The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations

Takeuchi, Hiroshi; Yoshikawa, Kunihiko; Takei, Yuto; Oki, Yusuke; Kikuchi, Shota; Ikeda, Hitoshi; Soldini, Stefania; Ogawa, Naoko; Mimasu, Yuya; Ono, Go; Terui, Fuyuto; Sakatani, Naoya; Kouyama, T.; Kameda, Shingo; Saiki, Takanao; Tsuda, Yuichi

doi:10.1007/s42064-020-0084-7

Cited by 20 publications

(2 citation statements)

References 14 publications

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“…This study then approximately estimated the rover's release condition using these observation results. As a result of the orbit determination of Hayabusa2, when it descended we obtained the position of the rover's release as r HP = [11.56, −22.07, 1503.78] m at 15:57:20 on 2 October 2019 [12]. The rover's release velocity was estimated using least-squares estimation to minimize the objective function, as expressed below.…”

Section: Flight Resultsmentioning

confidence: 99%

Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu

et al. 2020

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This paper describes the orbit design of the deployable payload Rover 2 of MINERVA-II, installed on the Hayabusa2 spacecraft. Because Rover 2 did not have surface exploration capabilities, the operation team decided to experiment with a new strategy for its deployment to the surface. The rover was ejected at a high altitude and made a semi-hard landing on the surface of the asteroid Ryugu after several orbits. Based on the orbital analysis around Ryugu, the expected collision speed was tolerable for the rover to function post-impact. Because the rover could not control its position, its motion was entirely governed by the initial conditions. Thus, the largest challenge was to insert the rover into a stable orbit (despite its large release uncertainty), and avoid its escape from Ryugu due to an environment strongly perturbed by solar radiation pressure and gravitational irregularities. This study investigates the solution space of the orbit around Ryugu and evaluates the orbit’s robustness by utilizing Monte Carlo simulations to determine the orbit insertion policy. Upon analyzing the flight data of the rover operation, we verified that the rover orbited Ryugu for more than one period and established the possibility of a novel method for estimating the gravity of an asteroid.

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Section: Flight Resultsmentioning

confidence: 99%

Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu

et al. 2020

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“…Cappuccio et al [3] used Ganymede's gravity field and tide response, determined by Doppler and range data from a 500 km circular orbit in the 3GM experiment simulation, to provide critical information for accurately modeling Ganymede's internal structure. However, the size of most asteroids is smaller than these moons, and we have less prior knowledge of the internal structure, although many asteroid exploration missions have measured their gravity fields [4][5][6]. Additionally, many asteroids are considered to be rubble pile asteroids, and their internal composition and structure may be unconstrained [7].…”

Section: Introductionmentioning

confidence: 99%

Free-Vertex Tetrahedral Finite-Element Representation and Its Use for Estimating Density Distribution of Irregularly-Shaped Asteroids

Yin

Shu

et al. 2021

Aerospace

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In this article, we present a free-vertex tetrahedral finite-element representation of irregularly shaped small bodies, which provides an alternative solution for estimating asteroid density distribution. We derived the transformations between gravitational potentials expressed by the free-vertex tetrahedral finite elements and the spherical harmonic functions. Inversely, the density of each free-vertex tetrahedral finite element can be estimated via the least-squares method, assuming a spherical harmonic gravitational function is present. The proposed solution is illustrated by modeling gravitational potential and estimating the density distribution of the simulated asteroid 216 Kleopatra.

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2022

Radio Science Techniques for Deep Space Exploration

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The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations

Cited by 20 publications

References 14 publications

Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu

Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu

Free-Vertex Tetrahedral Finite-Element Representation and Its Use for Estimating Density Distribution of Irregularly-Shaped Asteroids

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