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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 NTRS2005

Design and Performance of a Triple Source Air Mass Zero Solar Simulator

Simulating the sun in a laboratory for the purpose of measuring solar cells has long been a challenge for engineers and scientists. Multi-junction cells demand higher fidelity of a solar simulator than do single junction cells, due to a need for close spectral matching as well as AM0 intensity. A GaInP/GaAs/Ge solar cell for example, requires spectral matching in three distinct spectral bands (figure 1). A commercial single source high-pressure xenon arc solar simulator such as the Spectrolab X-25 at NASA Glenn Research Center, can match the top two junctions of a GaInP/GaAs/Ge cell to within 1.3% mismatch, with the GaAs cell receiving slightly more current than required. The Ge bottom cell however, is mismatched +8.8%. Multi source simulators are designed to match the current for all junctions but typically have small illuminated areas, less uniformity and less beam collimation compared to an X-25 simulator. It was our intent when designing a multi source simulator to preserve as many aspects of the X-25 while adding multi-source capability.

Jenkins, Phillip↗
NASA NTRSDate not supplied

Gateway bi-propellant refueling development testing and model validation activities

The Gateway is an upcoming long term lunar exploration program to be completed by NASA in partnership with ESA and other US and international partners. The system design of the Gateway contains both a high performance Xenon based Solar Electric Propulsion system, as well as a bi-propellant attitude control system. Both propulsion systems are designed for on-orbit refueling to enable long life performance of the Gateway. The ESPRIT-RM is a module which will expand the pressurized volume of Gateway, while also providing refueling capability for both the Xenon and Bipropellant propulsion systems, therefore extending the Gateway life on orbit. As part of the Gateway bi-propellant refueling system development, a simplified fluidic breadboard system was created to evaluate system performance and response using simulant fluids. The test plan includes verification activities with simulant (water, HFE-7100) to verify joined subsystem behavior in the critical operations, including propellant transfer demonstration between modules, transient tests and venting tests. Integrated testing occurred at TASUK in collaboration with NASA to support joint verification activities to de-risk the major functions of the ESPRIT BTS and the overall CONOPS of the refueling of the Gateway chemical propulsion system. Initially collected test data from the system testing is presented, as well as initial model validation, and correlated to collected high frequency test data and system response is shown. Initially collected data has shown the architected system performance is closing initial design assumptions, but much forward work remains to characterize and develop the system.

Christopher Daniel Radke↗
NASA NTRSDate not supplied

Joint Development Testing of the Integrated Gateway-Esprit Bipropellant Refuelling System

The Gateway is an upcoming long term lunar exploration program to be completed by NASA in partnership with ESA and other US and international partners. The system design of the Gateway contains both a high performance Xenon based Solar Electric Propulsion system, as well as a bi-propellant attitude control system. Both propulsion systems are designed for on-orbit refuelling to enable long life performance of the Gateway. The ESPRIT-RM is a module which will expand the pressurized volume of Gateway, while also providing refuelling capability for both the Xenon and Bipropellant propulsion systems, therefore extending the Gateway life on orbit. As part of the Gateway bi-propellant refuelling system development, a simplified fluidic breadboard system was created to evaluate system performance and response using simulant fluids. The test plan includes verification activities with simulant (water, HFE-7100) to verify joined subsystem behaviour in the critical operations, including propellant transfer demonstration between modules, transient tests and venting tests. Integrated testing will occur at TASUK in collaboration with NASA to support joint verification activities to de-risk the major functions of the ESPRIT Bipropellant Transfer Subsystem (BTS) and the overall CONOPS of the refuelling of the Gateway chemical propulsion system. Initially collected test data is presented and has shown the architected system performance is closing initial design assumptions, but much forward work is identified to continue to characterize and develop the system.

Sebastian Hill↗
NASA NTRS1985

Performance of Hughes GaAs concentrator cells under 1-MeV electron irradiation

Several Hughes gallium arsenide (GaAs) concentrator cells were exposed to 1-MeV electrons at fluences up to 1x10 to the 15th power electrons/sq cm. Performance data were taken after several fluences, at two temperatures, and at concentration levels from 1 to approx. 150x AMO. Data at 1 sun and 25 deg C were taken with an X-25 xenon-lamp solar simulator. Data at concentration were taken using a pulsed solar simulator with the assumption of a linear relationship between short-circuit current and irradiance. The cells are 5 by 5 mm with a 4-mm diameter illuminated area.

