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  • 1
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    Triggering of destructive earthquakes in El Salvador (2004)
    In:  Geology, Zagreb, 3-4, vol. 32, no. 1, pp. 65-68, pp. B06305, (ISSN: 1340-4202)
    Details
    Publication Date: 2004
    Keywords: Stress ; Seismicity ; Coulomb ; triggering ; Martinez ; Diaz ; Alvarez ; Gomez ; Hernandez ; Earthquake ; Central ; America
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    SeriesBuster: a Matlab program to extract spatio-temporal series from an earthquake database (2005)
    In:  Computers and Geosciences, Hannover, Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 31, no. 4, pp. 521-525, pp. 1281
    Details
    Publication Date: 2005
    Keywords: Seismicity ; Statistical investigations ; software ; spatial ; and ; temporal ; distance ; Gutenberg-Richter magnitude frequency b-value ; Earthquake hazard ; CaG ; Alvarez ; Gomez ; Martinez ; Diaz
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    STEREO Mission Design (2007)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: STEREO (Solar-TErestrial RElations Observatory) is the third mission in the Solar Terrestrial Probes program (STP) of the National Aeronautics and Space Administration (NASA). STEREO is the first mission to utilize phasing loops and multiple lunar flybys to alter the trajectories of more than one satellite. This paper describes the launch computation methodology, the launch constraints, and the resulting nine launch windows that were prepared for STEREO. More details are provided for the window in late October 2006 that was actually used.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Proceedings of the 20th International Symposium on Space Flight Dynamics; NASA/CP-2007-214158
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    NASA TECHNICAL REPORTS
  • 4
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    STEREO Mission Design Implementation (2007)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: STEREO (Solar-TErrestrial RElations Observatory) is the third mission in the Solar Terrestrial Probes program (STP) of the National Aeronautics and Space Administration (NASA) Science Mission Directorate Sun-Earth Connection theme. This paper describes the successful implementation (lunar swingby targeting) of the mission following the first phasing orbit to deployment into the heliocentric mission orbits following the two lunar swingbys. The STEREO Project had to make some interesting trajectory decisions in order to exploit opportunities to image a bright comet and an unusual lunar transit across the Sun.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Proceedings of the 20th International Symposium on Space Flight Dynamics; NASA/CP-2007-214158
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    NASA TECHNICAL REPORTS
  • 5
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    Using Bond Graphs for Articulated, Flexible Multi-bodies, Sensors, Actuators, and Controllers with Application to the International Space Station (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Conceptually, modeling of flexible, multi-body systems involves a formulation as a set of time-dependent partial differential equations. However, for practical, engineering purposes, this modeling is usually done using the method of Finite Elements, which approximates the set of partial differential equations, thus generalizing the approach to all continuous media. This research investigates the links between the Bond Graph method and the classical methods used to develop system models and advocates the Bond Graph Methodology and current bond graph tools as alternate approaches that will lead to a quick and precise understanding of a flexible multi-body system under automatic control. For long endurance, complex spacecraft, because of articulation and mission evolution the model of the physical system may change frequently. So a method of automatic generation and regeneration of system models that does not lead to implicit equations, as does the Lagrange equation approach, is desirable. The bond graph method has been shown to be amenable to automatic generation of equations with appropriate consideration of causality. Indeed human-interactive software now exists that automatically generates both symbolic and numeric system models and evaluates causality as the user develops the model, e.g. the CAMP-G software package. In this paper the CAMP-G package is used to generate a bond graph model of the International Space Station (ISS) at an early stage in its assembly, Zvezda. The ISS is an ideal example because it is a collection of bodies that are articulated, many of which are highly flexible. Also many reaction jets are used to control translation and attitude, and many electric motors are used to articulate appendages, which consist of photovoltaic arrays and composite assemblies. The Zvezda bond graph model is compared to an existing model, which was generated by the NASA Johnson Space Center during the Verification and Analysis Cycle of Zvezda.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 2003 Western NultiConference on Computer Simulation; Jan 19, 2003 - Jan 23, 2003; Orlando, FL; United States
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    NASA TECHNICAL REPORTS
  • 6
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    Tetrahedron Formation Control (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft flying in tetrahedron formations are excellent instrument platforms for electromagnetic and plasma studies. A minimum of four spacecraft - to establish a volume - is required to study some of the key regions of a planetary magnetic field. The usefulness of the measurements recorded is strongly affected by the tetrahedron orbital evolution. This paper considers the preliminary development of a general optimization procedure for tetrahedron formation control. The maneuvers are assumed to be impulsive and a multi-stage optimization method is employed. The stages include targeting to a fixed tetrahedron orientation, rotating and translating the tetrahedron and/or varying the initial and final times. The number of impulsive maneuvers citn also be varied. As the impulse locations and times change, new arcs are computed using a differential corrections scheme that varies the impulse magnitudes and directions. The result is a continuous trajectory with velocity discontinuities. The velocity discontinuities are then used to formulate the cost function. Direct optimization techniques are employed. The procedure is applied to the Magnetospheric Multiscale Mission (MMS) to compute preliminary formation control fuel requirements.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Flight Dynamics Symposium; Oct 28, 2003 - Oct 30, 2003; Greenbelt, MD; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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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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    NASA TECHNICAL REPORTS
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