Hayabusa2's Superior Solar Conjunction Phase Trajectory Design, Guidance and Navigation



Soldini, Stefania ORCID: 0000-0003-3121-3845, Yamaguchi, Tomohiro, Tsuda, Yuichi, Takanao, Saiki and Nakazawa, Satoru
(2020) Hayabusa2's Superior Solar Conjunction Phase Trajectory Design, Guidance and Navigation. Space Science Reviews, 216 (6).

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Abstract

Hayabusa2 is the ongoing JAXA’s sample and return mission to the asteroid Ryugu. In late 2018, Ryugu was in superior solar conjunction with the Earth. It is the first time that a spacecraft experiences the blackouts in the communication link with the Earth while hovering around a small celestial body. In this article, the design of the nominal conjunction trajectory flown by the Hayabusa2’s spacecraft is presented. The requirements for the conjunction trajectory were (1) to guarantee a low fuel consumption, (2) to ensure the visibility of the asteroid by the spacecraft’s wide angle camera (60∘ FoV), and (3) to increase the spacecraft altitude to a safety location (∼109 km) from the nominal BOX-A operation of 20 km (Home Position - HP). Finally, (4) to return at BOX-A after the conjunction phase. Given the mission constraints, the designed conjunction trajectory appears to have a fish-shape in the Hill coordinates therefore we renamed it as “ayu” (sweetfish in Japanese) trajectory. The optNEAR tool was developed for the guidance (ΔVs planning) and navigation design of the Hayabusa2’s conjunction mission phase. A preliminary sensitivity analysis in the Hill reference frame proved that the ayu trajectory is a good candidate for the conjunction operation of hovering satellite. The solution in the Hill coordinates is refined in the full-body planetary dynamics (optNEAR Tool) before flight. The ayu conjunction trajectory requires (a) two deterministic ΔVs at the Conjunction Orbit Insertion (COI) point and at the Home-position Recovery Maneuver (HRM) point respectively. (b) Two stochastic ΔVs, known as Trajectory Correction Manoeuvres (TCMs), before and after the deep conjunction phase are also required. The constraint linear covariance analysis in the full-body dynamics is here derived and used for the preliminary guidance and navigation planning. The results of the covariance analysis were validated in a nonlinear sense with a Monte Carlo approach which proved the validity of the semi-analytic method for the stochastic ΔVs planning derived in this paper.

Item Type: Article
Uncontrolled Keywords: Superior solar conjunction, Hayabusa2, Ryugu, Hovering satellite, optNEAR tool
Depositing User: Symplectic Admin
Date Deposited: 24 Sep 2020 09:48
Last Modified: 20 Sep 2021 18:10
DOI: 10.1007/s11214-020-00731-5
Open Access URL: https://doi.org/10.1007/s11214-020-00731-5
Related URLs:
URI: https://livrepository.liverpool.ac.uk/id/eprint/3102391