Curtis, H. B.↗
NASA NTRS1985

Performance of GaAs and silicon concentrator cells under 1 MeV electron irradiation

Gallium arsenide concentrator cells from three sources and silicon concentrator cells from one source were exposed to 1 MeV electrons at fluences up to 1 x 10 to the 15th electrons per square cm. Performance data were taken after several fluences, at two temperatures (25 and 80 C), and at concentration levels from 1 to about 150X AM0. Data at one sun and 25 C were taken with an X-25 xenon lamp solar simulator. Data at concentrations were taken using a pulsed solar simulator with the assumption of a linear relationship between short-circuit current and irradiance. The cells are 5 mm x 5 mm with a 4 mm diameter illuminated area.

Curtis, H. B.↗
NASA NTRS1987

Lunar Get Away Special (GAS) spacecraft

A new approach to the resumption of Lunar missions is discussed which relies upon Shuttle Get-Away-Special Canisters for launch and solar electric ion propulsion for slow orbit transfer to low Lunar orbit. The technique of orbit transfer is outlined along with a summary of a mission profile for a first mission which could carry a Gamma Ray Spectrometer. System design constraints are discussed followed by a description of the low mass spacecraft concept which has been developed. Particular emphasis is placed upon describing the small solar electric, xenon ion propulsion system.

Nock, K. T.↗
NASA NTRS1987

Performance of GaAs and silicon concentrator cells under 37 MeV proton irradiation

Gallium arsenide concentrator cells from three sources and silicon concentrator cells from one source were exposed to 37 MeV protons at fluences up to 2.8 x 10 to the 12th protons/sq cm. Performance data were taken after several fluences, at two temperatures (25 and 80 C), and at concentration levels from 1 to about 150 x AMO. Data at one sun and 25 C were taken with an X-25 xenon lamp solar simulator. Data at concentration were taken using a pulsed solar simulator with the assumption of a linear relationship between short circuit current and irradiance. The cells are 5 x 5 mm with a 4-mm diameter illuminated area.

Curtis, Henry B.↗
NASA NTRS1987

Performance of GaAs and silicon concentrator cells under 37 MeV proton irradiation

Gallium arsenide concentrator cells from three sources and silicon concentrator cells from one source were exposed to 37-MeV protons at fluences up to 2.8 x 10 to the 12th protons/sq cm. Performance data were taken after several fluences, at two temperatures (25 and 80 C), and at concentration levels from 1 to about 150X AM0. Data at one sun and 25 C were taken with an X-25 xenon-lamp solar simulator. Data at concentration were taken using a pulsed solar simulator with the assumption of a linear relationship between short-circuit current and irradiance. The cells are 5 mm x 5 mm with a 4-mm-diameter illuminated area.

Curtis, Henry B.↗
NASA NTRS1992

Proceedings of Lunar and Planetary Science, Volume 22; Conference, Houston, TX, Mar. 18-22, 1991

Various papers on lunar and planetary science are presented. Individual topics addressed include: analysis of Phobos Mission Gamma ray spectra from Mars, comparison of volcanic and modified landforms from Tharsis Montes on Mars, polygenetic origin of Hrad Vallis region of Mars, new evidence of lacustrine basins on Mars, flood surge through the Lunae Planum Outflow Complex on Mars, interpretation of canyon materials and flood sources on Kasei Valles on Mars, geochemistry of Manson Impact structure rocks, micrometer-sized glass spheres in Apollo 16 soil 61181, isotopic abundances in Pesyanoe of solar-type xenon, mineralogy of 12 large 'chondritic' interplanetary dust particles. Also discussed are: trace elements in chondritic stratospheric particles, evolution of isotopic signatures in lunar regolith nitrogen, pyroclastic deposits on the western limb of the moon, origin of picritic green glass magmas by polybaric fractional fusion, origin of yellow glasses associated with Apollo 15 KREEP basalt fragments, trace elements in 59 mostly highland moon rocks, mineralization on the moon, relation between diogenite cumulates and eucrite magmas.

