Computational and Physics-Based Modeling for the Development of in-Space Welding Technology

Jeffrey W Sowards; Ellis Crabtree; Andrew O'Connor; Christopher S Protz

NASA NTRS · 20240012632

Computational and Physics-Based Modeling for the Development of in-Space Welding Technology

Jeffrey W Sowards·Ellis Crabtree·Andrew O'Connor·Christopher S Protz

Abstract

Welding will be an enabling technology for in-space assembly and manufacturing (ISAM) and in-space repair operations in support of the growing Space Economy. Prospective use cases of welding include metal repair on long-duration lunar surface missions and assembly of large structures that exceed dimensions of the currently available launch vehicle envelopes such as space arrays, tall lunar transmission towers, or even large transit vehicles powered by nuclear propulsion. There is a brief history of beam welding for in-space use. Soviet and NASA astronauts performed electron beam welds (EBW) in space in the late-1960s through mid-1980s and several parabolic flights of laser beam welding (LBW) were undertaken in the USA and Canada in the early-1990s. Work has since stagnated until the recent boom of the in-space economy has demonstrated need for continued development of EBW and LBW processes, which are desirable for their compactness, low mass, low power consumption, and high wall plug efficiency. No space-based manufacturing laboratory capable of demonstrating, developing, and applying welding processes exists, and costs are high to develop and fly individual space-based trials. This drives the current approach to develop welding technology with computational and physics-based models in tandem with earth-based experiments. Several approaches are taken to complement and drive the selection of instrumentation for planned parabolic and suborbital flights. First, a thermal model of Skylab EBW experiments is established and compared to empirical data. Next, the model is used to show variation between Earth-based and in-space weld structure and properties through exploration of key variables that define the Low earth orbit and lunar surface space environments, namely temperature (40 – 400 K), pressure (10-10 to 104 Pa), and gravity (10-6 g to 1 g). Finally, physical processes associated with heat and mass transport during welding are evaluated through several case studies across the above variable ranges demonstrating need for further research.

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in-space welding electron beam welding Skylab M551 ICME CALPHAD KWN precipitation FEA thermal modeling 2219-T87

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Jeffrey W Sowards, Ellis Crabtree, Andrew O'Connor, Christopher S Protz. Computational and Physics-Based Modeling for the Development of in-Space Welding Technology. https://ntrs.nasa.gov/citations/20240012632

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