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Made in Space, We Propose an Entirely New Concept

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Made in Space, We Propose an Entirely New Concept EXECUTIVE SUMMARY “Those who control the spice control the universe.” – Frank Herbert, Dune Many interesting ideas have been conceived for building space-based infrastructure in cislunar space. From O’Neill’s space colonies, to solar power satellite farms, and even prospecting retrieved near earth asteroids. In all the scenarios, one thing remained fixed - the need for space resources at the outpost. To satisfy this need, O’Neill suggested an electromagnetic railgun to deliver resources from the lunar surface, while NASA’s Asteroid Redirect Mission called for a solar electric tug to deliver asteroid materials from interplanetary space. At Made In Space, we propose an entirely new concept. One which is scalable, cost effective, and ensures that the abundant material wealth of the inner solar system becomes readily available to humankind in a nearly automated fashion. We propose the RAMA architecture, which turns asteroids into self-contained spacecraft capable of moving themselves back to cislunar space. The RAMA architecture is just as capable of transporting conventional sized asteroids on the 10m length scale as transporting asteroids 100m or larger, making it the most versatile asteroid retrieval architecture in terms of retrieved-mass capability. ii This report describes the results of the Phase I study funded by the NASA NIAC program for Made In Space to establish the concept feasibility of using space manufacturing to convert asteroids into autonomous, mechanical spacecraft. Project RAMA, Reconstituting Asteroids into Mechanical Automata, is designed to leverage the future advances of additive manufacturing (AM), in-situ resource utilization (ISRU) and in-situ manufacturing (ISM) to realize enormous efficiencies in repeated asteroid redirect missions. A team of engineers at Made In Space performed the study work with consultation from the asteroid mining industry, academia, and NASA. Previous studies for asteroid retrieval have been constrained to studying only asteroids that are both large enough to be discovered, and small enough to be captured and transported using Earth-launched propulsion technology. Project RAMA is not forced into this constraint. The mission concept studied involved transporting a much larger ~50m asteroid to cislunar space. Demonstration of transport of a 50m-class asteroid has several groundbreaking advantages. First, the returned material is of an industrial, rather than just scientific, quantity (>10,000 tonnes vs ~10s of tonnes). Second, the “useless” material in the asteroid is gathered and expended as part of the asteroid’s propulsion system, allowing the returned asteroid to be considerably “purer” than a conventional asteroid retrieval mission. Third, the infrastructure used to convert and return the asteroid is reusable, and capable of continually returning asteroids to cislunar space. The RAMA architecture, as described in this report, was shown to be cross cutting through the NASA technology roadmap as well as the future goals of the greater aerospace industry. During the course of the study it was found that the RAMA technology path aligns with over twelve NASA roadmap missions across seven NASA technology areas, and has the opportunity to substantially improve the affordability and scalability of both the Human Exploration and Operations Mission Directorate (HEOMD) and the Science Mission Directorate (SMD) stated goals. The approach to studying this concept started with the development of Rock Finder, a rapid optimization tool for identifying suitable asteroids for utilization. In parallel to the Rock Finder development, a trade study was performed on various ISRU and ISM technologies. A technology roadmap was created to identify suitable technologies for turning asteroids into spacecraft. Rock Finder was then used to identify a single S-type asteroid, and a mission assessment was performed for a specific set of technologies, showing the feasibility of performing a RAMA style mission with the asteroid. The end results suggest that the RAMA architecture is a feasible way to automate a self-perpetuating suite of asteroid exploration, discovery, and utilization missions within a twenty to thirty year time horizon, demonstrating a maturation of the technology from TRL 1 to TRL 2. iii PROJECT RAMA TEAM Jason Dunn Max Fagin Michael Snyder Eric Joyce Principle Investigator Lead Project Engineer Chief Engineer Project Manager Cofounder and CTO at As the lead project Cofounder and Chief As project manager of Made In Space, Jason engineer for the study, Engineer at Made In the RAMA study Eric served the project as Max focused heavily the Space, Mike was in managed the overall the PI. His role focused technical