Nano semihard moon lander: OMOTENASHI

T Hashimoto, T Yamada, M Otsuki… - IEEE Aerospace and …, 2019 - ieeexplore.ieee.org
The 6U CubeSat “OMOTENASHI,” which is due to be launched in 2020 by NASA's Space
Launch System, will be the world's smallest moon lander. Its main mission is to present the …

OMOTENASHI trajectory analysis and design: Landing phase

J Hernando-Ayuso, S Campagnola, T Yamaguchi… - Acta Astronautica, 2019 - Elsevier
Abstract OMOTENASHI is a JAXA 6U cubesat that aims to perform a semi-hard landing on
the Moon's surface after being deployed into a lunar fly-by orbit by the American Space …

[PDF][PDF] EQUULEUS mission analysis: design of the transfer phase

K Oshima, S Campagnola, CH Yam, Y Kayama… - … Symposium on Space …, 2017 - issfd.org
This paper highlights the design of the transfer phase of EQUULEUS (EQUilibriUm Lunar-
Earth point 6U Spacecraft), which aims to reach and stay at the Earth-Moon L2 libration point …

OMOTENASHI trajectory analysis and design: Earth-Moon transfer phase

Y Ozawa, S Takahashi, J Hernando-Ayuso… - Transactions of the …, 2019 - jstage.jst.go.jp
Outstanding MOon exploration Technologies demonstrated by Nano Semi-Hard Impactor
(OMOTENASHI) is a 6U Cube-Sat that will be launched in 2019 as a secondary payload of …

Thermal System Design of Nano Moon Lander OMOTENASHI with Passive Control

J Kikuchi, T Hashimoto, T Osada - 2021 - ttu-ir.tdl.org
OMOTENASHI is a CubeSat that will be launched by a NASA SLS rocket. Its mission is to
demonstrate that a CubeSat can make a semi-hard landing on the Moon. The 6U-size …

Trajectory design for the JAXA moon nano-lander OMOTENASHI

J Hernando-Ayuso, Y Ozawa, S Takahashi… - 2017 - digitalcommons.usu.edu
Abstract OMOTENASHI (Outstanding MOon exploration TEchnologies demonstrated by
Nano Semi-Hard Impactor) is a JAXA 6U cubesat that aims to perform a semi-hard landing …

Families of unstable quasi-satellite orbits in the spatial circular restricted three-body problem

K Oshima, T Yanao - 2018 Space Flight Mechanics Meeting, 2018 - arc.aiaa.org
This paper explores the rich dynamics of quasi-satellite orbits with out-of-plane motions
(spatial QSOs) in the Earth-Moon and Mars-Phobos circular restricted three-body problems …

[PDF][PDF] A Doctor Thesis

航法誘導制御方策の統合的最適化 - repository.dl.itc.u-tokyo.ac.jp
In deep space exploration with micro/nano-spacecraft, the relatively high cost of trajectory
correction and orbit determination is an important issue. In this study, a method is proposed …

[PDF][PDF] OMOTENASHI Trajectory Analysis and Design: Landing Phase

J HERNANDO, S CAMPAGNOLA, T IKENAGA… - issfd.org
OMOTENASHI Trajectory Analysis and Design: Landing Phase Page 1 OMOTENASHI
Trajectory Analysis and Design: Landing Phase By Javier HERNANDO-AYUSO,1) Stefano …

[PDF][PDF] Analysis and Design of Chaotic Transfer Trajectories in the Restricted Three-and Four-Body Problems

大島健太 - 2017 - waseda.repo.nii.ac.jp
Trojan asteroids have been discovered around the stable Lagrange points L4 and L5 in
several planetary systems, such as Sun-Jupiter [46], Sun-Mars [47], Sun-Neptune [48], Sun …