SEARCH · Engineering Papers
Results for “CaIn”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Method for the Manufacturing of a Composite
Described herein are composites that are relatively lightweight, high strength and low thermal conductivity. Also described herein are methods for the manufacture and use thereof.
Periodic Eclipse Variations in Asynchronous Polar V1432 Aql: Evidence of a Shifting Threading Region
We report the results of a 28-month photometric campaign studying V1432 Aql, the only known eclipsing, asynchronous polar. Our data show that both the residual eclipse flux and eclipse O−C timings vary strongly as a function of the spin-orbit beat period. Relying upon a new model of the system, we show that cyclical changes in the location of the threading region along the ballistic trajectory of the accretion stream could produce both effects. This model predicts that the threading radius is variable, in contrast to previous studies which have assumed a constant threading radius. Additionally, we identify a very strong photometric maximum which is only visible for half of the beat cycle. The exact cause of this maximum is unclear, but we consider the possibility that it is the optical counterpart of the third accreting polecap proposed by Rana et al. Finally, the rate of change of the white dwarf's spin period is consistent with it being proportional to the difference between the spin and orbital periods, implying that the spin period is approaching the orbital period asymptotically.
Mission Configuration Tree for the James Webb Space Telescope (JWST)
The GSFC Mission Configuration web-based application is a means of documenting the structure of the many elements used in building each mission that NASA launches, as well as archiving the documents associated with each of these elements and keeping track of suppliers. This includes all available drawings, engineering orders, parts lists, block diagrams, and photos of each system, subsystem, and component. While the information for several of NASA's missions is being input into Mission Configuration, the ten weeks of this project focused on collecting information for the instrument systems of the James Webb Space Telescope. Documents were collected from a database called the Next Generation Integrated Network (NGIN) so that they can eventually be uploaded into the application. From these documents, including drawings and parts lists, a configuration tree was created in Microsoft Visio which showed the relationships between each system, subsystem, and component. When both these documents and the configuration tree are input into Mission Configuration, they will be place into a drill down tree structure, from which drawings and documents can be accessed directly. Mission Configuration also includes search functions that make all parts searchable by keywords such as vendor, part number, taxonomy, and alternate nomenclature. This application is an important resource for providing access to documents related to the components used on each mission. It has created a central repository for information which can be used to benefit Safety & Mission Assurance, but may also be useful across codes. The process of collecting the information and documents to put into Mission Configuration is also allowing for a concise breakdown of information from diverse formats, creating standardization which makes information more readily accessible, while retaining project-specific information that makes it more easily searchable.
Lunar Equator Regenerative Fuel Cell System Efficiency Analysis
It is expected that future NASA mission energy storage requirements can be adequately met by regenerative fuel cells (RFCs). Aerospace RFCs are likely to package proton exchange membrane electrochemical conversion devices based on hydrogen, oxygen, and water. To optimize system designs and direct further development, the most useful system metric is round-trip efficiency (RTE). Improving RTE generally increases specific energy and reduces system mass. The following analysis models the impact of several factors on RTE for RFCs scaling from 0.1 to 50 kW. The analysis demonstrates that higher electrolyzer (EZ) operational pressure most negatively impacts both RFC RTE and specific energy. Reactant storage heating and power management losses are significant for RFCs of any scale, but solenoid valve power becomes a noticeable parasitic load for smaller RFCs. Spherical gas storage vessels benefit RTE by only 2 to 4 percentage points but increase specific energy by ~50 percent. Cryogenic reactant storage is shown to depress RTE to below 15 percent in all cases. For a given RFC scale, there is an RTE benefit to specifying larger EZs and recharging at higher rates—if the RFC can be coupled with a corresponding power source. Although fuel cell (FC) operation is less impactful on RTE than EZ factors, efficiency is maximized by sizing the FCs relatively large and keeping current density low. RFC design is a balance of many interrelated factors, but this analysis provides a starting point for difficult decisions that must be made when designing a lunar equator RFC.
Bi-furcated Reversible Alkaline Cell for Energy Storage (BRACES) TP
Explore the source record for details and available documents.
Propellant Fueled Solid Oxide Fuel Cell (PropFC) TP
Explore the source record for details and available documents.
Aerospace Regenerative Fuel Cell Fluidic Component Design Challenges
A discrete regenerative fuel cell (RFC) system is currently under development at the NASA Glenn Research Center and Johnson Space Center. The objective of this activity is to produce an energy storage system with a higher specific energy (W·hr/kg) than the state-of-the-art battery technologies then test that system within an environment simulating the temperatures and pressures expected over a full lunar day cycle on the lunar surface. The system is designed to be as flight-like as possible given resource and commercially available technology limitations. The RFC system is comprised of a fuel cell power system, a high pressure electrolysis system, fluidic and electronic balance of plant systems, avionics, power management and distribution system, and software. This technical memorandum discusses components and subsystems that present challenges in developing flight ready RFCs. To remedy identified issues, functional application test plans are presented for components and subsystems primarily constructed with commercially available options due to the budget and schedule constraints of this ground technology demonstration project.
