TY - GEN
T1 - Systems Engineering of Using Sandbags for Site Preparation and Shelter Design for a Modular Lunar Base
AU - Raj, Athip Thirupathi
AU - Qiu, Jiawei
AU - Vilvanathan, Virupakshan
AU - Xu, Yinan
AU - Asphaug, Erik
AU - Thangavelautham, Jekan
N1 - Funding Information:
The work has been funded by the NASA BAA Next Space Technologies for Exploration Partnerships -2 (NextSTEP-2), In-Situ Resource Utilization (ISRU) Technology. The authors would like to thank the following individuals for their input and help: Hari Nayar, Julie Kleinhenz, Diane Linne, Jerry Sanders, and Brian Wilcox.
Funding Information:
The study on which this paper is based was supported by NASA MUREP Institutional Research Opportunity Grant under Cooperative Agreement #80NSSC19M0196. The results and opinions expressed in this paper do not necessarily reflect the views and policies of the National Aeronautics and Space Administration.
Funding Information:
A Lunar Space Technology Research (LuSTR) grant awarded to Michigan Technological University (MTU) has prompted the development of a Percussive Heated Cone Penetrometer (PHCP). This technology will allow for the active sampling of geotechnical data and thermal calorimetric measurements of lunar regolith in PSRs. This paper will focus on the sig nificance of the thermal measurements collected by the PHCP. Through the addition of heat and the active sampling of the temperatures surrounding the heated probe, temperature profiles will indicate phase changes for many volatiles present. This data will then be used in a predictive mathematical model to derive the volatile contents surrounding the PHCP.
Funding Information:
This project was undertaken with the financial support of the Canadian Space Agency, the Natural Sciences and Engineering Research Council of Canada (NSERC), and the Fonds de Recherche du Québec - Nature et Technologies (FRQNT). The authors would also like to thank Dominique Tremblay and Pierre-Lucas Aubin-Fournier for assistance with designing and building the experimental apparatus, and George Butt for assistance with performing the experiments.
Funding Information:
The author would like to thank the Norwich University Faculty Development Funding for the Charles A. Dana Research Fellowship AY19 -20 and the resourceful contribution of the Kreitzberg Library.
Funding Information:
This work is supported by NASA Small Business Technology Transfer (STTR) program 2021 (award number T7.04-2630 (STTR 2021-1)). We would like to thank our technical omtor Benveirly Kemmerer for her smooth management of this waard.
Funding Information:
The authors would like to express our gratitude to Dr. Mike Pereira, Mr. Duane Revilock, and Mr. Charles Ruggeri, Aerospace Engineers at NASA Glenn Research Center, for sharing their insight and expertise along with the test data, photos and videos generated during the tests. Their support greatly assisted with this research. The authors are also grateful to Mr. William Emmerling (retired) at FAA William J. Hughes Technical Center for his constant support and advice on this research, and Dr. Gilbert Queitzsch (retired) at FAA for his helpful discussion and feedback for this research. This research was conducted under FAA cooperative agreement 692M151840003 and sponsored by the Aircraft Catastrophic Failure Prevention Program (ACFPP).
Funding Information:
This work is funded by NASA SSERVI under the RESOURCE (Resource Exploration and Science of OUR Cosmic Environment) contract.
Funding Information:
This work was funded by the Laboratory Directed Research & Development (LDRD) program at Sandia National Laboratories, and the U.S. Department of Energy, Office of Science, Office of Advanced Scientific Computing Research under Award Number DE-SC-0000230927 and under the Collaboratory on Mathematics and Physics-Informed Learning Machines for Multiscale and Multiphysics Problems (PhILMs) project. The development of the ideas presented herein was funded in part by the third author’s Presidential Early Career Award for Scientists and Engineers (PECASE). Sandia National Laboratories is a multi-mission laboratory managed and operated by National Technology and Engineering Solutions of Sandia, LLC., a wholly owned subsidiary of Honeywell International, Inc., for the U.S. Department of Energy’s National Nuclear Security Administration under contract DE-NA0003525. This paper describes objective technical results and analysis. Any subjective views or opinions that might be expressed in the paper do not
Funding Information:
This work was partially funded by National Key R&D Program of China with grant No. 2017YFC1503106 and Science & Tec hnology Project of China Energy Engineering Group Planning and Engineering Co., Ltd with grant No. GSKJ2-T02-2020.
