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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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At least 577 records · Page 32
All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

Petrography and Mineralogy of Basalt Fragments in Apollo 17 Double Drive Tube 73002 and 73001

The ANGSA program was formed, in part, to examine previously unstudied Apollo 17 double drive tube samples. As a part of this project, the Moon United team received eight basalt fragments from 73001 and 73002. Here we present the petrography and mineralogy of these basalt fragments. Methods: We analyzed the petrography and mineralogy of the 73001/73002 particles using Electron Probe Microanalysis (EMPA) at both Carnegie Institution for Science and the Smithsonian Institution. We made quantitative compositional maps for each sample following the methods of [1,2].

S. N. Valencia↗
NASA NTRSDate not supplied

Solid State Drive Radiation Assurance With Active Testing

Automotive and industrial grade SSDs were tested for TID and SEE response at the assembly level to investigate radiation tolerance trends and explore radiation hardness assurance best practices in commercial memory devices. SSDs were installed in passive NVMe extenders to place only the drive in the beam line. A digital I/O module connected to the test computer provided inhibit signals to block both facility beam delivery and power while attempting recovery from any device failure conditions (e.g., failed write, failed read, or unresponsive device).

Edward P Wilcox↗
NASA NTRS1998

Thermal Performance of the Texas Instruments 1-W Linear Drive Cryocooler

The efficiency, of the electronics plays a large part in determining the overall spacecraft power requirements to operate the cooler as well as determining the thermal dissipation characteristics of the various electrical components. The results of all the performance measurements are presented in the paper.

linear drive cryocooler temperature thermal dissip↗
NASA NTRS2007

Key and Driving Requirements for the Juno Payload of Instruments

The Juno Mission was selected in the summer of 2005 via NASA's New Frontiers competitive AO process (refer to http://www.nasa.gov/home/hqnews/2005/jun/HQ_05138_New_Frontiers_2.html). The Juno project is led by a Principle Investigator based at Southwest Research Institute [SwRI] in San Antonio, Texas, with project management based at the Jet Propulsion Laboratory [JPL] in Pasadena, California, while the Spacecraft design and Flight System Integration are under contract to Lockheed Martin Space Systems Company [LM-SSC] in Denver, Colorado. the payload suite consists of a large number of instruments covering a wide spectrum of experimentation. The science team includes a lead Co-investigator for each one of the following experiments: A Magnetometer experiment (consisting of both a FluxGate Magnetometer (FGM) built at Goddard Space Flight Center GSFC] and a Scalar Helium Magnetometer (SHM) built at JPL, a MicroWave Radiometer (MWR) also built at JPL, a Gravity Science experiment (GS) implemented via the telecom subsystem, two complementary particle instruments (Jovian Auroral Distribution Experiment, JADE developed by SwRI and Juno Energetic-particle Detector Instrument, JEDI from the Applied Physics Lab (APL)--JEDI and JADE both measure electrons and ions), an Ultraviolet Spectrometer (UVS) also developed at SwRI, and a radio and plasma (WAVES) experiment (from the University of Iowa). In addition, a visible camera (JunoCam) is included in the payload to facilitate education and public outreach (designed & fabricated by Malin Space Science Systems [MSSS]).

challenges↗
NASA NTRS2023

Modeling and Mitigation of dv/dt and Transmission Line Effect for Motor Drive System in Electric Aircraft Propulsion

Due to constraints in space and structure as well as other practical limitations in aircraft system, the motor controller or electric motor are often installed far away from each other and interconnected via long cables. This amplifies the transmission line effect excited by the dv/dt PWM voltage and induces high voltage stress on the machine winding. This paper investigates the state-of-art modeling approaches for such systems, identifies several limitations in matching the tested voltage reflection waveform in terms of peak voltage, oscillation frequency and damping speed, and offers several key considerations not well covered in literature or in engineering practice. It then proposes a practical modeling methodology which, as validated by experimental results, truly captures these critical reflection voltage specs. To mitigate the high peak voltage and strong oscillation, dv/dt filter is applied and a parametric design optimization based on widely adopted LC-R topology is illustrated, which not only alleviates the voltage stress but also minimized the power loss of the passive damping resistor.

Inductor↗
NASA NTRSDate not supplied

Hard Fault Protection for a Silicon Carbide-Based Aerospace Motor Drive

Due to increasingly high DC link voltages and further advancements in the current density of silicon carbide (SiC) MOSFETs, it has become evident that conventional IGBT protection methods are not sufficient to protect these devices from overcurrent during low-inductance fault events. The use of an air core Rogowski coil topology was explored to see if it could mitigate these hard fault events. The design of this circuit resulted in safe shutdown of a low impedance phase-tophase fault, tested up to DC link voltages of 1 kV.

High Voltage↗