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  • 1
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    Optimization of the Lucy Interplanetary Trajectory via Two-Point Direct Shooting (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-24
    Description: Lucy is NASAs next Discovery-class mission and will explore the Trojan asteroids in the Sun-Jupiter L4 and L5 regions. This paper details the design of Lucys interplanetary trajectory using a two-point direct shooting transcription, nonlinear programming, and monotonic basin hopping. These techniques are implemented in the Evolutionary Mission Trajectory Generator (EMTG), a trajectory optimization tool developed at NASA Goddard Space Flight Center. We present applications to the baseline trajectory design, Monte Carlo analysis, and operations.
    Keywords: Astrodynamics
    Type: AAS 19-663 , GSFC-E-DAA-TN71085 , AAS/AIAA Astrodynamics Specialist Conference; Aug 11, 2019 - Aug 15, 2019; Portland, ME; United States
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  • 2
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    Multi-Objective Hybrid Optimal Control for Multiple-Flyby Low-Thrust Mission Design (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Preliminary design of low-thrust interplanetary missions is a highly complex process. The mission designer must choose discrete parameters such as the number of flybys, the bodies at which those flybys are performed, and in some cases the final destination. In addition, a time-history of control variables must be chosen that defines the trajectory. There are often many thousands, if not millions, of possible trajectories to be evaluated. The customer who commissions a trajectory design is not usually interested in a point solution, but rather the exploration of the trade space of trajectories between several different objective functions. This can be a very expensive process in terms of the number of human analyst hours required. An automated approach is therefore very desirable. This work presents such an approach by posing the mission design problem as a multi-objective hybrid optimal control problem. The method is demonstrated on a hypothetical mission to the main asteroid belt.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN19664 , AAS/AIAA Space Flight Mechanics Meeting; Jan 11, 2015 - Jan 15, 2015; Williamsburg, VA; United States
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  • 3
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    Mars, Phobos, and Deimos Sample Return Enabled by ARRM Alternative Trade Study Spacecraft (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Asteroid Robotic Redirect Mission (ARRM) has been the topic of many mission design studies since 2011. The reference ARRM spacecraft uses a powerful solar electric propulsion (SEP) system and a bag device to capture a small asteroid from an Earth-like orbit and redirect it to a distant retrograde orbit (DRO) around the moon. The ARRM Option B spacecraft uses the same propulsion system and multi-Degree of Freedom (DoF) manipulators device to retrieve a very large sample (thousands of kilograms) from a 100+ meter diameter farther-away Near Earth Asteroid (NEA). This study will demonstrate that the ARRM Option B spacecraft design can also be used to return samples from Mars and its moons - either by acquiring a large rock from the surface of Phobos or Deimos, and/or by rendezvousing with a sample-return spacecraft launched from the surface of Mars.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN15840 , AIAA/AAS Astrodynamics Specialist Conference; Aug 04, 2014 - Aug 07, 2014; San Diego, CA; United States
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  • 4
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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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  • 5
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    Refining Lucy Mission Delta-V During Spacecraft Design Using Trajectory Optimization Within High-Fidelity Monte Carlo Maneuver Analysis (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-23
    Description: Recent advances linking medium-fidelity trajectory optimization and high-fidelity trajectory propagation/maneuver design software with Monte Carlo maneuver analysis and parallel processing enabled realistic statistical delta-V estimation well before launch. Completing this high-confidence, refined statistical maneuver analysis early enabled release of excess delta-V margin for increased dry mass margin for the Lucy Jupiter Trojan flyby mission. By 3.3 years before launch, 16 of 34 TCMs had 1000 re-optimized trajectory design samples, yielding tens of m/s lower 99%-probability delta-V versus targeting maneuvers to one optimal trajectory. One year later, 1000 re-optimized samples of all deterministic maneuvers and subsequent flybys further lowered estimated delta-V.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN71229 , 2019 AAS/AIAA Astrodynamics Specialist Conference; Aug 11, 2019 - Aug 15, 2019; Portland, ME; United States
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  • 6
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    Trajectory Design of the Lucy Mission to Explore the Diversity of the Jupiter Trojans (2019)
    In:  CASI
    Details
    Publication Date: 2019-11-01