Funding Information:
The authors would like to thank the Korean Technology for financial support of this research.
Funding Information:
This work is supported by Louisiana Space Grant Consortium (LaSPACE), and Bert S. Turner Department of Construction Management at LSU. The authors would like to also thank Dr. Jennifer Edmunson (NASA Marshall Space Flight Center) for her valuable support.
Funding Information:
This work was supported by the Sandia National Laboratories (SNL) Laboratory-directed Research and Development (LDRD) program, and the U.S. Department of Energy, Office of Science, Office of Advanced Scientific Computing Research under Award Number DE-SC-0000230927 and under the Col-laboratory on Mathematics and Physics-Informed Learning Machines for Multiscale and Multiphysics Problems (PhILMs) project. This paper describes objective technical results and analysis. Any subjective views or opinions that might be expressed in the paper do not necessarily represent the views of the U.S. Department of Energy or the United States Government.
Funding Information:
This work is funded by the Technology Mission Directorate.
Funding Information:
The authors acknowledge the financial support received from the Quake Core, NZ, and University of Canterbury Doctoral Scholarship along with the technical support during the planning and testing phase of the research provided by Prof. Timothy Sullivan, Mr. Tim Perigo, Mr. Mosese Fifita, Mr. Alan Thirlwell, and the Structural Engineering Laboratory team.
Funding Information:
This work is supported by a Lunar Surface Technology Research (LuSTR) grant from 1$6$¶V 6SDFH 7HFKQRORJ\ 5HVHDUFK *UDQWV 3URJUDP 166& .
Funding Information:
We wish to express our sincere appreciation to Mr. Matt Duggan and Dr. Valery Aksamentov, project leads for Boeing for their effective central roles in initiating and supporting these efforts, and The Boeing Company for financial support of the study. We also owe a debt of gratitude to our own SICSA graduates who contributed to this project: Osaid Sasi and Albert Rajkumar.
Funding Information:
*Sandia National Laboratories is a multimission laboratory managed and operated by National Technology and Engineering Solutions of Sandia, LLC., a wholly owned subsidiary of Honeywell International, Inc., for the U.S. Department of Energy’s National Nuclear Security Administration under contract DE-NA-0003525.
Publisher Copyright:
© ASCE.
PY - 2023
Y1 - 2023
N2 - The next major milestone in space development will be to establish a semi-permanent or permanent human presence on the Moon. The Moon will become a springboard for future efforts to advance a Cislunar space economy and advance the colonization of Mars. We expect a lunar base camp rated for humans that is capable of in situ resource utilization (ISRU) will contain several facilities, such as stations for power, mining, robot operations, asset tracking, communications, material processing, geological survey lab, service, and repair station and launch/landing pads. Various parameters will be involved in the design of each facility. With so many parameters present, arriving at an optimal solution for the design of the lunar base requires the following: (1) Identifying the critical parameters involved; (2) Formulating the empirical relationships between the identified parameters; (3) Performing optimization utilizing the empirical relationships found. An early lunar base is expected to be modular, with lessons learned from the construction of the International Space Station (ISS). Site preparation tasks had initially been envisioned to be done using astronauts. However, the lunar surface is harsh, and performing dull, dirty, and dangerous tasks such as site preparation puts astronauts at risk. A compelling alternative is using robots to perform site preparation and base construction ready for human astronauts to live. In this paper, we identify the different parameters involved in constructing a modular lunar base with a focus on ISRU and aim to arrive at the empirical relationships between them. We perform a case study on a modular base with each module constructed with sandbags. Sandbags offer the lowest cost of entry towards surface construction. Sandbags are relatively easy to assemble into shelters and support structures and can be adapted to various lunar surface conditions. Sandbags structures do not require water or heat for construction. Obtaining enough water to produce the paste needed for additive building structures on the Moon is a significant challenge. In contrast, solar sintering requires high energy and relatively complex facilities to generate significant amounts of solar energy to be used in sintering and additive manufacturing. We perform a detailed analysis of sandbag structures for constructing a lunar base and critically analyze the shortcomings and what needs to be done to overcome them. First, we list out the critical parameters for each module (independent variables) and identify the interfacing requirements between modules to arrive at the dependent and derived variables. Then we use these variables to arrive at the relations to the size of the different modules and, consequently, the entire base itself. These relations may be used as a tool to arrive at configurations for lunar bases based on different objectives and requirements.
