Dawn Maneuver Design Performance at Vesta

Parcher, D. W.; Abrahamson, M.; Ardito, A.; Han, D.; Haw, R. J.; Kennedy, B. M.; Mastrodemos, N.; Nandi, S.; Park, R. S.; Rush, B. P.; Smith, B. A.; Smith, J. C.; Vaughan, A. T.; Whiffen, G. J.

NASA NTRS · 20150008673

Dawn Maneuver Design Performance at Vesta

Parcher, D. W.·Abrahamson, M.·Ardito, A.·Han, D.·Haw, R. J.·Kennedy, B. M.·Mastrodemos, N.·Nandi, S.·Park, R. S.·Rush, B. P.·Smith, B. A.·Smith, J. C.·Vaughan, A. T.·Whiffen, G. J.

View original source ↗Export metadata ↓

Abstract

The Dawn spacecraft orbited the asteroid Vesta from July 16, 2011 to September 5, 2012, successfully accomplishing the four planned science orbits and two planned rotational characterization orbits. The lowest-altitude science orbit lasted four months, with 20 planned orbit maintenance maneuvers. Navigation results from Vesta demonstrate that the navigation plan was sufficient to achieve orbit delivery accuracy requirements. This paper compares the flown Dawn trajectory against the planned trajectory and expected maneuver dispersions. Understanding the effectiveness of the Vesta maneuver design plan is a key component of planning for operations at Ceres, the next destination for the Dawn mission.

Explore related subjects

Ion Propulsion Asteroid Navigation Low Thrust

Keep this discovery

Explore connections, maps & timelines

BibTeX RIS

Parcher, D. W., Abrahamson, M., Ardito, A., Han, D., Haw, R. J., Kennedy, B. M., Mastrodemos, N., Nandi, S., Park, R. S., Rush, B. P., Smith, B. A., Smith, J. C., Vaughan, A. T., Whiffen, G. J.. 2013-02-10. Dawn Maneuver Design Performance at Vesta. https://ntrs.nasa.gov/citations/20150008673

Cite the original work for its findings. Save a collection to share your selection of sources.

KEEP EXPLORING

Related reports

NASA NTRS2015

The Ion Propulsion System for the Solar Electric Propulsion Technology Demonstration Mission

The Asteroid Redirect Robotic Mission is a candidate Solar Electric Propulsion Technology Demonstration Mission whose main objectives are to develop and demonstrate a high-power solar electric propulsion capability for the Agency and return an asteroidal mass for rendezvous and characterization in a subsequent human-crewed mission. The ion propulsion subsystem must be capable of operating over an 8-year time period and processing up to 10,000 kg of xenon propellant. This high-power solar electric propulsion capability, or an extensible derivative of it, has been identified as an enabling element of an affordable beyond low-earth orbit human-crewed exploration architecture. Under the NASA Space Technology Mission Directorate the critical electric propulsion and solar array technologies are being developed. The ion propulsion system for the Asteroid Redirect Vehicle is based on the NASA-developed 12.5 kW Hall Effect Rocket with Magnetic Shielding thruster and power processing technologies. This paper presents the conceptual design for the ion propulsion system, a status on the NASA in-house thruster and power processing is provided, and an update on acquisition for flight provided.

Ion Propulsion↗

NASA NTRS2015

Xenon Acquisition Strategies for High-Power Electric Propulsion NASA Missions

Solar electric propulsion (SEP) has been used for station-keeping of geostationary communications satellites since the 1980s. Solar electric propulsion has also benefitted from success on NASA Science Missions such as Deep Space One and Dawn. The xenon propellant loads for these applications have been in the 100s of kilograms range. Recent studies performed for NASA's Human Exploration and Operations Mission Directorate (HEOMD) have demonstrated that SEP is critically enabling for both near-term and future exploration architectures. The high payoff for both human and science exploration missions and technology investment from NASA's Space Technology Mission Directorate (STMD) are providing the necessary convergence and impetus for a 30-kilowatt-class SEP mission. Multiple 30-50- kilowatt Solar Electric Propulsion Technology Demonstration Mission (SEP TDM) concepts have been developed based on the maturing electric propulsion and solar array technologies by STMD with recent efforts focusing on an Asteroid Redirect Robotic Mission (ARRM). Xenon is the optimal propellant for the existing state-of-the-art electric propulsion systems considering efficiency, storability, and contamination potential. NASA mission concepts developed and those proposed by contracted efforts for the 30-kilowatt-class demonstration have a range of xenon propellant loads from 100s of kilograms up to 10,000 kilograms. This paper examines the status of the xenon industry worldwide, including historical xenon supply and pricing. The paper will provide updated information on the xenon market relative to previous papers that discussed xenon production relative to NASA mission needs. The paper will discuss the various approaches for acquiring on the order of 10 metric tons of xenon propellant to support potential near-term NASA missions. Finally, the paper will discuss acquisitions strategies for larger NASA missions requiring 100s of metric tons of xenon will be discussed.

Ion Propulsion↗