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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 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS2015

Status of Shock Layer Radiation Validation Studies

This paper presents a status update for the shock layer radiation validation studies conducted at NASA. A review of the present capability for the simulation and validation of shock layer radiation is presented as well as providing an overview of the data obtained from the Electric Arc Shock Tube (EAST). The paper will include details covering updated convective and radiative heating correlations, provide an overview of the development of new kinetics for Mars entry and detail some recent work calculating after-body radiation. Furthermore, the paper will highlight conditions where there is high confidence in the validation of EAST data (e.g. Earth entry for speeds greater than approximately 10 kms and for many Mars entry conditions) and where further experimental data would be highly beneficial (e.g. lower speed Earth entry around 7.5 to 10 kms and higher speed CO2 entries relevant to Venus). Nominal test conditions for both Earth and Mars are provided for future potential facility-to-facility comparisons.

Entry systems modeling↗
NASA NTRS2002

The Design and Use of Calorimeters For Characterization of High-Enthalpy Flows in Arc-Heated Test Facilities

High-enthalpy, arc-heated flows used for aerothermal testing present a challenging environment for flow characterization. This paper describes the design and use of cooled dwell probes used for heat-transfer and pressure characterization of the NASA and United States Department of Defense (DoD) arc facilities located at Moffett Field, CA, and Arnold Air Force Base, TN. Dwell calorimeters designed, fabricated, and tested by Thermal Technologies, Inc. (TTI) in the NASA IHF and the USAF H1 and H2 arc test facilities provide heat flux and pressure data with excellent repeatability. These calorimeters use standard Gardon calorimeter gages and pressure ports with unique cooling systems enabling them to withstand the severe arc-heated environments for durations sufficient for acquisition of steady-state data. The TTI probes have proven very robust in the extreme aerothermal environments of these facilities. This paper provides an overview of calorimeter instruments typically used in arc facilities, discusses design features of the TTI dwell probes, presents selected data acquired by the TTI calorimeters, and provides comparisons with data acquired from using measurement techniques.

D Mark Smith↗
NASA NTRS1996

Life and Biomedical Sciences and Applications Advisory Subcommittee Meeting

The proceedings of the August 1995 meeting of the Life and Biomedical Sciences and Applications Advisory Subcommittee (LBSAAS) are summarized. The following topics were addressed by the Subcommittee members: the activities and status of the LBSA Division; program activities of the Office of Life and Microgravity Sciences and Applications (OLMSA); the medical Countermeasures Program; and the Fettman Report on animal research activities at ARC. Also presented were a history and overview of the activities of the Space Station Utilization Advisory Committee and the Advanced Life Support Program (ALSP). The meeting agenda and a list of the Subcommittee members and meeting attendees are included as appendices.

Source record↗
NASA NTRS2021

Overview of Dragonfly Entry Aerosciences Measurements (DrEAM)

NASA Ames Research Center (ARC) leads the Dragonfly Entry Aerosciences Measurements (DrEAM) project, which is an aeroshell instrumentation suite on the Dragonfly mission that fulfills the Engineering Science Investigation requirement for the New Frontiers mission. NASA ARC is partnering with NASA Langley Research Center (LaRC) and the German Aerospace Center (DLR) to provide a comprehensive sensor suite, including a DLR-provided Data Acquisition System (DAS). DrEAM will provide key aerothermodynamic data and performance analysis for Dragonfly’s forebody and backshell Thermal Protection System (TPS). Titan’s atmosphere predominantly consists of ni-trogen (~98% by mole) with small amounts of me-thane (~2% by mole) and other trace gases. CN is a strong radiator, and is found in nonequilibrium con-centrations for Titan entry. The accurate modeling of nonequilibrium CN radiation has proven to be a diffi-cult task. Prompted by the Huygens mission, many experimental campaigns and analyses were performed to better understand the aerothermal environments experienced by the probe during Titan entry [1]. How-ever, the Huygens probe carried no heatshield instru-mentation. Therefore, the DrEAM sensor suite will sig-nificantly advance the state-of-the-art not only by documenting the environment and performance of Dragonfly’s entry system but also by making key in situ measurements in Titan’s atmosphere for the first time. Aerothermal environments and TPS response will be measured using sensors whose flight heritage is tak-en from the Mars Entry, Descent, and Landing In-strumentation 2 (MEDLI2) thermocouple plugs and the COMbined Aerothermal and Radiometer Sensor (COMARS) suite [2], with the latter supplied by DLR. The MEDLI2 project used embedded thermocouples to directly measure the in-depth TPS temperature-time history at several locations on the heat shield and backshell of the Mars 2020 entry vehicle. These tem-perature measurements, in turn, can be used to infer surface environments via an inverse analysis proce-dure analogous to that used for MEDLI. For DrEAM, the thermocouple plug subsystem will be known as Dragonfly Sensors for Aero-Thermal Reconstruction (DragSTR). On Schiaparelli, the COMARS suite in-cluded three total surface-mounted heat flux sensors, three pressure sensors, and one radiometer. For DrEAM, the COMARS package will be known as the COmbined Sensor System for Titan Atmosphere (COSSTA). Since the methane concentration in the Titan atmos-phere is directly proportional to the radiative heat flux, the COSSTA measurements will be used to reduce the current uncertainty in the methane volume fraction. Atmospheric density measurements and capsule aero-dynamic data will be obtained through the onboard Inertial Measurement Unit (IMU), supplemented by pressure transducers similar to those used by the MEDLI and MEDLI2 projects. The DrEAM pressure sensors will be known as the Dragonfly Atmospheric Flight Transducers. (DrAFT). The pressure measure-ments, when combined with data from the on-board IMU, will allow for reconstruction of such quantities as vehicle Mach number, freestream density, and atmos-pheric winds. DrAFT measurements will enhance Dragonfly trajectory reconstruction and enable a sepa-ration of the aerodynamics from the atmosphere, as was done for MEDLI [3] and is currently in process for the MEDLI2 flight data set.