details of all charge of overseeing budget and schedule of on the overall work plan elements. the technical the effort. His organization of the work The Rock Finder development efforts of background expertise in plan and customer program was created by the study. He was space resources and deliverables. Jason also Max and was used to instrumental in mission planning was managed the design the overall determining the vital in directing the relationships with mission concept and appropriate study path overall path of the study industry and academic trajectories. Much of the to be executed on, and effort. Eric was active experts. Jason was a detailed mission directed the engineering throughout the study main author of this concept is credited to focus. maintaining alignment to report. Max. Max was a main study goals. author of this report. Supporting Roles Phil Metzger, University of Central Florida – Phil brought his experience in ISRU and space resources to the RAMA study as a lead advisor to the work. The RAMA team consulted with Phil on mission concept design and resource mining options. Andrew Rush, Made In Space, CEO – Andrew provided a role of ensuring the RAMA study maintained alignment to the overall Made In Space business focus. His contributions were seen through in depth reviews of work and connection to other Made In Space development programs. iv TABLE OF CONTENTS 1 Introduction and Background _____________________________________________________ 1 1.1 Problem and Motivation ______________________________________________________ 1 1.2 A Vision of Space Development ________________________________________________ 3 1.3 The RAMA Solution __________________________________________________________ 4 1.4 Related Work at Made In Space ________________________________________________ 5 1.5 Asteroids: What and Where? __________________________________________________ 6 2 RAMA Architecture Concept _____________________________________________________ 12 2.1 The Asteroid Spacecraft _____________________________________________________ 12 2.2 Mechanical Systems Capabilities & Limits ______________________________________ 12 2.2.1 Creating Spacecraft From Mechanical Systems _________________________________ 12 2.2.2 Subsystem Requirements __________________________________________________ 14 2.2.3 Advanced Mechanical Computers ___________________________________________ 14 2.2.4 RAMA Functional Block Diagram ____________________________________________ 15 2.2.5 Mechanical Systems Limits _________________________________________________ 17 2.3 The Seed Craft _____________________________________________________________ 18 2.4 Mission Implementation—Stockpiling Multiple NEAs at an Earth­Moon Lagrange Point 19 3 Project RAMA Phase I Work _____________________________________________________ 21 3.1 Technical Approach _________________________________________________________ 21 3.2 Rock Finder - Mission Design Tool ____________________________________________ 21 3.2.1 Why Rock Finder Was Needed ______________________________________________ 21 3.2.2 What Rock Finder Does ___________________________________________________ 22 3.2.3 How Rock Finder Works ___________________________________________________ 25 3.2.4 Limits and Future Development _____________________________________________ 26 3.3 Asteroid Spacecraft System Level Design ______________________________________ 27 3.3.1 Asteroid Spacecraft Design Methodology ______________________________________ 27 3.3.2 Subsystem Feasibility Assessment __________________________________________ 27 3.3.3 Asteroid Spacecraft Subsystem Analysis ______________________________________ 27 3.3.4 Selected Methods ________________________________________________________ 33 3.4 ISRU Manufacturing Assessment _____________________________________________ 33 3.4.1 In-Situ Resource Availabilities and Opportunities ________________________________ 33 v 3.4.2 In-Situ Manufacturing Trade Study ___________________________________________ 41 3.5 S-Type Asteroid Mission Assessment __________________________________________ 47 3.5.1 The Far End of the Spectrum – Asteroid 2009 UY19 _____________________________ 50 3.6 C-Type Asteroid Mission Assessment _________________________________________ 63 3.7 M-Type Asteroid Mission Assessment _________________________________________ 64 3.8 Asteroid Hopping Mission Assessment ________________________________________ 64 3.9 Value Proposition for RAMA-Based Asteroid Exploration __________________________ 65 3.9.1 Comparison to Other Missions ______________________________________________ 65 3.9.2 Relevance to NASA Technical Roadmap ______________________________________ 66 3.9.3 Benefits of the RAMA Program Thus Far ______________________________________ 68 3.10 RAMA Technical Feasibility Assessment ______________________________________
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