21 research outputs found

    Superconductivity in zirconium-rhodium alloys

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    Metallographic studies and transition temperature measurements were made with isothermally annealed and water-quenched zirconium-rhodium alloys. The results clarify both the solid-state phase relations at the Zr-rich end of the Zr-Rh alloy system and the influence upon the superconducting transition temperature of structure and composition

    Thermal Cycling Equipment

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    Apparatus for measuring the thermal conductivities of metals /

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    "Operated by the University of Chicago under Contract W-31-109-eng-38."At head of title: Argonne National Laboratory."This report supersedes information in the following Metallurgy Division reports: ANL-5541 pp. 39-42 October, November & December 1955; ANL-5975 pp. 62-63 March 1959.""Final report - Metallurgy Program 4.1.20.""October, 1959."Includes bibliographical references (p. 15) and abstract.Mode of access: Internet

    Mechanical stabilization of uranium fuel elements /

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    Portions of the material contained in this report have been given in the following reports: ANL-4825, pages 83, 84; ANL-4860, pages 87, 88; ANL-5036, pages 12-14; ANL-5097, pages 18-21; ANL-5153, pages 20, 21; ANL-5257, page 43; ANL-5338, pages 74, 75; ANL-5439, pages 25, 27-29; TID-5185 (Pt.1), pages 200-207.Includes bibliography references.Mode of access: Internet

    Comparative Benchmarking of Crewed Lunar and Mars Mission Architectures

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    © 2020 The MITRE Corporation. All Rights Reserved. Fuel selection is a strong driver of the mass fraction for many proposed lunar and Mars missions, but fuel technology trends have not been comprehensively evaluated for their impact on the system in literature. We evaluate the impact of fuel selection on overall lunar architectures. Our analysis shows that although hydrogen architectures have a higher wet mass cost, they provide more payload capacity to the lunar surface than non-hydrogen architectures given the same number of campaign launches. The Moon has been viewed as a stepping stone for future planetary exploration, so we evaluate both Mars and lunar architectures. We functionally decompose architectural decisions and compare key campaign decisions across 18 notable Mars architectural studies. The 18 landers are classified into four groups depending on which of the four the functional capabilities the lander performs, namely outbound transit, mars descent, mars ascent, and inbound transit. We find that there is no strong relationship between the Martian landers’ wet mass and the length of crewed Martian surface. Furthermore, fuel type selection did not have a clear trend with the aforementioned capabilities. The lack of similarities across Mars architectures suggests the reference studies had a wide range of depths of analysis along with an array of different methods. Furthermore, they were completed at various points in history, some with high political pressure
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