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  • 1
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    ARTEMIS Mission Design (2011)
    Springer
    Details
    Publication Date: 2011-12-01
    Print ISSN: 0038-6308
    Electronic ISSN: 1572-9672
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 2
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    1st ACT global trajectory optimisation competition: Results found at the Jet Propulsion Laboratory (2007)
    Elsevier
    Details
    Publication Date: 2007-11-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Thrust Direction Optimization: Satisfying Dawn's Attitude Agility Constraints (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The science objective of NASA's Dawn Discovery mission is to explore the two largest members of the main asteroid belt, the giant asteroid Vesta and the dwarf planet Ceres. Dawn successfully completed its orbital mission at Vesta. The Dawn spacecraft has complex, difficult to quantify, and in some cases severe limitations on its attitude agility. The low-thrust transfers between science orbits at Vesta required very complex time varying thrust directions due to the strong and complex gravity and various science objectives. Traditional thrust design objectives (like minimum (Delta)V or minimum transfer time) often result in thrust direction time evolutions that can not be accommodated with the attitude control system available on Dawn. This paper presents several new optimal control objectives, collectively called thrust direction optimization that were developed and necessary to successfully navigate Dawn through all orbital transfers at Vesta.
    Keywords: Spacecraft Propulsion and Power; Spacecraft Design, Testing and Performance
    Type: AAS/AIAA Spaceflight Mechanics Meeting; Feb 10, 2013 - Feb 14, 2013; Kauai, HI; United States
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    NASA TECHNICAL REPORTS
  • 4
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    Low Altitude Mapping Orbit Design and Maintenance for the Dawn Discovery Mission at Vesta (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA's Dawn discovery mission will orbit the giant asteroid Vesta beginning in the summer of 2011. Four different near polar science orbits are planned. The lowest planned orbit at Vesta is called the Low Altitude Mapping Orbit or LAMO and is by far the most challenging to design and maintain due to the strong, nonspherical gravity expected there. This paper describes the orbit selection process. The true gravity field of Vesta remains highly uncertain. The proposed orbit selection process will be applied once sufficient gravity knowledge is obtained at higher orbits. The orbit selection process is applied here to a fictitious gravity field based on a Hubble space telescope shape model for Vesta assuming uniform density. The outcome of the process described here is a variety of stable orbits. However, Initially stable orbits at the LAMO altitude are not expected to remain stable operationally due to the unpredictable impulses resulting from the Dawn spacecraft thruster firings to de-saturate its momentum wheels. As a result, orbital maintenance maneuvers will be probably be necessary. This paper also briefly describes the statistical maneuver design process that resulted in the orbit maintenance plan.
    Keywords: Astrodynamics
    Type: AAS 11-182 , AAS/AIAA Space Flight Mechanics Meeting; Feb 10, 2011 - Feb 16, 2011; New Orleans, LA; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Dawn Statistical Maneuver Design for Vesta Operations (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In July of 2011 the Dawn spacecraft is scheduled to begin orbital operations at Vesta, a large main-belt asteroid. Dawn is a NASA Discovery mission that uses solar-electric low-thrust ion propulsion for both interplanetary cruise and orbital operations. Navigating between the Dawn project's four targeted science orbits at Vesta requires a plan that accounts for uncertainties not only in thrust execution, orbit determination, and other spacecraft forces, but also large uncertainties in characteristics of Vesta - such as the asteroid's gravity field and pole orientation. Accommodating these uncertainties requires strategic use of low-thrust maneuvers reserved for statistical trajectory corrections. This paper describes the placement and evaluation of low-thrust statistical maneuvers during two key phases of the Vesta mission along with a discussion of the tools, constraints, and methods used to plan those maneuvers.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: AAS 11-180 , 21st AAS/AIAA Space Flight Mechanics Meeting; Feb 13, 2011; New Orlean, LA; United States
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    NASA TECHNICAL REPORTS
  • 6
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    Earth Orbit Raise Design for the ARTEMIS Mission (2012)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: ARTEMIS is a mission to send two spacecraft from Earth orbit to libration orbits around the Moon Lagrange points and then into lunar orbit. Lunar flybys were used early in the mission to send the spacecraft into low-energy lunar transfers which were designed libration orbits for minimal deltaV. ARTEMIS began by raising the Earth orbits of each spacecraft to achieve the planned lunar flybys. Spacecraft conguration and operation constraints made the Earth orbit raise phase of the mission a signicant mission design challenge by itself. This paper describes the process used to and trajectories that achieved mission goals and the resulting series of Earth orbits that culminated in successful lunar flybys.