EDL↗
NASA NTRSDate not supplied

NASA’s Unsteady Pressure-Sensitive Paint Phase I Development Overview

Since 2019, a group out of NASA Ames Research Center(ARC)has been focused on implementing systematic updates to make unsteady pressure-sensitive paint (uPSP) a more viable capability for production wind tunnel testing. Focusing on the general categories of data acquisition, data transfer, data processing, and data visualization, the uPSP Development Team has made several improvements to increase data quality and innovate a more workable system that would provide valuable surface pressure data to customers. As a result of the COVID-19 pandemic and several initial demonstration tests prior to the formal start of the development effort, the decision was made to focus on launch vehicles as the test article. To-date this development has focused on implementation in the ARC Unitary Plan Wind Tunnel 11-by11-footTransonic Wind Tunnel due to the large optical access of the test section and that the NASA Advanced Supercomputer is located at ARC. This paper summarizes the project origins and the results of four years of development effort, which will all culminate in a final demonstration test in the first half of2024.

unsteady pressure-sensitive paint↗
NASA NTRS2007

NASA-STD-4005 and NASA-HDBK-4006, LEO Spacecraft Solar Array Charging Design Standard

Two new NASA Standards are now official. They are the NASA LEO Spacecraft Charging Design Standard (NASA-STD-4005) and the NASA LEO Spacecraft Charging Design Handbook (NASA-HDBK-4006). They give the background and techniques for controlling solar array-induced charging and arcing in LEO. In this paper, a brief overview of the new standards is given, along with where they can be obtained and who should be using them.

Ferguson, Dale C.↗
NASA NTRSDate not supplied

Bridging the Gap Between Microscale Modeling and Additive Manufacturing for TPS

An overview of the now open-source NASA ARC software PuMA will be provided. On top of the well-documented ability to import and compute material properties from micro-CT images, PuMA has the ability to design microstructures and compute/predict material properties such as: porosity, permeability, tortuosity, thermal and electrical conductivity, tensile strength, etc. Therefore, a whole new range of capabilities is available, and provides users with the ability to build TPS materials (both fibrous and woven types) and optimize their properties based on missions and requirements. This talk will aim to provide a seed to start bridging the gap between microscale modeling of TPS materials and additive manufacturing.

Conductivity↗
NASA NTRSDate not supplied

Development and Sizing of the Mars 2020 Thermal Protection System

The Mars 2020 entry vehicle successfully delivered the Perseverance rover to the Martian surface on 18 February 2021. The entry vehicle aeroshell was shielded from aerodynamic heating with a thermal protection system (TPS) made of three different ablative materials. This paper provides an overview of the methodology and assumptions employed for the thermal sizing and design of the Mars 2020 aeroshell TPS. The sizing results demonstrate that the as-built thicknesses of the TPS materials were sufficient to withstand the predicted aerothermal environments without exceeding temperature limits of the underlying aeroshell structure. This paper also provides an overview of the ground testing performed in NASA arc jet facilities to verify the performance of flight lot TPS materials. Finally, temperature data returned by thermocouples embedded in the flight vehicle TPS are compared with predictions by the thermal response models used in pre-flight TPS sizing.

Mars2020↗
NASA NTRSDate not supplied

Development and Sizing of the Mars 2020 Thermal Protection System

The Mars 2020 entry vehicle successfully delivered the Perseverance rover to the Martian surface on 18 February 2021. The entry vehicle aeroshell was shielded from aerodynamic heating with a thermal protection system (TPS) made of three different ablative materials. This paper provides an overview of the methodology and assumptions employed for the thermal sizing and design of the Mars 2020 aeroshell TPS. The sizing results demonstrate that the as-built thicknesses of the TPS materials were sufficient to withstand the predicted aerothermal environments without exceeding temperature limits of the underlying aeroshell structure. This paper also provides an overview of the ground testing performed in NASA arc jet facilities to verify the performance of flight lot TPS materials. Finally, temperature data returned by thermocouples embedded in the flight vehicle TPS are compared with predictions by the thermal response models used in pre-flight TPS sizing.

