On-orbit depot architectures using contingency propellant

Ho, Koki; Gerhard, Katherine; Nicholas, Austin; Buck, Alexander; Hoffman, Jeffrey A.

doi:10.1016/j.actaastro.2013.11.023

Cited by 11 publications

(6 citation statements)

References 14 publications

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“…Numerous technologies have been developed to support sustainable space exploration. This includes In-Situ Resource Utilization (ISRU) technologies from the resources on the Moon, Phobos, Contents lists available at ScienceDirect journal homepage: www.elsevier.com/locate/actaastro Deimos, and Mars [2][3][4][5], on-orbit propellant storage depot with its temperature control technologies [6][7][8][9], and novel rocket propulsion technologies such as nuclear thermal rockets (NTR) and advanced chemical propulsion [10][11][12]. Most of these technologies have been developed separately, and there have been little research about how to optimally combine them.…”

Section: Introductionmentioning

confidence: 99%

Dynamic modeling and optimization for space logistics using time-expanded networks

Ho¹,

Weck²,

Hoffman³

et al. 2014

Acta Astronautica

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Section: Introductionmentioning

confidence: 99%

Dynamic modeling and optimization for space logistics using time-expanded networks

Ho¹,

Weck²,

Hoffman³

et al. 2014

Acta Astronautica

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“…Furthermore, previous architectural concepts have proposed using the collinear Earth-moon Lagrange points to stage mission infrastructure elements [26,27]. Many researchers have also concentrated on designing optimal high-thrust [28][29][30] and low-thrust trajectories within the cislunar system [31,32].…”

Section: Case Study Overviewmentioning

confidence: 99%

Event-Driven Network Model for Space Mission Optimization with High-Thrust and Low-Thrust Spacecraft

Jagannatha

2020

Journal of Spacecraft and Rockets

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Numerous high-thrust and low-thrust space propulsion technologies have been developed in the recent years with the goal of expanding space exploration capabilities; however, designing and optimizing a multi-mission campaign with both high-thrust and low-thrust propulsion options are challenging due to the coupling between logistics mission design and trajectory evaluation. Specifically, this computational burden arises because the deliverable mass fraction (i.e., final-to-initial mass ratio) and time of flight for low-thrust trajectories can can vary with the payload mass; thus, these trajectory metrics cannot be evaluated separately from the campaignlevel mission design. To tackle this challenge, this paper develops a novel event-driven space logistics network optimization approach using mixed-integer linear programming for space campaign design. An example case of optimally designing a cislunar propellant supply chain to support multiple lunar surface access missions is used to demonstrate this new space logistics framework. The results are compared with an existing stochastic combinatorial formulation developed for incorporating low-thrust propulsion into space logistics design; our new approach provides superior results in terms of cost as well as utilization of the vehicle fleet. The eventdriven space logistics network optimization method developed in this paper can trade off cost, time, and technology in an automated manner to optimally design space mission campaigns.(GMCNF) model [5,6]. These space logistics methods have been extended to campaign-level mission design framework using a time-expanded network by Ho et al [7,8]. These frameworks approach the problem of campaign design through a logistics-driven perspective. Other works such as the EXAMINE framework [9] and the graph-theory-based space system architectures model developed by Arney et al. [10] can compare and/or optimize user-input system architecture scenarios.A critical limitation of the conventional space logistics design methods referenced above is that they are unable to account for the use of low-thrust vehicles for transportation. More specifically, the conventional methods assumed a decoupling between logistics mission design and trajectory evaluation, where the mission design model takes pre-computed trajectory metrics such as the final-to-initial mass ratio (or ∆v) and time of flight for each arc as inputs and then optimize the mission architecture including the logistics flows of propellant, payload, and other commodities. This approach is effective for a campaign with a fleet of high-thrust spacecraft, and responded well to the background that many past space exploration campaigns considered only high-thrust spacecraft options (e.g., chemical propulsion). However, given the significant advancements made in low-thrust propulsion technology (e.g., SEP) in recent years, there is a growing interest in the question of how low-thrust spacecraft can be optimally integrated into a space exploration campaign. Thus, we need a mathematical fram...

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“…Additionally, oxygen production could lead to a complete closure in the ECLSS, while, together with hydrogen, could also support propellant production, and regeneration for fuel cell consumables. For both Mars and Earth-LEO-Moon sorties, propellant could be delivered to a space depot located at the Earth-Moon Lagrangian point 1 (EML1) or 2 (EML2) [15], [16], where lower ∆Vs are required for station-keeping, reducing mass to be launched and improving mission adaptability.…”

Section: Mission Scenariomentioning

confidence: 99%

Analysis of a Moon outpost for Mars enabling technologies through a Virtual Reality environment

et al. 2018

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The Moon is now being considered as the starting point for human exploration of the Solar System beyond low-Earth orbit. Many national space agencies are actively advocating to build up a lunar surface habitat capability starting from 2030 or earlier: according to ESA Technology Roadmaps for Exploration this should be the result of a broad international cooperation. Taking into account an incremental approach to reduce risks and costs of space missions, a lunar outpost can be considered as a test bed towards Mars, allowing to validate enabling technologies, such as water processing, waste management, power generation and storage, automation, robotics and human factors. Our natural satellite is rich in resources that could be used to pursue such a goal through a necessary assessment of ISRU techniques.The aim of this research is the analysis of a Moon outpost dedicated to the validation of enabling technologies for human space exploration.The main building blocks of the outpost are identified and feasible evolutionary scenarios are depicted, to highlight the incremental steps to build up the outpost. Main aspects that are dealt with include outpost location and architecture, as well as ISRU facilities, which in a far term future can help reduce the mass at launch, by producing hydrogen and oxygen for consumables, ECLSS and propellant for Earth-Moon sorties and Mars journeys. A test outpost is implemented in a Virtual Reality (VR) environment as a first proof-of-concepts, where the elements are computer-based mock-ups. The VR facility has a first-person interactive perspective, allowing for specific in-depth analyses of ergonomics and operations. The feedbacks of these analyses are crucial to highlight requirements that might otherwise be overlooked, while their general outputs are fundamental to write down procedures. Moreover, the mimic of astronauts' EVAs is useful for pre-flight training, but can also represent an additional tool for failures troubleshooting during the flight controllers' nominal operations. Additionally, illumination maps have been obtained to study the light conditions, which are essential parameters to assess the base elements location. This unique simulation environment may offer the largest suite of benefits during the design and development phase, as it allows to design future systems to optimize operations, thus maximizing the mission's scientific return, and to enhance the astronauts training, by saving time and cost.The paper describes how a virtual environment could help to design a Moon outpost for an incremental architecture strategy towards Mars missions.

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On-orbit depot architectures using contingency propellant

Cited by 11 publications

References 14 publications

Dynamic modeling and optimization for space logistics using time-expanded networks

Dynamic modeling and optimization for space logistics using time-expanded networks

Event-Driven Network Model for Space Mission Optimization with High-Thrust and Low-Thrust Spacecraft

Analysis of a Moon outpost for Mars enabling technologies through a Virtual Reality environment

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