Simple logistics strategies such as "carry-along" and Earth-based "resupply" were sufficient for past human space programs. Next-generation space logistics paradigms are expected to be more complex, involving multiple exploration destinations and insitu resource utilization (ISRU). Optional ISRU brings additional complexity to the interplanetary supply chain network design problem. This paper presents an interdependent network flow modeling method for determining optimal logistics strategies for space exploration and its application to the human exploration of Mars. It is found that a strategy utilizing lunar resources in the cislunar network may improve overall launch mass to low Earth orbit for recurring missions to Mars compared to NASA's Mars Design Reference Architecture 5.0, even when including the mass of the ISRU infrastructures that need to be pre-deployed. Other findings suggest that chemical propulsion using LOX/LH 2 , lunar ISRU water production, and the use of aerocapture significantly contribute to reducing launch mass from Earth. A sensitivity analysis
We examine the use of real-options valuation in the context of prioritizing advanced technologies for NASA funding. Further, we offer a set of computational procedures that quantifies the option value of each technology. Other researchers have applied a real-options framework to private sector investments. In the case of NASA investments in advanced technologies, the underlying products, which must be used to justify the investments, are nearly pure public goods-in particular, space-related scientific results and discoveries to be shared worldwide. As in the private sector, uncertainty plays a significant role in the motivation to use real options in NASA. Uncertainty in NASA technology investments can be classified as development risk and programmatic risk (whether missions using the technology will actually fly). The latter might be called the technology's "market risk."We carried out the approach on a number of planetary exploration technologies. We illustrate the detailed calculations using one of them lightweight propellant tank technology.
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