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  • 1
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    Concurrent Aerocapture with Orbital Plane Change Using Starbody Waveriders (2014)
    Springer
    Details
    Publication Date: 2014-12-01
    Print ISSN: 0021-9142
    Electronic ISSN: 2195-0571
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 2
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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; Statistics and Probability
    Type: GSFC-E-DAA-TN45920 , International Astronautical Congress 2017; Sep 25, 2017 - Sep 29, 2017; Adelaide; Australia
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 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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    NASA TECHNICAL REPORTS
  • 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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    NASA TECHNICAL REPORTS
  • 7
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    Validation of a Low-Thrust Mission Design Tool Using Operational Navigation Software (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Design of flight trajectories for missions employing solar electric propulsion requires a suitably high-fidelity design tool. In this work, the Evolutionary Mission Trajectory Generator (EMTG) is presented as a medium-high fidelity design tool that is suitable for mission proposals. EMTG is validated against the high-heritage deep-space navigation tool MIRAGE, demonstrating both the accuracy of EMTG's model and an operational mission design and navigation procedure using both tools. The validation is performed using a benchmark mission to the Jupiter Trojans.
    Keywords: Astrodynamics
    Type: AAS 17-204 , GSFC-E-DAA-TN38473-1 , AAS/AIAA Space Flight Mechanics Meeting; Feb 05, 2017 - Feb 09, 2017; San Antonio, TX; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Improved Propulsion Modeling for Low-Thrust Trajectory Optimization (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Low-thrust trajectory design is tightly coupled with spacecraft systems design. In particular, the propulsion and power characteristics of a low-thrust spacecraft are major drivers in the design of the optimal trajectory. Accurate modeling of the power and propulsion behavior is essential for meaningful low-thrust trajectory optimization. In this work, we discuss new techniques to improve the accuracy of propulsion modeling in low-thrust trajectory optimization while maintaining the smooth derivatives that are necessary for a gradient-based optimizer. The resulting model is significantly more realistic than the industry standard and performs well inside an optimizer. A variety of deep-space trajectory examples are presented.
    Keywords: Astrodynamics; Spacecraft Propulsion and Power
    Type: GSFC-E-DAA-TN38572 , AAS/AIAA Space Flight Mechanics Meeting; Feb 05, 2017 - Feb 09, 2017; San Antonio, TX; United States
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    NASA TECHNICAL REPORTS
  • 9
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    Automated Sensitivity Analysis of Interplanetary Trajectories for Optimal Mission Design (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This work describes a suite of Python tools known as the Python EMTG Automated Trade Study Application (PEATSA). PEATSA was written to automate the operation of trajectory optimization software, simplify the process of performing sensitivity analysis, and was ultimately found to out-perform a human trajectory designer in unexpected ways. These benefits will be discussed and demonstrated on sample mission designs.
    Keywords: Astrodynamics
    Type: GSFC-E-DAA-TN41242 , International Symposium on Space Flight Dynamics; Jun 03, 2017 - Jun 09, 2017; Matsuyama; Japan
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    NASA TECHNICAL REPORTS
  • 10
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    Benchmarking the Collocation Stand-Alone Library and Toolkit (CSALT) (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the processes and results of Verification and Validation (V&V) efforts for the Collocation Stand Alone Library and Toolkit (CSALT). We describe the test program and environments, the tools used for independent test data, and comparison results. The V&V effort employs classical problems with known analytic solutions, solutions from other available software tools, and comparisons to benchmarking data available in the public literature. Presenting all test results are beyond the scope of a single paper. Here we present high-level test results for a broad range of problems, and detailed comparisons for selected problems.
    Keywords: Computer Programming and Software; Aeronautics (General)
    Type: GSFC-E-DAA-TN40959 , Nano-Satellite Symposium NSAT; Jun 03, 2017 - Jun 09, 2017; Matsuyama; Japan|International Symposium on Space Flight Dynamics ISSFD; Jun 03, 2017 - Jun 09, 2017; Matsuyama; Japan|International Symposium on Space Technology and Science ISTS; Jun 03, 2017 - Jun 09, 2017; Matsuyama; Japan
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