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  • 1
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    Near-Earth Asteroids: Destinations for Human Exploration (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Near-Earth Object Human Space Flight Accessible Targets Study (NHATS) is a system that monitors the near-Earth asteroid (NEA) population to identify NEAs whose orbital characteristics may make them potential destinations for future round-trip human space flight missions. To accomplish this monitoring, Brent Barbee (GSFC) developed and automated a system that applies specialized trajectory processing to the orbits of newly discovered NEAs, and those for which we have updated orbit knowledge, obtained from the JPL Small Bodies Database (SBDB). This automated process executes daily and the results are distributed to the general public and the astronomy community. This aids in prioritizing telescope radar time allocations for obtaining crucial follow-up observations of highly accessible NEAs during the critical, because it is often fleeting, time period surrounding the time at which the NEAs are initially discovered.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN15527 , AIAA Mid-Atlantic Section Awards Dinner; Jun 10, 2014; Baltimore, MD; United States
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  • 2
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    A Class of Selenocentric Retrograde Orbits With Innovative Applications to Human Lunar Operations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Selenocentric distant retrograde orbits with radii from approx. 12,500 km to approx. 25,000 km are assessed for stability and for suitability as crewed command and control infrastructure locations in support of telerobotic lunar surface operations and interplanetary human transport. Such orbits enable consistent transits to and from Earth at virtually any time if they are coplanar with the Moon's geocentric orbit. They possess multiple attributes and applications distinct from NASA's proposed destination orbit for a redirected asteroid about 70,000 km from the Moon.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN15844 , AIAA/AAS Astrodynamics Specialist Conference; Aug 04, 2014 - Aug 07, 2014; San Diego, CA; United States
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  • 3
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    Near-Earth Asteroids 2006 RH120 AND 2009 BD: Proxies for Maximally Accessible Objects? (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA's Near-Earth Object Human Space Flight Accessible Targets Study (NHATS) has identified over 1,400 of the approximately 12,800 currently known near-Earth asteroids (NEAs) as more astrodynamically accessible, round-trip, than Mars. Hundreds of those approximately 1,400 NEAs can be visited round-trip for less change-in-velocity than the lunar surface, and dozens can be visited round-trip for less change-in-velocity than low lunar orbit. How accessible might the millions of undiscovered NEAs be? We probe that question by investigating the hypothesis that NEAs 2006 RH120 and 2009 BD are proxies for the most accessible NEAs we would expect to find, and describing possible future NEA population model studies.
    Keywords: Astrodynamics
    Type: AAS 15-526 , GSFC-E-DAA-TN25192 , 2015 AAS/AIAA Astrodynamics Specialist Conference; Aug 09, 2015 - Aug 13, 2015; Vail, CO; United States
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  • 4
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    Fast, Safe, Propellant-Efficient Spacecraft Motion Planning Under Clohessy-Wiltshire-Hill Dynamics (2016)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a sampling-based motion planning algorithm for real-time and propellant-optimized autonomous spacecraft trajectory generation in near-circular orbits. Specifically, this paper leverages recent algorithmic advances in the field of robot motion planning to the problem of impulsively actuated, propellant- optimized rendezvous and proximity operations under the Clohessy-Wiltshire-Hill dynamics model. The approach calls upon a modified version of the FMT* algorithm to grow a set of feasible trajectories over a deterministic, low-dispersion set of sample points covering the free state space. To enforce safety, the tree is only grown over the subset of actively safe samples, from which there exists a feasible one-burn collision-avoidance maneuver that can safely circularize the spacecraft orbit along its coasting arc under a given set of potential thruster failures. Key features of the proposed algorithm include 1) theoretical guarantees in terms of trajectory safety and performance, 2) amenability to real-time implementation, and 3) generality, in the sense that a large class of constraints can be handled directly. As a result, the proposed algorithm offers the potential for widespread application, ranging from on-orbit satellite servicing to orbital debris removal and autonomous inspection missions.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN46943 , Journal of Guidance, Control, and Dynamics (ISSN 0731-5090) (e-ISSN 1533-3884); 40; 2; 418-438
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  • 5
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    Mission Design and Optimal Asteroid Deflection for Planetary Defense (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Planetary defense is a topic of increasing interest for many reasons, which has been mentioned in "Vision and Voyages for Planetary Science in the Decade 2013-2022''. However, perhaps one of the most significant rationales for asteroid studies is the number of close approaches that have been documented recently. A space mission with a planetary defense objective aims to deflect the threatening body as far as possible from Earth. The design of a mission that optimally deflects an asteroid has different challenges: speed, precision, and system trade-off. This work addresses such issues and develops a fast transcription of the problem that can be implemented into an optimization tool, which allows for a broader trade study of different mission concepts with a medium fidelity. Such work is suitable for a mission?s preliminary study. It is shown, using the fictitious asteroid impact scenario 2017 PDC, that the complete tool is able to account for the orbit sensitivity to small perturbations and quickly optimize a deflection trajectory. The speed in which the tool operates allows for a trade study between the available hardware. As a result, key deflection dates and mission strategies are identified for the 2017 PDC.
    Keywords: Astrodynamics
    Type: IAC-2017-C1.7.11 , GSFC-E-DAA-TN45284 , International Astronautical Congress 2017; Sep 25, 2017 - Sep 29, 2017; Adelaide; Australia
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  • 6
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    NEA Mitigation Studies for Short Warning Time Scenarios (2016)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This talk describes current collaborative research efforts between NASA GSFC and the Department of Energy's National Nuclear Security Administration (NNSA) national labs (Lawrence Livermore, Los Alamos, and Sandia) to design systems and frameworks for robust responses to short warning time near-Earth asteroid (NEA) scenarios, in which we would have less than 10 years to respond to an NEA on its way to impact the Earth.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN33007 , NASA Small Bodies Assessment Group (SBAG) Meeting; Jun 28, 2016 - Jun 30, 2016; Laurel, MD; United States
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  • 7
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    Near-Earth Asteroids 2006 RH120 And 2009 BD: Proxies For Maximally Accessible Objects? (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Near-Earth Object Human Space Flight Accessible Targets Study(NHATS): http://neo.jpl.nasa.govnhats/. As of mid-July 2015: 1,434 of the 12,778 currently known NEAs are more astrodynamically accessible than is Mars (requiring less Delta v and or less flight time for round-trip missions). Within those 1,434 NEAs: 605 NEAs can be visited round-trip for less Delta v (9 km/s) than the lunar surface. 51 NEAs can be visited round-trip for less v (5 km/s) than low circular lunar orbit. NEO population statistical models:Tens of thousands of NEAs greater than 100 m yet to be discovered. At least several million NEAs less than or equal to100 m in size (down to approximately 3 m in size) yet to be discovered. How accessible are the NEAs that haven't yet been discovered?
    Keywords: Astrodynamics
    Type: AAS 15-526 , GSFC-E-DAA-TN25333 , 2015 AAS/AIAA Astrodynamics Specialist Conference; Aug 09, 2015 - Aug 13, 2015; Vail, CO; United States
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  • 8
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    An Innovative Solution to NASA's NEO Impact Threat Mitigation Grand Challenge and Flight Validation Mission Architecture Development (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: To develop an innovative yet practically implementable mitigation technique for the most probable impact threat of an asteroid or comet with short warning time(i.e., when we don't have sufficient warning times for a deflection mission)
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN22340 , IAA Planetary Defense Conference; Apr 13, 2015 - Apr 17, 2015; Frascati; Italy
    Format: application/pdf
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