A Survey of Mission Opportunities to Trans-Neptunian Objects - Part IV

Baskaran, G. B.; Bonthalapati, Anurag S.; Lewis, Justin D.; Malone, Kyle J.; Ved, Harsh M.; Lyne, James Evans

doi:10.2514/6.2014-4353

Cited by 5 publications

(4 citation statements)

References 2 publications

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“…Our limit is just outside both the orbit of Io (5.91 Jupiter radii) and the peak S+ region of the Io plasma torus (5.71 Jupiter radii) [35]. A more-detailed study that calculates the expected radiation exposure for a particular trajectory, along the lines of Kreitzman et al [25], Baskaran et al [26,27] or Costigan [28] is beyond the scope of this work. We did not have any radiation information or warnings for Saturn, Uranus or Neptune, so we set the closest approach limits at an arbitrary 1.1 radii for each of those planets.…”

Section: B Parameter Selectionmentioning

confidence: 99%

“…Baskaran et al [26,27] or Costigan [28] is beyond the scope of this work. We did not have any radiation information or warnings for Saturn, Uranus or Neptune, so we set the closest approach limits at an arbitrary 1.1 radii for each of those planets.…”

Section: B Parameter Selectionmentioning

confidence: 99%

“…Greaves el al [24] [25] calculate the particular radiation dose received during the path through the Jupiter system, and compare it to a common cut-off limit. Baskaran et al [26,27] compare high (C3 ~100 km 2 / 2 ) and low (C3 ~50 km 2 /s 2 ) thrust Jupiter gravity assist trajectories to Haumea, Huya, Ixion Pluto, Quaoar, and Varuna departing between 2022-2025, and calculate their Jupiter radiation doses. A Jupiter-Saturn gravity assist trajectory to Huya is also considered…”

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confidence: 99%

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Return to the Kuiper Belt: Launch Opportunities from 2025 to 2040

Zangari

Finley

Stern

et al. 2019

Journal of Spacecraft and Rockets

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Nomenclature AU = astronomical unit, average Earth -Sun distance B = impact parameter C3 = excess launch energy ∆V = change in velocity required to alter a spacecraft's trajectory KBO = Kuiper Belt Object PC = plane crossing r p = planet radius r q = distance from a planet at periapse = gravitational constant * planet mass ! = arrival velocity of a spacecraft = angle between incoming and outgoing velocity vectors during a swingby Preliminary spacecraft trajectories for 45 Kuiper Belt Objects (KBOs) and Pluto suitable for launch between 2025 and 2040 are presented. These 46 objects comprise all objects with H magnitude < 4.0 or which have received a name from the International Astronomical Union as of May 2018. Using a custom Lambert solver, trajectories are modeled after the New Horizons mission to Pluto-Charon, which consisted of a fast launch with a Jupiter gravity assist. In addition to searching for Earth-Jupiter-KBO trajectories, Earth-Saturn-KBO trajectories are examined, with the option to add on a flyby to either Uranus or Neptune. With a single Jupiter gravity assist, all 45 KBOs and Pluto can be reached within a 25 year maximum mission duration. A more limited number can be reached when non-Jupiter flybys are added, and the KBOs that can be reached via these alternate routes are listed. In most cases, a single Jupiter flyby is the most efficient way to get to the Kuiper Belt, but the science return from revisiting Saturn, Uranus, or Neptune may add substantial value to a mission, so alternate flybys should be considered.

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Section: B Parameter Selectionmentioning

confidence: 99%

Section: B Parameter Selectionmentioning

confidence: 99%

mentioning

confidence: 99%

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Return to the Kuiper Belt: Launch Opportunities from 2025 to 2040

Zangari

Finley

Stern

et al. 2019

Journal of Spacecraft and Rockets

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“…Furthermore, the possibility to study those dwarf planets for many years by following them during their path around the Sun could reveal important information about the origins of the solar system, its evolution, as well as about the nature of the Kuiper Belt itself. Throughout the years, very few missions have been studied to reach those worlds, mostly with classical propulsion systems [22][23][24][25][26].…”

Section: Trans-neptunian Objectsmentioning

confidence: 99%

Exploration of trans-Neptunian objects using the Direct Fusion Drive

Aime,

Gajeri,

Kezerashvili

2020

Preprint

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The Direct Fusion Drive (DFD) is a nuclear fusion engine that will provide thrust and electrical power for any spacecraft. It is a compact engine, based on the D -3 He aneutronic fusion reaction that uses the Princeton field reversed configuration for the plasma confinement and an odd parity rotating magnetic field as heating method to achieve nuclear fusion (Cohen et al., 2019), which will heat the deuterium, also used as propellant.In this work we present possibilities to explore the solar system outer border using the DFD. The objective is to reach some trans-Neptunian object, such as the dwarf planets Makemake, Eris and Haumea in less than 10 years with a payload mass of at least of 1500 kg, so that it would enable all kind of missions, from scientific observation to in-situ operations. For each mission a thrust-coast-thrust profile is considered. For this reason, each mission is divided into 3 phases: i. the spiral trajectory to escape Earth gravity; ii. the interplanetary travel, from the exit of Earth sphere of influence to the end of the coasting phase; iii. maneuvers to rendezvous with the dwarf planet. Propellant mass consumption, initial and final masses, velocities and ∆V for each maneuver are presented. Calculations to reach a vicinity at 125 AU for the study of Sun magnetosphere as well as Eris via flyby are also presented, with interest on the influence of different acceleration phases.Our calculations show that a spacecraft propelled by DFD will open unprecedented possibilities to explore the border of the solar system, in a limited amount of time and with a very high payload to propellant masses ratio.

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