Inflatable Antenna for CubeSats: Development of the X-Band Prototype
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Atmospheric entry vehicle thermal protection systems (TPS) are margined due to the uncertainties that exist in entry aeroheating environments and the thermal response of the materials and structures. Traditional approaches typically over-margin TPS and offer very little insight into the risk of over-temperature during flight. A probabilistic margin process can be used to apply thermal margin to an aeroshell based on a rigorously calculated risk of failure. This probabilistic margin process allows engineers to make informed aeroshell design, entry-trajectory modifications, and risk trades while preventing excessive margin from being applied. This methodology can also be applied to other TPS applications, hot structures, and other engineering disciplines.
We currently are studying an advanced space Very Long Baseline Interferometry (VLBI) mission
This paper will present an overview of all three ASPIRE flights. First, the Test Architecture that was used for all three ASPIRE flights will be presented. This will be broken down into an explanation of the Concept of Operations (CONOPS),the parachute test articles, the data sources used, and the process that was used to reconstruct the flight trajectories and parachute performance. Next, the performance and results for all three ASPIRE flights will be presented in the order of the phases of flight. Lastly this paper will discuss the Conclusions and Lessons Learned from those results and from the ASPIRE project as a whole.
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