Predicting Crew Time Allocations for Lunar Orbital missions based on Historical ISS Operational Activities

<div class="htmlview paragraph">A National Aeronautics and Space Administration (NASA) program has been completed which outlined an advanced missions Environmental Control/Life Support System (ECLSS) technology research and development (R&D) plan. The study defined the ECLSS requirements and ECLSS-related unique mission drivers (i.e., mission duration, crew size, etc.) of a broad range of advanced missions currently being considered by the NASA and recommended by the National Commission on Space. The existing ECLSS technologies were assessed and an evaluation was made to determine the potential application of the existing ECLSS technology to the requirements of the future missions. Technology needs were identified and an advanced missions ECLSS technology R&D plan was outlined.</div>

The Ulysses mission is a collaborative effort of the European Space Agency (ESA) and the National Aeronautics and Space Administration (NASA) to study the Sun's environment, the heliosphere, especially over its polar regions. Mission operations are carried out by a joint multi-national ESA/NASA team located at NASA's Jet Propulsion Laboratory. At the time of writing, the nominal date for the end of science mission operations is the end of March 2008, a total mission duration of 17½ years from the launch date of 6th October 1990. Supporting such a long duration mission using the original mission control system is clearly undesirable for a number of reasons: hardware failures, hardware and operating system obsolescence and requirements imposed due to reasons external to the mission or user requests. This paper presents the real-life experiences of the Ulysses flight control team in evolving the Ulysses mission control system (UMCS) to support on-going mission operations. The UMCS is into its third generation and the lessons learned in migrating from the first to the second generation and carried over into the recently completed migration will be discussed in this paper. One example of such a lesson is the need to understand fully the requirements driving the migration and assigning priorities to such requirements. Another is the need to identify the migration paths available and trade them off in terms of risks and costs. One of the major contributors to both successful migrations was the decision to stay with the same operating system family, HP OpenVMS, for the UMCS. Another was that the need for minimal changes to the application code base, modify code to support hardware only, was clearly understood by the user community. A crucial element in migration success was the live comparison testing of the new and old UMCS carried out by the UMCS users, which generated an auditable trail for system validation. This exercise also produced strong confidence among all stakeholders that the new UMCS is even better than the old.