Ryder, Graham↗
NASA NTRS1994

A Segmented Ion Engine Design for Solar Elctric Propulsion Systems

Solar electric xenon ion propulsion can be used to deliver a substantial quantity of science instruments in rendezvous missions to small bodies such as comets and main belt asteroids with an Atlas IIAS launch vehicle. The performance of the ion propulsion system enables it to deliver typically more than twice the total mass to the destination in less than half the trip time relative to a chemical/ballistic approach using the same launch vehicle.

electron bombardment↗
NASA NTRS2012

Mars Science Laboratory Rover System Thermal Test

On November 26, 2011, NASA launched a large (900 kg) rover as part of the Mars Science Laboratory (MSL) mission to Mars. The MSL rover is scheduled to land on Mars on August 5, 2012. Prior to launch, the Rover was successfully operated in simulated mission extreme environments during a 16-day long Rover System Thermal Test (STT). This paper describes the MSL Rover STT, test planning, test execution, test results, thermal model correlation and flight predictions. The rover was tested in the JPL 25-Foot Diameter Space Simulator Facility at the Jet Propulsion Laboratory (JPL). The Rover operated in simulated Cruise (vacuum) and Mars Surface environments (8 Torr nitrogen gas) with mission extreme hot and cold boundary conditions. A Xenon lamp solar simulator was used to impose simulated solar loads on the rover during a bounding hot case and during a simulated Mars diurnal test case. All thermal hardware was exercised and performed nominally. The Rover Heat Rejection System, a liquid-phase fluid loop used to transport heat in and out of the electronics boxes inside the rover chassis, performed better than predicted. Steady state and transient data were collected to allow correlation of analytical thermal models. These thermal models were subsequently used to predict rover thermal performance for the MSL Gale Crater landing site. Models predict that critical hardware temperatures will be maintained within allowable flight limits over the entire 669 Sol surface mission.

Novak, Keith S.↗
NASA NTRS2012

Mars Science Laboratory Rover System Thermal Test

On November 26, 2011, NASA launched a large (900 kg) rover as part of the Mars Science Laboratory (MSL) mission to Mars. The MSL rover is scheduled to land on Mars on August 5, 2012. Prior to launch, the Rover was successfully operated in simulated mission extreme environments during a 16-day long Rover System Thermal Test (STT). This paper describes the MSL Rover STT, test planning, test execution, test results, thermal model correlation and flight predictions. The rover was tested in the JPL 25-Foot Diameter Space Simulator Facility at the Jet Propulsion Laboratory (JPL). The Rover operated in simulated Cruise (vacuum) and Mars Surface environments (8 Torr nitrogen gas) with mission extreme hot and cold boundary conditions. A Xenon lamp solar simulator was used to impose simulated solar loads on the rover during a bounding hot case and during a simulated Mars diurnal test case. All thermal hardware was exercised and performed nominally. The Rover Heat Rejection System, a liquid-phase fluid loop used to transport heat in and out of the electronics boxes inside the rover chassis, performed better than predicted. Steady state and transient data were collected to allow correlation of analytical thermal models. These thermal models were subsequently used to predict rover thermal performance for the MSL Gale Crater landing site. Models predict that critical hardware temperatures will be maintained within allowable flight limits over the entire 669 Sol surface mission.

Novak, Keith S.↗
NASA NTRS2024

Gateway to the Future: Lessons Learned in Development of the Refueling Systems for NASA's First Lunar Space Station

Developed in collaboration with international and commercial partners, Gateway will be humanity’s first space station around the Moon as a vital component of NASA’s deep space exploration plans to the Moon, Mars and beyond. As part of it’s focus on developing a sustainable, long term lunar capability, both it’s Xenon based Solar Electric Propulsion System, as well as it’s bi-propellant Reaction Control System of the Gateway are designed to be on-orbit refuellable. Through design studies, numerical modeling, hardware development, and early testing, the system architecture has undergone significant changes to meet mission requirements and utilize evolving hardware capabilities between concept formulation and it’s successful completion of it’s Critical Design Review. This paper presents key lessons learned during this process, highlighting specific design elements and test results that contribute to a robust and adaptable refueling system for the Gateway.