Regenerative Fuel Cell Systems for Lunar Surface Applications
A discrete Regenerative Fuel Cell (RFC), comprised of a Proton Exchange Membrane (PEM) Fuel Cell (FC) system integrated with a PEM Electrolyzer (EZ) system, can provide energy conversion and storage options for applications where batteries are not practical. This includes missions on the lunar surface where long charge and discharge periods result in extremely high battery system mass for sufficient energy storage. While both PEM FC and PEM EZ are mature terrestrial technologies, there is still a lot of development needed for aerospace applications. Integrating the PEM FC and PEM EZ systems together requires the integration of multiple thermal, fluid, and electrical subsystems, increasing the complexity of the overall RFC system. Additionally, Balance of Plant (BoP) components and subsystems play a crucial role in the effective performance to maximize the RFC round trip efficiency. This presentation will give a high-level overview of RFCs, select BoP components including a catalytic recombiner and gas drying equipment, and the current testing that is being done on the RFC project at NASA GRC.
Lunar South Pole Regenerative Fuel Cell System Efficiency Analysis
It is expected that future NASA mission energy storage needs can be adequately met by regenerative fuel cells (RFCs). Aerospace RFCs package proton exchange membrane (PEM) electrochemical conversion devices based on hydrogen, oxygen, and water. To optimize system designs and direct further development, the most useful system metric is round-trip efficiency (RTE). Improving RTE generally increases specific energy and reduces system mass. The following analysis models the impact of several factors on RTE for RFCs at the lunar south pole scaling from 0.1 kW to 50 kW. The analysis demonstrates that higher electrolyzer operational pressure most negatively impacts both RFC RTE and specific energy. Optimal electrolyzer membrane thickness is evaluated as a function of operational current density and pressure. Reactant storage heating and power management losses are significant for RFCs of any scale but are reduced in impact at the south pole compared to colder equator applications. Solenoid valve power remains a noticeable parasitic load for smaller RFCs. Larger electrolyzers enable higher peak theoretical efficiencies when recharging at higher rates, if the RFC can be coupled with a corresponding higher power source. RFC design is a compromise of many interrelated factors, but this analysis provides a starting point for difficult decisions that must be made when designing a lunar south pole RFC.
Lunar South Pole Regenerative Fuel Cell System Efficiency Analysis
Explore the source record for details and available documents.
Space Technology Mission Directorate - Game Changing Development Program: FY22 BRACES-TP Annual Review Presentation
Explore the source record for details and available documents.
Advanced Alkaline Fuel Cell (AARC) ACO
Explore the source record for details and available documents.
Venus Aerosol and Cloud Simulator (VACS)
Explore the source record for details and available documents.
Earth/Moon System Star Tracking Sensor for Improved Deep Space Laser Communications
The goal of this research is to improve deep space communication links by exploring a new concept in stellar navigation that uses images of the Earth/Moon system to obtain precise pointing information so that the laser signal from the satellite can be directed at the ground station with unprecedented accuracy. Currently, the concept for satellite pointing relies on a dual axis star tracker that compares images of the celestial sphere to a star catalog to obtain a 3-axis orientation solution. Most star trackers are designed with a wide field of view (required to obtain enough bright starts to achieve a navigational fix) and only provide reliable pitch and yaw estimates thus necessitating the use of a second star tracker looking at an axis perpendicular to the first one to obtain an accurate estimate of the roll of the spacecraft. In the new concept the optical design will be modified to ensure that both the Earth and the Moon will be within a narrow field of view centered on Earth relative to the field of view of most star tracking systems. Because of the proximity of the bodies, it is possible to obtain highly accurate estimates of the pitch, yaw and roll of the spacecraft relative to the Earth/Moon system. The new tracker will allow for accurate 3-axis control of the spacecraft from a single tracker thus allowing the second star tracker, which would normally be pointed in a direction perpendicular to the one pointed at earth, to obtain the spacecraft roll estimate. This wide field star tracker facilitates functions like the initial satellite pointing during the acquisition phase of establishing the laser communication link or solving the lost in space problem should the system need to be reset. This new design will be tested in simulation and compared for 3-axis pointing accuracy against a standard commercial star tracker.
FY23 BRACES-TP Annual Review Presentation
Explore the source record for details and available documents.
Bifurcated Reversible Alkaline Cell for Energy Storage Tipping Point (BRACES-TP)
Develop a highly integrated and novel unitized reversible fuel cell (URFC) system that enables reliable, long duration energy storage at significantly higher energy density than state-of-the-art systems.
Space Rated High Voltage Plasma Generating Supply
The use of plasma for in-situ resource utilization (ISRU) applications (such as water treatment, acid production, plant seed activation, biofilm sanitization, or waste gasification) is an active area of research at the KSC Applied Chemistry Lab (ACL). The generation of plasma for experimentation has thus far been done with lab-rated power supplies which are unsuitable for space applications, and no suitable supply is readily available for purchase. This project tackled the development of a low TRL prototype 500 W power supply intended for generating plasma in space. The design was based on similar power electronic circuits used for electric propulsion systems and was adapted for use in ISRU applications. This technology will enable KSC’s plasma-based ISRU related technologies to be demonstrated in the space environment.