Personal computers of the past were limited to running computational fluid dynamics codes in serial mode. With the advent of multicore technology and suitable compilers, personal computers nowadays can execute codes in a parallel fashion similar to that of supercomputers and cluster computer systems. This article investigated what performance can be achieved when executing an aerodynamic code on an Intel quad core based personal computer with an OpenMP compiler in a Windows environment. The code solved the Euler equations to find the flowfield around a NACA0012 aerofoil on an O-type boundary fitted structured grid system. A speedup of up to 350% was obtainable in double precision accuracy. The reduced computation time means that, for small scale problems, more accurate Euler codes can replace commonly used transonic small disturbance codes. For larger problems, this information serves as a reference for developers of hybrid MPI/OpenMP algorithms for cluster computer systems. References Advanced Micro Devices (AMD), AMD FireStream 9170: Industry's First GPU with Double-Precision Floating Point, 2007, http://ati.amd.com/products/streamprocessor/specs.html Allmaras, S. R., Venkatakrishnan, V., and Johnson, F. T., Farfield Boundary Conditions for 2-D Airfoils, AIAA Paper 2005-4711, AIAA, 2005. Bailey, D., Barszcz, E., Barton, J., Browning, D., Carter, R., Dagum, L., Fatoohi, R., Fineberg, S., Frederickson, P., Lasinski, T., Schreiber, R., Simon, H., Venkatakrishnan, V., and Weeratunga, S., The NAS Parallel Benchmarks, National Aeronautics and Space Administration (NASA), Contractor Report 203186, USA, 1994, http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19970014936_1997021577.pdf Dong, S., and Karniadakis, G. E., Dual-Level Parallelism for High-Order CFD Methods, Parallel Computing, 30, Jan. 2004, pp. 1--20. Hirsch, C., Numerical Computation of Internal and External Flows (Volume 2): Computational Methods for Inviscid and Viscous Flows, John Wiley and Sons, Great Britain, 1992. Hoffmann, K. A., Computational Fluid Dynamics for Engineers, Engineering Educational System, Texas, USA, 1989. Intel, Tera-scale Computing Research Program, c.2007, http://www.intel.com/research/platform/terascale/ Jin, H., Frumkin, M., and Yan, J., The OpenMP Implementation of NAS Parallel Benchmarks and its Performance, National Aeronautics and Space Administration (NASA), Technical Report NAS-99-011, Moffett Field, USA, 1999. Liu, Y., and Vinokur, M., Nonequilibrium Flow Computations 1: An Analysis of Numerical Formulations of Conservation Laws, National Aeronautics and Space Administration (NASA), Contractor Report 177489, California, USA, 1988, http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19880021000_1988021000.pdf Lock, R. C., Test Cases for Numerical Methods in Two-Dimensional Transonic Flows, Advisory Group for Aerospace Research and Development (AGARD), Report Number 575, 1970. Ly, E., Improved Approximate Factorisation Algorithm for the Steady Subsonic and Transonic Flow over an Aircraft Wing, Proceedings of the 21st Congress of the International Council of the Aeronautical Sciences (ICAS98), ICAS and AIAA, Melbourne, Australia, 1998, Paper A98-31699. Ly, E., and Gear, J. A., Time-Linearized Transonic Computations Including Shock Wave Motion Effects, Journal of Aircraft, 39, 6, Nov/Dec. 2002, pp. 964--972. Ly, E., and Nakamichi, J., Time-Linearised Transonic Computations Including Entropy, Vorticity and Shock Wave Motion Effects, The Aeronautical Journal, Nov. 2003, pp. 687--695. Ly, E., and Norrison, D., Automatic Elliptic Grid Generation by an Approximate Factorisation Algorithm, ANZIAM Journal, 48 (CTAC2006), pp. C188--C202, July 2007, http://anziamj.austms.org.au/ojs/index.php/ANZIAMJ/article/view/48. Ly, E., and Norrison, D., Generating Elliptic Grids in Three Dimensions by a Method of False Transients, ANZIAM Journal, 49 (EMAC2007), pp. C170--C183, Nov. 2007, http://anziamj.austms.org.au/ojs/index.php/ANZIAMJ/article/view/313. Nvidia, The Era of the Personal Supercomputer, 2007, http://www.nvidia.com/content/events/siggraph_2007/supercomputing.html Pope, S. B., A Perspective on Turbulence Modeling, Modeling Complex Turbulent Flows, Kluwer Academic Publishers, The Netherlands, 1999. Pulliam, T., Kutler, P., and Rossow, V., Harvard Lomax: His Quiet Legacy to Computational Fluid Dynamics, 14th AIAA Computational Fluid Dynamics Conference, Norfolk, VA, 28 June-1 July, 1999, http://people.nas.nasa.gov/ pulliam/mypapers/lomax_la.ps Steger, J. L., and Warming, R. F., Flux Vector Splitting of the Inviscid Gasdynamic Equations with Application to Finite Difference Methods, National Aeronautics and Space Administration (NASA) Technical Memorandum 78605, California, USA, 1979, http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19790020779_1979020779.pdf Thompson, J. R., Warsi, Z. U. A., and Mastin, C. W., Numerical Grid Generation: Foundations and Applications, Elsevier Science Publishing Co. Inc., New York, USA, 1985. Van Leer, B., Flux-Vector Splitting for the Euler Equations, Proceedings of the 8th International Conference on Numerical Methods in Fluid Dynamics, Aachen, West Germany, 1982.