Mars2020↗
NASA NTRS1990

The solar optical telescope

Objectives of the Solar Optical Telescope are to study the physics of the Sun on the scale at which many of the important physical processes occur and to attain a resolution of 73km on the Sun or 0.1 arc seconds of angular resolution. Topics discussed in this overview of the Solar Optical Telescope include: why is the Solar Optical Telescope needed; current picture of the Sun's atmosphere and convection zone; scientific problems for the Solar Optical Telescope; a description of the telescope; the facility - science management, contamination control, and accessibility to the instruments; the scientific instruments - a coordinated instrument package for unlocking the Sun's secrets; parameters of the coordinated instrument package; science operations from the Space Shuttle; and the dynamic solar atmosphere.

Source record↗
NASA NTRS2006

Recent Results from the Swift Burst Alert Telescope

The Burst Alert Telescope (BAT) on the Swift Gamma-Ray Burst MIDEX mission has detected more than 125 gamma-ray bursts (GRBs), nearly all of which have been followed up by the narrow-field instruments on Swift through automatic repointing, and by ground and other satellite telescopes after rapid notification. Within seconds of a trigger the BAT produces and relays to the ground a position good to three arc minutes and a four channel light curve. An overview of the properties of BAT bursts and BAT'S performance as a burst monitor will be presented in this talk. BAT is a coded aperture imaging system with a wide (approx.2 sr) field of view consisting of a large coded mask located 1 m above a 5200 sq cm array of 32.768 CdZnTe detectors. All electronics and other hardware systems on the BAT have been operating well since commissioning and there is no sign of any degradation on orbit. The flight and ground software have proven similarly robust and allow the real time localization of all bursts and the rapid derivation of burst light curves, spectra and spectral fits on the ground.

Krimm, Hans↗
NASA NTRSDate not supplied

Orion @ Ames

NASA Ames is a key contributor in Orion heatshield development, aerothermodynamics and aerodynamic and launch abort system modeling of the Artemis generation spacecrafts. This talk will provide an overview and highlights of various present and past activities that ARC staff has been contributing to the program.

heatshield↗
NASA NTRS1992

Sonic boom prediction and minimization using computational fluid dynamics

This paper describes the NASA ARC program in sonic boom prediction methodologies. This activity supports NASA's High Speed Research Program (HSRP). An overview of the program, recent results, conclusions, and current effort will be given. This effort complements research in sonic boom acceptability and validation being conducted at LaRC and ARC. The goals of the sonic boom element are as follows: to establish a predictive capability for sonic booms generated by High-Speed Civil Transport (HSCT) concepts; to establish guidelines of acceptability for supersonic overland flight; and to validate these findings with wind tunnel and flight tests. The cumulative result of these efforts will be an assessment of economic viability for supersonic transportation. This determination will ultimately be made by the aerospace industry.

Edwards, Thomas A.↗
NASA NTRS1992

Advanced ceramic matrix composites for TPS

Recent advances in ceramic matrix composite (CMC) technology provide considerable opportunity for application to future aircraft thermal protection system (TPS), providing materials with higher temperature capability, lower weight, and higher strength and stiffness than traditional materials. The Thermal Protection Material Branch at NASA Ames Research Center has been making significant progress in the development, characterization, and entry simulation (arc-jet) testing of new CMC's. This protection gives a general overview of the Ames Thermal Protection Materials Branch research activities, followed by more detailed descriptions of recent advances in very-high temperature Zr and Hf based ceramics, high temperature, high strength SiC matrix composites, and some activities in polymer precursors and ceramic coating processing. The presentation closes with a brief comparison of maximum heat flux capabilities of advanced TPS materials.

Rasky, Daniel J.↗
NASA NTRS1984

The Western Aeronautical Test Range of NASA Ames Research Center

An overview of the Western Aeronautical Test Range (WATR) of NASA Ames Research Center (ARC) is presented in this paper. The three WATR facilities are discussed, and three WATR elements - mission control centerns, communications systems, real-time processing and display systems, and tracking systems -are reviewed. The relationships within the NASA WATR, with respect to the NASA aeronautics program, are also discussed.

Moore, A. L.↗
NASA NTRS1985

The Western Aeronautical Test Range of NASA Ames Research Center

An overview of the Western Aeronautical Test Range (WATR) of NASA Ames Research Center (ARC) is presented in this paper. The three WATR facilities are discussed, and three WATR elements - mission control centers, communications systems, real-time processing and display systems, and tracking systems - are reviewed. The relationships within the NASA WATR, with respect to the NASA aeronautics program, are also discussed.

Moore, A. L.↗