timely feedback to NASA by requiring quarterly rather than annual reports, and by requiring ASAP to perform special assessments with immediate feedback to NASA. ASAP was positioned to help institutionalize the safety culture of NASA in the post- Stafford-Covey Return to Flight environment.
Combustion of metals with CO2 has been identified as a possible propellant for Mars ascent applications. CO2 could be condensed from the Martian atmosphere, reducing the amount of propellant that must be transported from Earth. An attractive feature of this approach compared to other in situ propellant concepts is that no chemical processing on Mars is required. Magnesium has been identified as the most promising metal for this application because it ignites and burns easily in CO2. Preliminary systems studies indicate a 2 to 1 delivered mass advantage for Mg ascent propulsion using in situ C02, as compared to a conventional storable propellant system. The Propulsion Research Center at MSFC is undertaking an experimental investigation of magnesium powder combustion with CO2 in order to provide fundamental data on the combustion performance of Mg powder + CO2 mixtures needed to assess the feasibility of developing a practical Mg powder + CO2 rocket engine. Initial combustion experiments will be carried out in a small scale atmospheric pressure dump combustor. Effects of varying the Mg particle size, firing rate and O/F ratio on combustion stability and efficiency will be investigated. The combustion process will be characterized by optical flame measurements and extraction of combustion product samples. The experimental facility is currently being prepared and combustion experiments will begin during the first quarter of 2005. The final paper will describe the test facility and initial experimental results.
A series of NASA/Boeing cooperative low speed wind tunnel tests was conducted in the National Transonic Facility (NTF) between 2003 and 2004 using a semi-span high lift model representative of the 777-200 aircraft. The objective of this work was to develop the capability to acquire high quality, low speed (flaps down) wind tunnel data at up to flight Reynolds numbers in a facility originally optimized for high speed full span models. In the course of testing, a number of facility and procedural improvements were identified and implemented. The impact of these improvements on key testing metrics data quality, productivity, and so forth - was significant, and is discussed here, together with the relevance of these metrics as applied to cryogenic wind tunnel testing in general. Details of the improvements at the NTF are discussed in AIAA-2006-0508 (Recent Improvements in Semi-span Testing at the National Transonic Facility). The development work at the NTF culminated with validation testing of a 787-8 semi-span model at full flight Reynolds number in the first quarter of 2006.
This paper presents an update to the methods and procedures used in Direct Field Acoustic Testing (DFAT). The paper will discuss some of the recent techniques and developments that are currently being used and the future publication of a reference standard. Acoustic testing using commercial sound system components is becoming a popular and cost effective way of generating a required acoustic test environment both in and out of a reverberant chamber. This paper will present the DFAT test method, the usual setup and procedure and the development and use of a closed-loop, narrow-band control system. Narrow-band control of the acoustic PSD allows all standard techniques and procedures currently used in random control to be applied to acoustics and some examples are given. The paper will conclude with a summary of the development of a standard practice guideline that is hoped to be available in the first quarter of next year.
The James Webb Space Telescope (JWST) will carry four scientific instruments, one of which is the Tunable Filter Imager (TFI), which is an instrument within the Fine Guidance Sensor. The Dual Wheel (DW) mechanism is being designed, built and tested by COM DEV Ltd. under contract from the Canadian Space Agency. The DW mechanism includes a pupil wheel (PW) holding seven coronagraphic masks and two calibration elements and a filter wheel (FW) holding nine blocking filters. The DW mechanism must operate at both room temperature and at 35K. Successful operation at 35K comprises positioning each optical element with the required repeatability, for several thousand occasions over the five year mission. The paper discusses the results of testing geared motors and bearings at the cryogenic temperature. In particular bearing retainer design and PGM-HT material, the effects of temperature gradients across bearings and the problems associated with cooling mechanisms down to cryogenic temperatures. The results of additional bearing tests are described that were employed to investigate an abnormally high initial torque experienced at cryogenic temperatures. The findings of these tests, was that the bearing retainer and the ball/race system could be adversely affected by the large temperature change from room temperature to cryogenic temperature and also the temperature gradient across the bearing. The DW mechanism is now performing successfully at both room temperature and at cryogenic temperature. The life testing of the mechanism is expected to be completed in the first quarter of 2010.
