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  • *Ecosystem  (3)
  • Spacecraft Design, Testing and Performance  (3)
  • Life and Medical Sciences
  • 2020-2024
  • 2005-2009  (6)
  • 1990-1994
  • 1975-1979
  • 1970-1974
  • 1930-1934
  • 2005  (6)
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  • 2020-2024
  • 2005-2009  (6)
  • 1990-1994
  • 1975-1979
  • 1970-1974
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  • 1
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    Ecology. Are U.S. coral reefs on the slippery slope to slime? (2005)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 2005-03-19
    Description: 〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Pandolfi, J M -- Jackson, J B C -- Baron, N -- Bradbury, R H -- Guzman, H M -- Hughes, T P -- Kappel, C V -- Micheli, F -- Ogden, J C -- Possingham, H P -- Sala, E -- New York, N.Y. -- Science. 2005 Mar 18;307(5716):1725-6.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Centre for Marine Studies and Department of Earth Sciences, University of Queensland, St. Lucia, QLD 4072, Australia. j.pandolfi@uq.edu.au〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/15774744" target="_blank"〉PubMed〈/a〉
    Keywords: Animals ; *Anthozoa ; Biodiversity ; Biomass ; Conservation of Natural Resources ; *Ecosystem ; Eutrophication ; Fishes ; Food Chain ; Greenhouse Effect ; International Cooperation ; Public Policy ; United States ; Water Pollution
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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  • 2
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    Community structure of corals and reef fishes at multiple scales (2005)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 2005-08-27
    Description: Distributions of numerical abundance and resource use among species are fundamental aspects of community structure. Here we characterize these patterns for tropical reef fishes and corals across a 10,000-kilometer biodiversity gradient. Numerical abundance and resource-use distributions have similar shapes, but they emerge at markedly different scales. These results are consistent with a controversial null hypothesis regarding community structure, according to which abundance distributions arise from the interplay of multiple stochastic environmental and demographic factors. Our findings underscore the importance of robust conservation strategies that are appropriately scaled to the broad suite of environmental processes that help sustain biodiversity.〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Connolly, Sean R -- Hughes, Terry P -- Bellwood, David R -- Karlson, Ronald H -- New York, N.Y. -- Science. 2005 Aug 26;309(5739):1363-5.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Centre for Coral Reef Biodiversity, Department of Marine Biology, James Cook University, Townsville, QLD 4811, Australia.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/16123298" target="_blank"〉PubMed〈/a〉
    Keywords: Animals ; *Anthozoa ; Biodiversity ; Biomass ; *Ecosystem ; Environment ; Mathematics ; Models, Biological ; Normal Distribution ; Pacific Ocean ; *Perciformes ; Population Density
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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  • 3
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    Social-ecological resilience to coastal disasters (2005)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 2005-08-16
    Description: Social and ecological vulnerability to disasters and outcomes of any particular extreme event are influenced by buildup or erosion of resilience both before and after disasters occur. Resilient social-ecological systems incorporate diverse mechanisms for living with, and learning from, change and unexpected shocks. Disaster management requires multilevel governance systems that can enhance the capacity to cope with uncertainty and surprise by mobilizing diverse sources of resilience.〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Adger, W Neil -- Hughes, Terry P -- Folke, Carl -- Carpenter, Stephen R -- Rockstrom, Johan -- New York, N.Y. -- Science. 2005 Aug 12;309(5737):1036-9.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Tyndall Centre for Climate Change Research, School of Environmental Sciences, University of East Anglia, Norwich, NR4 7TJ, UK. n.adger@uea.ac.uk〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/16099974" target="_blank"〉PubMed〈/a〉
    Keywords: *Adaptation, Psychological ; Animals ; Asia ; Biodiversity ; Communicable Diseases ; Conservation of Natural Resources ; *Disaster Planning ; *Disasters ; *Ecosystem ; Environment ; Geography ; Government ; Humans ; *Social Environment
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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  • 4
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    A Simple, Powerful Method for Optimal Guidance of Spacecraft Formations (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: One of the most interesting and challenging aspects of formation guidance law design is the coupling of the orbit design and the science return. The analyst s role is more complicated than simply to design the formation geometry and evolution. He or she is also involved in designing a significant portion of the science instrument itself. The effectiveness of the formation as a science instrument is intimately coupled with the relative geoniet,ry and evolution of the collection of spacecraft. Therefore, the science return can be maximized by optimizing the orbit design according to a performance metric relevant to the science mission goals. In this work, we present a simple method for optimal formation guidance that is applicable to missions whose performance metric, requirements, and constraints can be cast as functions that are explicitly dependent upon the orbit states and spacecraft relative positions and velocities. We present a general form for the cost and constraint functions, and derive their semi-analytic gradients with respect to the formation initial conditions. The gradients are broken down into two types. The first type are gradients of the mission specific performance metric with respect to formation geometry. The second type are derivatives of the formation geometry with respect to the orbit initial conditions. The fact that these two types of derivatives appear separately allows us to derive and implement a general framework that requires minimal modification to be applied to different missions or mission phases. To illustrate the applicability of the approach, we conclude with applications to twc missims: the Magnetospheric Mu!tiscale mission (MMS), a,nd the TJaser Interferometer Space Antenna (LISA).