A successful transition to global clean energy hinges on meeting the world’s growing demand for power, while at the same time reducing greenhouse gas emissions. Achieving this will require significant growth in electricity generation from clean and carbon-free energy sources. Several energy providers (Acar and Dincer, 2019, “Review and Evaluation of Hydrogen Production Options for Better Environment,” J. Cleaner Prod., 218, pp. 835–849 and Nagashima, M., 2024, “Japan’s Hydrogen Strategy and Its Economic and Geopolitical Implications,” Afficher la page d’accueil du site) have already begun the transition from traditional carbon-based fuels to cleaner alternatives, such as hydrogen (H2) and hydrogen-enriched natural gas (HENG). However, there are still many technical questions/challenges that must be addressed when applying these fuels in gas turbines. The application of H2 or H2/natural gas (NG) blends to advanced-class gas turbines, which have higher operating pressures and temperatures, has raised concerns about the potential for leakages or fuel sequencing operations where flammable mixtures of fuel and air could auto-ignite. Public information on the auto-ignition of H2 in the air at atmospheric pressure shows an auto-ignition temperature (AIT) between 520 and 585 °C (U.S. Department of Energy, 2024, “U.S. Department of Energy Hydrogen Program Plan,” U.S. Department of Energy, Washington, DC; Georgia Power, 2022, “Georgia Power, Mitsubishi Power, EPRI Complete World’s Largest Hydrogen Fuel Blending at Plant McDonough-Atkinson,” Georgia Power, Atlanta, GA; and gepower-v2, 2024, “New York Power Authority: GE Vernova,” gepower-v2, Cambridge, MA). Such data show AIT of H2 is ∼100 °C lower than that of methane (CH4) which has a minimum AIT of around 600 °C (Huth, M., and Heilos, A., 2013, “Fuel Flexibility in Gas Turbine Systems: Impact on Burner Design and Performance,” Modern Gas Turbine Systems, Sawston, UK, pp. 635–684). Studies also show that as pressure increases, methane’s AIT decreases significantly to around 390 °C (Loving, C., Mastantuono, G., Terracciano, A. C., Vasu, S. S., Pigon, T., Hernandez, A., and Cloyd, S., 2023, “Auto-Ignition Test Results of Hydrogen and Natural Gas Fuels at Atmospheric and Elevated Pressures for Gas Turbine Safety,” ASME Paper No. GT2023-102674). However, there was insufficient information in the published literature to characterize the influence of pressure on the AIT of H2 and HENG fuels. At atmospheric conditions, H2 has a wider flammability range of equivalence ratios that ignition can occur compared to methane. H2’s flammability ranges from 4% to 75% molar (volume) fuel concentration, which is an equivalence ratio range of 0.137–2.57. Methane’s flammability limit ranges from 5% to 15% molar (volume) or an equivalence ratio between 0.53 and 1.58 (National Aeronautics and Space Administration, 1997, Safety Standard for Hydrogen and Hydrogen Systems: Guidelines for Hydrogen System Design, Materials Selection, Operations, Storage, and Transportation, National Aeronautics and Space Administration, Office of Safety and Mission Assurance; National Technical Information Service, Distributor, Washington, DC, Springfield, VA). Previous research has also been done to determine the effect of longer hydrocarbons present in natural gas mixtures. The presence of ethane (C2H6) and propane (C3H8) has been shown to reduce the AIT of natural gas, especially at elevated pressures (The Association, 1994, NFPA 49: Hazardous Chemicals Data, The Association, Quincy, MA). These longer hydrocarbons also tend to promote ignition in richer conditions, whereas methane tends to ignite easier in slightly lean conditions (National Aeronautics and Space Administration, 1997, Safety Standard for Hydrogen and Hydrogen Systems: Guidelines for Hydrogen System Design, Materials Selection, Operations, Storage, and Transportation, National Aeronautics and Space Administration, Office of Safety and Mission Assurance; National Technical Information Service, Distributor, Washington, DC, Springfield, VA). Numerous variables besides the pressure, fuel, and equivalence ratio can affect the AIT including chamber volume size, chamber materials, presence of diluents, and other factors (Standards Australia International, 2000, Electrical Apparatus for Explosive Gas Atmospheres. Part 20, Data for Flammable Gases and Vapours, Relating to the Use of Electrical Apparatus, Standards Australia International; Standards New Zealand, Strathfield, NSW, Wellington, NZ). This study describes the test methodology used to evaluate conditions where auto-ignition occurs for various fuel–air mixtures operating at different pressures (1–30 atm) and temperatures. Testing was completed with 100% H2 and multiple H2/NG blends at various equivalence ratios (ER) between 0.2 and 2.5. Testing was similarly performed for 100% NG to validate the test and data collection methods cited in prior published literature. Results indicate that, at atmospheric pressures, an increase in H2 concentration results in a reduced AIT. However, at 30 atm, the increased presence of H2 increased the AIT. At elevated pressures above 10 atm, increased equivalence ratio resulted in reduced AIT for all mixtures with NG having the greatest sensitivity to equivalence ratio. Variations of auto-ignition delay times (AIDT) were also observed during the testing and are compared to modeling predictions, providing insight into auto-ignition characteristics.

Human health and performance considerations for near earth asteroids (NEA)

Within the US National Aeronautics and Space Administration (NASA), the Earth Science Technology Office (ESTO) is leading the effort in developing new, CubeSat- and SmallSat-class instruments and instrument technologies for Earth observations. ESTO has been on forefront of the CubeSat related activities through In-space Validation of Earth Science Technology program. In 2010 ESTO supported a pilot for early CubeSat developments in 1 U - 3U form factors. With the success of these CubeSats a formal program was launched with a solicitation in 2012 followed by 3 more in 2015, 2017 and 2020. Early on, the program was targeted towards validation of technology in the space environment. Over time demonstrations of emerging technologies have made possible unique science from new mission architectures on smaller satellite platforms at more rapid development and lower cost. Simultaneous multi-point observations, for example, are now possible challenging what can be achieved scientifically through innovative and disruptive approaches alternative to the traditional larger spacecraft missions. However, it has also been shown that measurements from smaller platforms have their own limitations. Experience and knowledge acquired through these efforts is instrumental in the development of future missions. This presentation will summarize CubeSat concepts, the progress to date, the preliminary science results, and their impact on future missions.

