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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Retrospectively Documenting Satisfaction of the Overarching Properties: An Exploratory Prototype
Software-intensive aviation systems are typically developed in accordance with recognized development process, safety analysis, and software development standards such as SAE ARP4754A, SAE ARP4761, and RTCA DO-178C. Efforts to streamline assurance processes and make them flexible enough to handle future assurance challenges have produced the Overarching Properties (OPs) for airworthiness approval. Each of the three OPs is a property systems must possess to be certifiable. There is no mandated means of documenting possession of the OPs. To explore possible means, we have prepared retrospective documentation showing that a specimen software system possesses the OPs. The specimen system, Safeguard, enforces geofencing restrictions on unmanned aerial vehicles. Our OP-possession case for its airborne component comprises eight arguments in the Goal Structuring Notation (GSN): a main argument for each OP and five cross-cutting auxiliary arguments. We present this argument as an example for discussion and further research, e.g., into means of assessing OP possession.
Technical Primer on Design and SPICE Modeling of Circuits for NASA Glenn SiC JFET IC Generation 13 Prototype Wafer Run - Part 1: SiC JFET Behavior and SPICE Modeling
Goal: Enable anyone to SPICE-model and design 500 °C durable integrated circuits for their intended application.
Technical Primer on Design and SPICE Modeling of Circuits for NASA Glenn SiC JFET IC Generation 13 Prototype Wafer Run - Part 2: SiC Resistor Behavior and SPICE Modeling
Goal: Enable anyone to SPICE-model and design 500 °C durable integrated circuits for their intended application.
STEM Takes Flight ED1: Design and Prototype of 3D Printed Wind Tunnel Model with Integrated Force Measurement System
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ED1: Design and Prototype of a 3D Printed Wind Tunnel Model with Integrated Force Measurement
Wind tunnel testing using conventionally manufactured force measurement systems (balances) is able to yield precise and accurate results. These balances are delicate, complex instruments. Due to the nature of this high-precision complexity, balances are expensive and time-consuming to produce. These factors can limit the design potential of the model because using conventionally manufactured balances generally means that the model is designed to accommodate balances that already exist. Ideally, engineers would be able to design a measurement system that is tailored to fit the needs of the model, rather than the other way around. The goal of this research project was to determine if it is possible to overcome these drawbacks by designing a wind tunnel model with a modifiable integrated force measurement system that leverages additive manufacturing. This was undertaken by utilizing the existing UT-63 wind tunnel balance (measurement system), integrating it with a model based on the existing AGARD-B model, and performing stress analysis to optimize the design. Due to time constraints, the result of this endeavor is currently incomplete. Continued analysis and optimization are required to have a thorough understanding of the success or failure of the attempted design. As additive manufacturing technology evolves, the ability for it to become the primary method of fabrication for sensitive measurement systems increases. This project contributes to this by providing one method for design, a framework for optimizing existing balances for additive manufacturing, and resources for performing necessary stress analysis.
Prototyping and Evaluating NUCAPS-Aqua as Part of a Multi-instrument Near-real Time Capability to Support Pre-convective Forecasting
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Joint Augmented Reality Visual Informatics System Project: HID Prototype System Goals for FY22
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A Prototype Model for Conducting Trades on NASA Food Systems
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Highlights of Aeroacoustic Tests of a Metal Spacecraft Cabin Ventilation Fan Prototype
A metal spacecraft cabin ventilation fan suitable for aerodynamic and acoustic ground tests was designed and tested in the NASA Glenn Research Center Acoustical Testing Laboratory. The fan design featured a low-noise blade-vane count that was chosen to reduce the rotor-stator interaction tone noise. The fan was throttled through its operating range, and results indicate that the measured aerodynamic and acoustic performance was in good agreement with predictions. Recommendations for further research of quiet high-performance fans intended to support long duration human space exploration missions are offered. This small fan aerodynamic and acoustic test rig and the NASA Glenn Acoustical Testing Laboratory are valuable resources available for supporting NASA’s aeronautics research and space exploration missions.
Mem-Models and State Event Location Algorithm for a Prototypical Aerospace System
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