Christopher Radke↗
NASA NTRS2024

Gateway to the Future: Lessons Learned in Development of the Refueling Systems for NASA's First Lunar Space Station

Developed in collaboration with international and commercial partners, Gateway will be humanity’s first crewed space station around the Moon as a vital component of NASA’s Artemis Program for exploration to the Moon, Mars and beyond. As part of it’s focus on developing a sustainable, long term lunar capability, both Xenon based Solar Electric Propulsion System, as well as bi-propellant Reaction Control System of Gateway are designed to be on-orbit refuelable. Through design studies, numerical modeling, hardware development, and substantial testing, the system architecture has undergone significant changes to meet mission requirements and utilize evolving hardware capabilities between concept formulation and the successful completion of its Critical Design Review. This paper presents key lessons learned during this process, highlighting specific design elements and test results that contribute to a robust and adaptable refueling system for the Gateway.

Christopher Radke↗
NASA NTRS2008

NASA's Evolutionary Xenon Thruster: The NEXT Ion Propulsion System for Solar System Exploration

This viewgraph presentation reviews NASA s Evolutionary Xenon Thruster (NEXT) Ion Propulsion system. The NEXT project is developing a solar electric ion propulsion system. The NEXT project is advancing the capability of ion propulsion to meet NASA robotic science mission needs. The NEXT system is planned to significantly improve performance over the state of the art electric propulsion systems, such as NASA Solar Electric Propulsion Technology Application Readiness (NSTAR). The status of NEXT development is reviewed, including information on the NEXT Thruster, the power processing unit, the propellant management system (PMS), the digital control interface unit, and the gimbal. Block diagrams NEXT system are presented. Also a review of the lessons learned from the Dawn and NSTAR systems is provided. In summary the NEXT project activities through 2007 have brought next-generation ion propulsion technology to a sufficient maturity level.

Pencil, Eric J.↗
NASA NTRS2024

Xenon Isotopic Analysis of Individual Intermediate Particles From the OSIRIS-REx Sample of Asteroid Bennu

The OSIRIS-REx mission sampled material from the B-type asteroid Bennu and delivered the sample to Earth on 24 September 2023. Here we present initial xenon isotopic analysis of individual intermediate particles of Bennu material collected by the OSIRIS-REx mission. Noble gases are key tracers of Solar System evolution. Xenon is particularly useful among the noble gases because its nine isotopes allow multiple contributing sources to be unambiguously identified. The sun, asteroids (as measured in meteorites), and comets (measured in the coma of comet 67P) have distinct xenon isotopic signatures reflecting different mixtures of nucleosynthetic components. In addition, 129 I, 238 U, and 244 Pu decay with different half-lives, producing characteristic xenon signatures. Exposure of samples containing light rare earth elements and barium to cosmic rays produces xenon from spallation and secondary neutron capture reaction. Noble gas analyses help address several of the driving hypotheses of the mission [9]. Particle-by-particle analysis can elucidate the diversity of material present and reveal distinct noble gas compositions, including the potential to detect presolar or cometary noble gas signatures on a small scale. The isotopic signature provides a fingerprint that can be used to constrain the sources of volatiles in planetary reservoirs and combined with other information (e.g. mineralogy and petrology of the material analyses) contributes to our understanding of the initial constituents, formation, and history of Bennu and its parent asteroid.

S A Crowther↗
NASA NTRS1980

A first roadmap for kryptology

Studies of the complex variations of the isotopic composition of xenon in the solar system have been christened 'xenology'. In the title of the present investigation, the word 'kryptology' is employed to indicate the primary objective of the reported studies. This objective is related to the prediction of the isotopic composition of krypton which comes from a number of specific locations of a supernova in association with the isotopic compositions of xenon from these locations. Krypton is a logical candidate for testing the stellar theory on geochemical grounds, taking into account also the point of view of nucleosynthesis, because the isotopes of xenon and krypton are formed by the same thermonuclear processes in stars. The data and arguments presented in the investigation show that the treatment by Heymann and Dziczkaniec (1979), although not wrong, is too simplistic, because it has ignored the possibility of holdup and arrest in Xe network.

Heymann, D.↗