TY - JOUR
T1 - An alternative opportunity of future Psyche mission using differential evolution and gravity assists
AU - Kumar, Vijil
AU - Kushvah, Badam Singh
AU - Bando, Mai
N1 - Publisher Copyright:
© 2022 the Author(s), licensee AIMS Press.
PY - 2022
Y1 - 2022
N2 - NASA’s Psyche mission will launch in August 2022 and begin a journey of 3.6 years to the metallic asteroid: Psyche, where it will orbits and examine this unique body. This paper presents an alternative opportunity of the Psyche mission as well as the return opportunity to the Earth. It uses Mars’s gravity assists to rendezvous with and orbits to the largest metal asteroid in the solar system. The spacecraft orbits around Psyche for approximately 1710 solar days, then starts its return journey. In the outer layer of the proposed methodology, the differential evolution algorithm is used to find the optimal launch, flyby and arrival date. In the inner layer, Lambert’s algorithm is used for finding the feasible and optimal space trajectories solution. Considering gravity assists, before the gravity assists impulse, an optimal thrust impulse has been calculated at periapsis of the fly-by planet that gives the maximum ∆ν2 to the spacecraft.
AB - NASA’s Psyche mission will launch in August 2022 and begin a journey of 3.6 years to the metallic asteroid: Psyche, where it will orbits and examine this unique body. This paper presents an alternative opportunity of the Psyche mission as well as the return opportunity to the Earth. It uses Mars’s gravity assists to rendezvous with and orbits to the largest metal asteroid in the solar system. The spacecraft orbits around Psyche for approximately 1710 solar days, then starts its return journey. In the outer layer of the proposed methodology, the differential evolution algorithm is used to find the optimal launch, flyby and arrival date. In the inner layer, Lambert’s algorithm is used for finding the feasible and optimal space trajectories solution. Considering gravity assists, before the gravity assists impulse, an optimal thrust impulse has been calculated at periapsis of the fly-by planet that gives the maximum ∆ν2 to the spacecraft.
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U2 - 10.3934/math.2022390
DO - 10.3934/math.2022390
M3 - Article
AN - SCOPUS:85124331871
VL - 7
SP - 7012
EP - 7025
JO - AIMS Mathematics
JF - AIMS Mathematics
SN - 2473-6988
IS - 4
ER -