Mission Analysis for the EM-1 CubeSats EQUULEUS and OMOTENASHI

Campagnola, Stefano; Hernando-Ayuso, Javier; Kakihara, Kota; Kawabata, Yusuke; Chikazawa, Takuya; Funase, Ryu; Ozaki, Naoya; Baresi, Nicola; Hashimoto, Tatsuaki; Kawakatsu, Yasuhiro; Ikenaga, Toshinori; Oguri, Kenshiro; Oshima, Koichiro

doi:10.1109/maes.2019.2916291

Cited by 21 publications

(8 citation statements)

References 4 publications

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“…Other several proposed missions have encountered similar eclipse problems, such as JUICE [5], LUMIO [6], and JWST [7]. A similar situation occurred to the authors of this paper while designing science orbits for the CubeSat mission EQUULEUS [8].…”

Section: Introductionsupporting

confidence: 60%

Minimizing eclipses via synodic resonant orbits with applications to EQUULEUS and MMX

et al. 2021

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Section: Introductionsupporting

confidence: 60%

Minimizing eclipses via synodic resonant orbits with applications to EQUULEUS and MMX

et al. 2021

Self Cite

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“…The spacecraft can fly by an asteroid every few years. The total Δ𝑉 of 65 m/s is affordable for micro spacecraft and CubeSats, such as PROCYON [36,37] and EQUULEUS [38].…”

Section: F Representative Solutionsmentioning

confidence: 99%

Asteroid Flyby Cycler Trajectory Design Using Deep Neural Networks

Ozaki,

Yanagida,

Chikazawa

et al. 2021

Preprint

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“…A further example is given by the Space Launch System (SLS) rocket, which plans to carry 13 nano-satellites together with the Artemis I Orion spacecraft to the Moon [4][5][6][7][8][9][10][11]. This mission includes JAXA's Earth-Moon libration point orbiter EQUULEUS and the world's smallest lunar lander OMOTENASHI as piggyback spacecraft [12]. In general, the number of piggyback probes for deep space missions is expected to increase in the future.…”

Section: Introductionmentioning

confidence: 99%

Expanding Interplanetary Transfer Opportunities from Geostationary Transfer Orbits via Earth Synchronous Orbits

Ito

Pushparaj

Kawakatsu

2023

Journal of Spacecraft and Rockets

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GeostationaryTransfer Orbits (GTO) are geocentric orbits widely considered for kick-stage operations of satellites for deep space missions. A piggyback spacecraft departing from GTOs requires a low transfer cost. The type of GTO and launch timings of piggyback missions, on the other hand, are typically determined by the primary mission that carried the piggyback spacecraft. This research introduces a new transfer strategy that coordinates piggyback spacecraft's departure timing from Earth to deep space via an Earth synchronous orbit (ESO) after departure from GTO. It also enables the spacecraft to change its velocity direction by introducing Earth gravity assists. Connecting several GTOs and interplanetary trajectories via ESOs reduces the Δ𝑉 required for the transfers. It leads to utilizing transfer opportunities

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Mission Analysis for the EM-1 CubeSats EQUULEUS and OMOTENASHI

Cited by 21 publications

References 4 publications

Minimizing eclipses via synodic resonant orbits with applications to EQUULEUS and MMX

Minimizing eclipses via synodic resonant orbits with applications to EQUULEUS and MMX

Asteroid Flyby Cycler Trajectory Design Using Deep Neural Networks

Expanding Interplanetary Transfer Opportunities from Geostationary Transfer Orbits via Earth Synchronous Orbits

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