    Keywords: Lunar and Planetary Science and Exploration
    Type: AIAA/AAS Astrodynamics Specialist Conference; Aug 13, 2012 - Aug 16, 2012; Minneapolis, MN; United States
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    NASA TECHNICAL REPORTS
  • 7
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    The Stability of Powered Flight around Asteroids with Application to Vesta (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The reliability of low-thrust trajectories between science orbits around large asteroids must be evaluated subject to the unavoidable uncertainties of orbit determination, asteroid physical parameters, momentum de-saturation maneuvers, and transfer maneuver execution error. This paper presents a computationally inexpensive way to extend the concept or orbital stability to trajectories undergoing continuously powered low-thrust flight. Trajectories that are stable using this measure are shown to be stable under the combined uncertainties expected during operations. The measure is general and relatively simple to implement. The method was applied to maneuvers planed around the asteroid Vesta in support of NASA's Dawn Discovery mission.
    Keywords: Astrodynamics
    Type: AAS 11-186 , 21st AAS/AIAA Space Flight Mechanics Meeting; Feb 13, 2011 - Feb 17, 2011; New Orleans, LA; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Orbit Transfers for Dawn's Ceres Operations: Navigation and Mission Design Experience at a Dwarf Planet (2016)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Dawn, a mission belonging to NASAs Discovery Program, was launched on September 27, 2007 to explore two objects in the main asteroid belt in order to yield insights into important questions about the formation and evolution of the solar system. Successfully completing all mission objectives at Vesta, Dawn arrived at dwarf planet Ceres in March 2015 and continued its journey to a series of four near circular polar science orbits. Dawn became the first mission to orbit around two extraterrestrial targets; such a mission would have been impossible without the low thrust ion propulsion system (IPS). Maneuvering a spacecraft using only the IPS for the transfers between the mapping orbits posed many technical challenges to Dawns flight team at NASAs Jet Propulsion Laboratory. Failure of the second reaction wheel assembly, shortly before leaving Vesta, added another challenge for Dawns flight team. This paper discusses the mission design and navigational experience and challenges during Dawns Ceres operations.
    Keywords: Astrodynamics; Astronomy
    Type: JPL-CL-16-1423 , SpaceOps 2016 Conference; May 16, 2016 - May 20, 2016; Daejeon; Korea, Republic of
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    NASA TECHNICAL REPORTS
  • 9
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    Dawn's Mission at Ceres (2016)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Dawn is NASA's ninth Discovery class mission. The Dawn spacecraft was designed to orbit both the giant asteroid Vesta and the dwarf planet Ceres in succession, a mission only made possible by the high efficiency of ion propulsion. While the same spacecraft visited both bodies, the mission planning and maneuver execution at the two bodies were necessarily very different. The mission at Vesta benefited from at least three functioningreaction control wheels. At Ceres, all maneuvering and coasting during transfers was done without reaction wheel control due to the loss of the second of four wheels while departing Vesta. Loss of the second wheel made conserving attitude control propellant (hydrazine) critical to achieving mission success at Ceres. To save hydrazine, avoiding unnecessary coasting and attitude turns became essential during the interplanetary cruise to Ceres and for all transfers once at Ceres. In contrast, operations at Vesta did not need to avoid coasting. Operating at Ceres requires being farther from the Sun. Greaterheliocentric distances (approaching 3 AU (Astronomical Units) make Dawn's attitude control constraints while maneuvering more restrictive as a result of reduced control authority.
    Keywords: Lunar and Planetary Science and Exploration
    Type: JPL-CL-16-3736 , AIAA/AAS Astrodynamics Specialist Conference; Sep 12, 2016 - Sep 15, 2016; Long Beach, CA; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Dawn Safing Approach to Ceres Re-Design (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-13
    Description: In mid-2014 the Dawn team finalized preparations for the spacecrafts approach to Ceres. The design was the product of careful planning that began several years in advance, when the spacecraft left Vesta in September 2012. However, a few months prior to the anticipated start of approach, the spacecraft entered a safe mode. While temporary loss of thrust for ion propulsion missions is usually not mission-critical, it still presents many challenges. The safing event occurred at a time when thrusting to match Ceres orbital velocity was most effective, which meant the spacecraft must fly past Ceres before capturing into orbit. The new approach geometry changed the teams strategy for navigating the spacecraft safely into orbit around Ceres with optical data. In this paper we describe the challenges of navigating the Dawn spacecraft into orbit around Ceres, including the safing event and re-design of the approach architecture.
    Keywords: Astrodynamics
    Type: AIAA 2016-5426 , JPL-CL-16-3759 , AIAA/AAS Astrodynamics Specialist Conference; Sep 13, 2016 - Sep 16, 2016; Long Beach, CA; United States
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