Human urine and flush water are eventually converted into drinking water with the Urine Processor Assembly (UPA) aboard the International Space Station (ISS). This conversion is made possible through the Distillation Assembly (DA) of the UPA. One component of the DA is a molded circular piston cup made of virgin polytetrafluoroethylene (PTFE). The piston cup is assembled to a titanium component using eight fasteners and washers. Molded PTFE produced for spare piston cups in the first quarter of 2010 was different in appearance and texture, and softer than material molded for previous cups. For the suspect newer PTFE material, cup fasteners were tightened to only one-half the required torque value, yet the washers embedded almost halfway into the material. The molded PTFE used in the DA piston cup should be Type II, based on AMS 3667D and ASTM D4894 specifications. The properties of molded PTFE are considerably different between Type I and II materials. Engineers working with the DA thought that if Type I PTFE was molded by mistake instead of Type II material, that could have resulted in the anomalous material properties. Typically, the vendor molds flat sheet PTFE from the same material lot used to mold the piston cups, and tensile testing as part of quality control should verify that the PTFE is Type II material. However, for this discrepant lot of material, such tensile data was not available. Differential scanning calorimetry (DSC) and dynamic mechanical analysis (DMA) were two of the testing techniques used at the NASA/Marshall Space Flight Center (MSFC) to investigate the anomaly for the PTFE material. Other techniques used on PTFE specimens were: Shore D hardness testing, tensile testing on dog bone specimens and a qualitative estimation of porosity by optical and scanning electron microscopy.
This report summarizes the Applied Meteorology Unit (AMU) activities for the first quarter of Fiscal Year 2010 (October - December 2009). A detailed project schedule is included in the Appendix. Included tasks are: (1) Peak Wind Tool for User Launch Commit Criteria (LCC), (2) Objective Lightning Probability Tool, Phase III, (3) Peak Wind Tool for General Forecasting, Phase II, (4) Upgrade Summer Severe Weather Tool in Meteorological Interactive Data Display System (MIDDS), (5) Advanced Regional Prediction System (ARPS) Data Analysis System (ADAS) Update and Maintainability, (5) Verify 12-km resolution North American Model (MesoNAM) Performance, and (5) Hybrid Single-Particle Lagrangian Integrated Trajectory (HYSPLIT) Graphical User Interface.
This report summarizes the Applied Meteorology Unit (AMU) activities for the first quarter of Fiscal Year 2008 (October-December 2008).
In the summer of 2017, the third and final spacecraft of the 3rd generation of the Tracking and Data Relay Satellites (TDRS) launched aboard an Atlas V rocket from Complex 41 on the Eastern Test Range. Finishing final testing and integration in the first quarter of 2018, the TDRS-M communication and navigation satellite completes a constellation that began service in the early 1980s. The 3rd generation of spacecraft, TDRS-K, L, and M, not only provided beneficial systems engineering lessons in handling anomalous Radio Frequency and Doppler interference as well as integrating new spacecraft into an aging ground support infrastructure, but also supplies NASA with a valuable test bed for new operational concepts and technologies useful in defining the future architecture of the NASA Space Network. This paper presents an overview of the TDRS-K, L, and M missions, including transfer orbit, Level 5 bus and payload testing, and finally NASA-led Level 6 testing, which includes active TDRS System (TDRSS) users. Highlights include relevant testing results, commissioning challenges, and lessons learned. The final discussion includes a brief overview of future NASA communication and navigation technologies and network architectures.
The DGEN AeroPropulsion Research Turbofan (DART) is a small engine representative of commercial transport propulsors. It is used at NASA to study, among other topics, core and combustor noise production mechanisms and propagation. This includes development/validation of robust and accurate instrumentation/techniques for evaluating noise production in the extreme environment of a turbofan core. This presentation highlights upcoming core-noise research activities contributing to or directly utilizing the DART facility during the remaining CY2018 and First Quarter CY 2019 period. The near-term aim is to further investigate features seen in the baseline DART core/combustor-noise test performed in the NASA GRC Aero-Acoustic Propulsion Laboratory (AAPL) during 2017 as well as to provide an improved documentation of the core noise emanating from the turbofan engine. The research is aligned with the NASA Ultra-Efficient Commercial Transport strategic thrust and is supported by the NASA Advanced Air Vehicle Program, Advanced Air Transport Technology Project, under the Aircraft Noise Reduction Subproject.
The Kilopower Project was initiated by NASA’s Space Technology Mission Directorate/Game Changing Development Program in fiscal year 2015 to demonstrate subsystem-level technology readiness of small space fission power in a relevant environment (Technology Readiness Level 5) for space science and human exploration power needs. The Kilopower Project centerpiece is the Kilowatt Reactor Using Stirling TechnologY (KRUSTY) test, which consists of the development and testing of a ground technology demonstrator of a 1-kW(electric)–class fission power system (FPS). The technologies to be developed and validated by KRUSTY are extensible to space FPSs from 1 to 10 kW(electric), which can enable modular surface FPSs for human exploration as well as higher-power future potential deep space science missions. The KRUSTY demonstration is cofunded by NASA and the U.S. Department of Energy National Nuclear Security Administration. The KRUSTY demonstration in the National Critical Experiment Research Center’s Device Assembly Facility was completed in the first quarter of 2018.