Orbit determination and gravity field recovery from Doppler tracking data to the Lunar Reconnaissance Orbiter

Space travel: medicine in extremes

TECHNOLOGY FORECAST AND APPLICATIONS FOR AUTONOMOUS, INTELLIGENT SYSTEMS

Technology forecast and applications for autonomous, intelligent systems

Evaluation of dual multi-mission space exploration vehicle operations during simulated planetary surface exploration

HE ownership of resulting from T government financed research and development constitutes a very controversial problem. The federal government mainly the Department of Defense (DOD) has permitted industrial firms to obtain the patent rights to most of the inventions emerging from its contract research, under the so-called with the government acquiring royaltyfree licenses on the inventions. Our task here is an empirical investigation of one of the issues in the controversy over federal patent policy, namely, the concentration of resulting from the operation of the license policy. One of the strongest objections to the license policy rests on the belief that it causes undue concentration of economic power. The objection has been raised repeatedly by attorneys general, by legislators, and by economists who favor the so-called ' under which the government retains ownership of resulting from its contract research. From records of the United States Patent Office, we have compiled data for the period 1946 to 1962 on the numbers of assigned to business firms that have been the research and development (R and D) for the Atomic Energy Commission (AEC), the Department of Defense, and the National Aeronautics and Space Administration (NASA). The data are neither estimates nor samples; they are complete counts. The three agencies account for nearly all of the issued under the license policy to contractors. Henceforth, we shall refer to these as license-policy patents. We also have data on the private patents resulting from the company financed R and D of the same contractors. The major R and D contractors are 177 business firms that were among the first 100 of DOD in any fiscal year from 1955 to 1962, or who had contract awards of $2 million or more from the AEC or from NASA.2 Of these 177 firms, 40 are among the first 100 in Fortune's list for 1962. Another 49 are among Fortune's 500 companies. A further 36 have been officially stamped as small businesses. With the exception of a few of the bigger chemical and oil companies that have done little or no research for the federal government, the names of nearly all the Schumpeterian giants of American industry are on our list. By treating each firm and its subsidiaries as a unit, we overstate patent concen* The research underlying this article was supported by a grant (NsG 425) from the National Aeronautics and Space Administration to The George Washington University. 1 Department of Justice, Investigations of Government Patent Practices and Policies: Report and Recommendations of the Attorney General to the President 1 (Washington, D.C.: U.S. Government Printing Office, 1947), 37; Report of the Attorney General Pursuant to Section 708 (e) of the Defense Production Act of 1950, as Amended (Nov. 9, 1956, mimeo.); Clair Wilcox, Public Policies Toward Business (Homewood, Ill.: Richard D. Irwin, 1960), 191; Walter Adams and Horace M. Gray, Monopoly in America: The Government as Promotor (New York: Macmillan, 1955), 47, 94, and 148-152. Testimony against the license policy and in favor of the title policy was given to a Senate subcommittee in 1963 by Horace M. Gray, Robert F. Lanzillotti, Wassily W. Leontief, Richard R. Nelson, and Lee E. Preston. See Aspects of Government Patent Policies, Hearings before a Subcommittee of the Select Committee on Small Business, United States Senate, 88th Congress, First Session, Impact of Government Patent Policies on Economic Growth, Scientific and Technological Progress, Competition, and Opportunities for Small Business, March 7, 8, 13, and 14, 1963 (Washington, D.C.: U.S. Government Printing Office, 1963). Only Leontief (p. 236), however, addressed himself specifically to the question of concentration. 2 Department of Defense, 500 Contractors Listed According to Net Value of Military Prime Contract Awards for Experimental, Development Test and Research Work (Fiscal years 1955 through 1962, mimeo.); and Files of the Atomic Energy Commission and published reports of the National Aeronautics and Space Administration. 'Usually, government employees are required to assign title to the government. However, if a government employee, with his own resources, produces an invention that his agency wants, the government frequently files the patent application in exchange for a royalty-free license. Also, if an agency does not want a government financed invention made by an employee, the employee often is permitted to acquire title. Regulations governing employees were tightened in 1950. This fact and the relative growth of contract research are the causes of the decline in the number of licenses from employees after 1950.

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The National Aeronautics and Space Administration (NASA) carries out a variety of cooperative programs with African countries, the most extensive being the Landsat data analysis projects begun in 1972. Other programs include television broadcasts via satellite to Africa and use of meteorological satellites. All of NASA’s cooperative programs in Africa are run on a no-exchange-of-funds basis, with each nation bearing its own costs. Hence, no NASA funds are transferred to Africa in connection with cooperative activities. In NASA’s Office of International Affairs, the staff of twenty-five persons spends somewhat less than ten per cent of their time on African matters.