A mission to Uranus facilitates a thorough examination of Uranus, its rings, satellites, and other planetary objects. To travel from Earth to any other planet, a variety of approaches can be used. Despite the standard gravity assist methods to reach the ice-giant Uranus, a direct transfer mission is also feasible. This work provides an overview of the preliminary estimation of the launch mass for a direct transfer mission. The departure year 2022-2030 is considered for this study. The payload and spacecraft subsystems for the proposed mission were selected based on past interplanetary missions. The estimated mass of the scientific instrument of this work was found to be 147.5 Kg. The mass of the payload is 11% of the spacecraft's dry mass. The delta-V for the various departure years is obtained using Lambert’s problem for the different time frames. Delta-V and the launch mass are calculated for a range of 15.5-8.5 years of time-of-flight. The upper limit of the time-of-flight is selected based on a Hohmann transfer. Launch mass decreases from 15.5-13.5 years of time-of-flight and then increases to a maximum value at 8.5 years. For time-of-flight of 13.5 and 12.5 years, the delta-V and the launch mass obtained are optimum, 6.7 km/s and 1700 kg, respectively. In the period selected, these minimum values are observed for the departure year 2022. The data obtained reveal the feasibility of such a mission in the near future.
| Published in | Science Research (Volume 10, Issue 4) |
| DOI | 10.11648/j.sr.20221004.11 |
| Page(s) | 89-98 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2024. Published by Science Publishing Group |
Uranus, Ice-Giants, Preliminary Mission Design, Launch Mass, Spacecraft Subsystems, Delta-V
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APA Style
Gisa Geoson Suseela, Yadu Krishnan Sukumarapillai, Hariprasad Thimmegowda, Manjunath Nagendra, Tamore Silviya Dhiraja, et al. (2022). Preliminary Estimation of Launch Mass for a Direct Transfer Earth-Uranus Mission. Science Research, 10(4), 89-98. https://doi.org/10.11648/j.sr.20221004.11
ACS Style
Gisa Geoson Suseela; Yadu Krishnan Sukumarapillai; Hariprasad Thimmegowda; Manjunath Nagendra; Tamore Silviya Dhiraja, et al. Preliminary Estimation of Launch Mass for a Direct Transfer Earth-Uranus Mission. Sci. Res. 2022, 10(4), 89-98. doi: 10.11648/j.sr.20221004.11
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Download@article{10.11648/j.sr.20221004.11,
author = {Gisa Geoson Suseela and Yadu Krishnan Sukumarapillai and Hariprasad Thimmegowda and Manjunath Nagendra and Tamore Silviya Dhiraja and Pavan Kalyan Devaiah},
title = {Preliminary Estimation of Launch Mass for a Direct Transfer Earth-Uranus Mission},
journal = {Science Research},
volume = {10},
number = {4},
pages = {89-98},
doi = {10.11648/j.sr.20221004.11},
url = {https://doi.org/10.11648/j.sr.20221004.11},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.sr.20221004.11},
abstract = {A mission to Uranus facilitates a thorough examination of Uranus, its rings, satellites, and other planetary objects. To travel from Earth to any other planet, a variety of approaches can be used. Despite the standard gravity assist methods to reach the ice-giant Uranus, a direct transfer mission is also feasible. This work provides an overview of the preliminary estimation of the launch mass for a direct transfer mission. The departure year 2022-2030 is considered for this study. The payload and spacecraft subsystems for the proposed mission were selected based on past interplanetary missions. The estimated mass of the scientific instrument of this work was found to be 147.5 Kg. The mass of the payload is 11% of the spacecraft's dry mass. The delta-V for the various departure years is obtained using Lambert’s problem for the different time frames. Delta-V and the launch mass are calculated for a range of 15.5-8.5 years of time-of-flight. The upper limit of the time-of-flight is selected based on a Hohmann transfer. Launch mass decreases from 15.5-13.5 years of time-of-flight and then increases to a maximum value at 8.5 years. For time-of-flight of 13.5 and 12.5 years, the delta-V and the launch mass obtained are optimum, 6.7 km/s and 1700 kg, respectively. In the period selected, these minimum values are observed for the departure year 2022. The data obtained reveal the feasibility of such a mission in the near future.},
year = {2022}
}
TY - JOUR T1 - Preliminary Estimation of Launch Mass for a Direct Transfer Earth-Uranus Mission AU - Gisa Geoson Suseela AU - Yadu Krishnan Sukumarapillai AU - Hariprasad Thimmegowda AU - Manjunath Nagendra AU - Tamore Silviya Dhiraja AU - Pavan Kalyan Devaiah Y1 - 2022/08/24 PY - 2022 N1 - https://doi.org/10.11648/j.sr.20221004.11 DO - 10.11648/j.sr.20221004.11 T2 - Science Research JF - Science Research JO - Science Research SP - 89 EP - 98 PB - Science Publishing Group SN - 2329-0927 UR - https://doi.org/10.11648/j.sr.20221004.11 AB - A mission to Uranus facilitates a thorough examination of Uranus, its rings, satellites, and other planetary objects. To travel from Earth to any other planet, a variety of approaches can be used. Despite the standard gravity assist methods to reach the ice-giant Uranus, a direct transfer mission is also feasible. This work provides an overview of the preliminary estimation of the launch mass for a direct transfer mission. The departure year 2022-2030 is considered for this study. The payload and spacecraft subsystems for the proposed mission were selected based on past interplanetary missions. The estimated mass of the scientific instrument of this work was found to be 147.5 Kg. The mass of the payload is 11% of the spacecraft's dry mass. The delta-V for the various departure years is obtained using Lambert’s problem for the different time frames. Delta-V and the launch mass are calculated for a range of 15.5-8.5 years of time-of-flight. The upper limit of the time-of-flight is selected based on a Hohmann transfer. Launch mass decreases from 15.5-13.5 years of time-of-flight and then increases to a maximum value at 8.5 years. For time-of-flight of 13.5 and 12.5 years, the delta-V and the launch mass obtained are optimum, 6.7 km/s and 1700 kg, respectively. In the period selected, these minimum values are observed for the departure year 2022. The data obtained reveal the feasibility of such a mission in the near future. VL - 10 IS - 4 ER -
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