At the request of NASA, Deloitte conducted an independent market study to provide an independent assessment on the economic viability of hypersonic and supersonic air transportation to inform ongoing strategic planning of research areas within the government and industry and to focus on the areas for technology development and vehicle design requirements. The Study was organized into three primary areas of investigation: Defining the Market appetite for high speed air transport, Defining the business cases; and Assessing Barriers in the environment. The market demand was assessed across a range of Mach numbers from Mach 2 to Mach 6 and ticket price elasticity was determined by surveying potential customers, literature reviews and stakeholder and expert interviews for passenger aircraft, private aircraft and cargo markets. The business case analyses assessed potential business cases across a three-dimensional trade space: flight speed (Mach 2-6), passenger capacity (20-200 passengers) and design range (2500-7500 nmi.). By using the SpaceWorks Rosetta model, we were able to assess each combination in the trade space and to determine the steady state Internal Rate of Return (IRR or profit) was our primary figure of merit and allowed us to rank order the business cases to understand the trends and draw conclusions from the complex trade space. Lastly, we assessed other potential barriers to high speed flight. These were determined through literature review and stakeholder/expert interviews. Once these were compiled, we developed an objective scoring system to allow us to determine overall significance and challenge to aspiring market entrants. The majority of the research was conducted between July and December of 2020 and the results compiled and communicated to NASA in the first quarter of calendar year 2021. This report, along with the companion briefing deck, document the summation of our research and serve as a data repository for use by future researchers in government and industry.
Commercial Hypersonic Transportation Market Study. At the request of NASA, Deloitte conducted an independent market study to provide an independent assessment on the economic viability of hypersonic and supersonic air transportation to inform ongoing strategic planning of research areas within the government and industry and to focus on the areas for technology development and vehicle design requirements. The Study was organized into three primary areas of investigation: Defining the Market appetite for high speed air transport, Defining the business cases; and Assessing Barriers in the environment. The market demand was assessed across a range of Mach numbers from Mach 2 to Mach 6 and ticket price elasticity was determined by surveying potential customers, literature reviews and stakeholder and expert interviews for passenger aircraft, private aircraft and cargo markets. The business case analyses assessed potential business cases across a three-dimensional trade space: flight speed (Mach 2-6), passenger capacity (20-200 passengers) and design range (2500-7500 nmi.). By using the SpaceWorks Rosetta model, we were able to assess each combination in the trade space and to determine the steady state Internal Rate of Return (IRR or profit) was our primary figure of merit and allowed us to rank order the business cases to understand the trends and draw conclusions from the complex trade space. Lastly, we assessed other potential barriers to high speed flight. These were determined through literature review and stakeholder/expert interviews. Once these were compiled, we developed an objective scoring system to allow us to determine overall significance and challenge to aspiring market entrants. The majority of the research was conducted between July and December of 2020 and the results compiled and communicated to NASA in the first quarter of calendar year 2021. This report, along with the companion briefing deck, document the summation of our research and serve as a data repository for use by future researchers in government and industry.
International Observe the Moon Night is a worldwide public engagement program that has been held annually since 2010. Every autumn, we ask people to observe the Moon in whatever way makes sense to them (via binoculars, telescopes, unaided eye, images, artwork, songs, stories, etc.). The event occurs when the Moon is in or near a first-quarter phase, which provides excellent viewing opportunities along the terminator (the line between night and day), as long shadows place lunar features into great relief. Hundreds of thousands of individuals all around the globe participate in the event as a collective whole, learning about lunar science and exploration, taking part in celestial observations, and honoring cultural and personal connections to the Moon. People participate in a variety of ways, including hosting or attending virtual or in-person events and observing the Moon from home. Participants also have the opportunity to connect with other lunar observers around the world through our Facebook page (facebook.com/observethemoon/), our Flickr group for images (flickr.com/groups/observethemoon2021/), and through the hashtag #ObserveTheMoon across social media platforms.
During its departure from Pluto, New Horizons used its LORRI camera to image a portion of Pluto's southern hemisphere that was in a decades-long seasonal winter darkness, but still very faintly illuminated by sunlight reflected by Charon. Recovery of this faint signal was technically challenging. The bright ring of sunlight forward-scattered by haze in the Plutonian atmosphere encircling the nightside hemisphere was severely overexposed, defeating the standard smeared-charge removal required for LORRI images. Reconstruction of the overexposed portions of the raw images, however, allowed adequate corrections to be accomplished. The small solar elongation of Pluto during the departure phase also generated a complex scattered-sunlight background in the images that was three orders of magnitude stronger than the estimated Charon-light flux (the Charon-light flux is similar to the flux of moonlight on Earth a few days before first quarter). A model background image was constructed for each Pluto image based on principal component analysis applied to an ensemble of scattered-sunlight images taken at identical Sun−spacecraft geometry to the Pluto images. The recovered Charon-light image revealed a high-albedo region in the southern hemisphere. We argue that this may be a regional deposit of N2 or CH4 ice. The Charon-light image also shows that the south polar region currently has markedly lower albedo than the north polar region of Pluto, which may reflect the sublimation of N2 ice or the deposition of haze particulates during the recent southern summer.