    Description: Lucy, NASAs next Discovery-class mission, will explore the diversity of the Jupiter Trojan asteroids. The Jupiter Trojans are thought to be remnants of the early solar system that were scattered inward when the gas giants migrated to their current positions as described in the Nice model. There are two stable subpopulations, or swarms, captured at the Sun-Jupiter L4 and L5 regions. These objects are the most accessible samples of what the outer solar system may have originally looked like. Lucy will launch in 2021 and will visit five Trojans, including one binary system. This paper discusses the target selection process, including a description of alternate Lucys that were ultimately passed over in favor of the final design. The mathematics of the trajectory optimization are also discussed.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN74075 , International Astronautical Congress; Oct 21, 2019 - Oct 25, 2019; Washington, D. C. ; United States
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  • 7
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    An Automated Solution of the Low-Thrust Interplanetary Trajectory Problem (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Preliminary design of low-thrust interplanetary missions is a highly complex process. The mission designer must choose discrete parameters such as the number of flybys, the bodies at which those flybys are performed, and in some cases the final destination. In addition, a time-history of control variables must be chosen that defines the trajectory. There are often many thousands, if not millions, of possible trajectories to be evaluated, which can be a very expensive process in terms of the number of human analyst hours required. An automated approach is therefore very desirable. This work presents such an approach by posing the mission design problem as a hybrid optimal control problem. The method is demonstrated on hypothetical missions to Mercury, the main asteroid belt, and Pluto.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN34196 , Journal of Guidance, Control, and Dynamics (ISSN 0731-5090) (e-ISSN 1533-3884); 40; 1; 15-27
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  • 8
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    Global Optimization of Low-Thrust Interplanetary Trajectories Subject to Operational Constraints (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Low-thrust interplanetary space missions are highly complex and there can be many locally optimal solutions. While several techniques exist to search for globally optimal solutions to low-thrust trajectory design problems, they are typically limited to unconstrained trajectories. The operational design community in turn has largely avoided using such techniques and has primarily focused on accurate constrained local optimization combined with grid searches and intuitive design processes at the expense of efficient exploration of the global design space. This work is an attempt to bridge the gap between the global optimization and operational design communities by presenting a mathematical framework for global optimization of low-thrust trajectories subject to complex constraints including the targeting of planetary landing sites, a solar range constraint to simplify the thermal design of the spacecraft, and a real-world multi-thruster electric propulsion system that must switch thrusters on and off as available power changes over the course of a mission.
    Keywords: Astrodynamics
    Type: AAS 16-239 , GSFC-E-DAA-TN29037 , AAS&AIAA Space Flight Mechanics Meeting; Feb 14, 2016 - Feb 18, 2016; Napa Valley, CA; United States
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  • 9
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    Walking the Filament of Feasibility: Global Optimization of Highly-Constrained, Multi-Modal Interplanetary Trajectories Using a Novel Stochastic Search Technique (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Interplanetary trajectory optimization problems are highly complex and are characterized by a large number of decision variables and equality and inequality constraints as well as many locally optimal solutions. Stochastic global search techniques, coupled with a large-scale NLP solver, have been shown to solve such problems but are inadequately robust when the problem constraints become very complex. In this work, we present a novel search algorithm that takes advantage of the fact that equality constraints effectively collapse the solution space to lower dimensionality. This new approach walks the filament'' of feasibility to efficiently find the global optimal solution.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN45144-2 , 2017 AIAA/AAS Astrodynamics Specialist Meeting; Aug 20, 2017 - Aug 24, 2017; Stevenson, WA; United States
    Format: application/pdf
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  • 10
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    Walking the Filament of Feasibility: Global Optimization of Highly-Constrained, Multi-Modal Interplanetary Trajectories Using a Novel Stochastic Search Technique (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Interplanetary trajectory optimization problems are highly complex and are characterized by a large number of decision variables and equality and inequality constraints as well as many locally optimal solutions. Stochastic global search techniques, coupled with a large-scale NLP solver, have been shown to solve such problems but are inadequately robust when the problem constraints become very complex. In this work, we present a novel search algorithm that takes advantage of the fact that equality constraints effectively collapse the solution space to lower dimensionality. This new approach walks the filament'' of feasibility to efficiently find the global optimal solution.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN45144-1 , 2017 AIAA/AAS Astrodynamics Specialist Meeting; Aug 20, 2017 - Aug 24, 2017; Stevenson, WA; United States
    Format: application/pdf
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