    Keywords: Spacecraft Design, Testing and Performance
    Type: 595 Flight Mechanics Symposium; Oct 18, 2005 - Oct 20, 2005; Greenbelt, MD; United States
    Format: application/pdf
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  • 5
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    Inflatable Re-Entry Vehicle Experiment (IRVE) Design Overview (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Inflatable aeroshells offer several advantages over traditional rigid aeroshells for atmospheric entry. Inflatables offer increased payload volume fraction of the launch vehicle shroud and the possibility to deliver more payload mass to the surface for equivalent trajectory constraints. An inflatable s diameter is not constrained by the launch vehicle shroud. The resultant larger drag area can provide deceleration equivalent to a rigid system at higher atmospheric altitudes, thus offering access to higher landing sites. When stowed for launch and cruise, inflatable aeroshells allow access to the payload after the vehicle is integrated for launch and offer direct access to vehicle structure for structural attachment with the launch vehicle. They also offer an opportunity to eliminate system duplication between the cruise stage and entry vehicle. There are however several potential technical challenges for inflatable aeroshells. First and foremost is the fact that they are flexible structures. That flexibility could lead to unpredictable drag performance or an aerostructural dynamic instability. In addition, durability of large inflatable structures may limit their application. They are susceptible to puncture, a potentially catastrophic insult, from many possible sources. Finally, aerothermal heating during planetary entry poses a significant challenge to a thin membrane. NASA Langley Research Center and NASA's Wallops Flight Facility are jointly developing inflatable aeroshell technology for use on future NASA missions. The technology will be demonstrated in the Inflatable Re-entry Vehicle Experiment (IRVE). This paper will detail the development of the initial IRVE inflatable system to be launched on a Terrier/Orion sounding rocket in the fourth quarter of CY2005. The experiment will demonstrate achievable packaging efficiency of the inflatable aeroshell for launch, inflation, leak performance of the inflatable system throughout the flight regime, structural integrity when exposed to a relevant dynamic pressure and aerodynamic stability of the inflatable system. Structural integrity and structural response of the inflatable will be verified with photogrammetric measurements of the back side of the aeroshell in flight. Aerodynamic stability as well as drag performance will be verified with on board inertial measurements and radar tracking from multiple ground radar stations. The experiment will yield valuable information about zero-g vacuum deployment dynamics of the flexible inflatable structure with both inertial and photographic measurements. In addition to demonstrating inflatable technology, IRVE will validate structural, aerothermal, and trajectory modeling techniques for the inflatable. Structural response determined from photogrammetrics will validate structural models, skin temperature measurements and additional in-depth temperature measurements will validate material thermal performance models, and on board inertial measurements along with radar tracking from multiple ground radar stations will validate trajectory simulation models.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2005-1636 , 18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar; May 23, 2005 - May 26, 2005; Munich; Germany
    Format: application/pdf
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  • 6
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    A Direct Method for Fuel Optimal Maneuvers of Distributed Spacecraft in Multiple Flight Regimes (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: We present a method to solve the impulsive minimum fuel maneuver problem for a distributed set of spacecraft. We develop the method assuming a non-linear dynamics model and parameterize the problem to allow the method to be applicable to multiple flight regimes including low-Earth orbits, highly-elliptic orbits (HEO), Lagrange point orbits, and interplanetary trajectories. Furthermore, the approach is not limited by the inter-spacecraft separation distances and is applicable to both small formations as well as large constellations. Semianalytical derivatives are derived for the changes in the total AV with respect to changes in the independent variables. We also apply a set of constraints to ensure that the fuel expenditure is equalized over the spacecraft in formation. We conclude with several examples and present optimal maneuver sequences for both a HE0 and libration point formation.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AAS 05-158 , 15th AAS/AIAA Space Flight Mechanics Meeting; Jan 23, 2005 - Jan 27, 2005; Copper Mountain, CO; United States
    Format: application/pdf
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