AB - The next major milestone in space development will be to establish a semi-permanent or permanent human presence on the Moon. The Moon will become a springboard for future efforts to advance a Cislunar space economy and advance the colonization of Mars. We expect a lunar base camp rated for humans that is capable of in situ resource utilization (ISRU) will contain several facilities, such as stations for power, mining, robot operations, asset tracking, communications, material processing, geological survey lab, service, and repair station and launch/landing pads. Various parameters will be involved in the design of each facility. With so many parameters present, arriving at an optimal solution for the design of the lunar base requires the following: (1) Identifying the critical parameters involved; (2) Formulating the empirical relationships between the identified parameters; (3) Performing optimization utilizing the empirical relationships found. An early lunar base is expected to be modular, with lessons learned from the construction of the International Space Station (ISS). Site preparation tasks had initially been envisioned to be done using astronauts. However, the lunar surface is harsh, and performing dull, dirty, and dangerous tasks such as site preparation puts astronauts at risk. A compelling alternative is using robots to perform site preparation and base construction ready for human astronauts to live. In this paper, we identify the different parameters involved in constructing a modular lunar base with a focus on ISRU and aim to arrive at the empirical relationships between them. We perform a case study on a modular base with each module constructed with sandbags. Sandbags offer the lowest cost of entry towards surface construction. Sandbags are relatively easy to assemble into shelters and support structures and can be adapted to various lunar surface conditions. Sandbags structures do not require water or heat for construction. Obtaining enough water to produce the paste needed for additive building structures on the Moon is a significant challenge. In contrast, solar sintering requires high energy and relatively complex facilities to generate significant amounts of solar energy to be used in sintering and additive manufacturing. We perform a detailed analysis of sandbag structures for constructing a lunar base and critically analyze the shortcomings and what needs to be done to overcome them. First, we list out the critical parameters for each module (independent variables) and identify the interfacing requirements between modules to arrive at the dependent and derived variables. Then we use these variables to arrive at the relations to the size of the different modules and, consequently, the entire base itself. These relations may be used as a tool to arrive at configurations for lunar bases based on different objectives and requirements.
UR - http://www.scopus.com/inward/record.url?scp=85146586520&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85146586520&partnerID=8YFLogxK
U2 - 10.1061/9780784484470.076
DO - 10.1061/9780784484470.076
M3 - Conference contribution
AN - SCOPUS:85146586520
T3 - Earth and Space 2022: Space Exploration, Utilization, Engineering, and Construction in Extreme Environments - Selected Papers from the 18th Biennial International Conference on Engineering, Science, Construction, and Operations in Challenging Environments
SP - 904
EP - 919
BT - Earth and Space 2022
A2 - Dreyer, Christopher B.
A2 - Littell, Justin
PB - American Society of Civil Engineers (ASCE)
T2 - 18th Biennial International Conference on Engineering, Science, Construction, and Operations in Challenging Environments: Space Exploration, Utilization, Engineering, and Construction in Extreme Environments, Earth and Space 2022
Y2 - 25 April 2022 through 28 April 2022
ER -