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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 325 records · Page 18
All sourcesNASA NTRSDOE OSTI
NASA NTRS2019

The Role of Advanced Materials and Manufacturing in Future NASA Exploration Missions

Future NASA missions to the Moon and Mars will require significant advances in materials and manufacturing technologies. These missions will likely be constrained in mass and volume. Lightweight, high strength materials will be required to reduce the mass of launch vehicles and spacecraft in order to maximize the amount of supplies and equipment that can be transported to the surface of the planet. Additive manufacturing and advanced in-space assembly methods will be needed to fabricate spare parts and build habitats for the astronauts. Methods to convert resources on the planet and recycle waste into materials, parts, and fuel will also be required. This presentation will discuss some of these needs, potential solutions currently being explored, and research opportunities for students, faculty, and researchers from industry and government to help address these needs.

chemistry↗
NASA NTRS2020

TPSAS-NF1676L-35628-DND

CHARISMA responds to the Committee on Astrobiology and Planetary Science (CAPS)'s recommendation to study a large/medium-class dedicated space telescope for planetary science. We are nearing the end of the Hubble Space Telescope lifetime, at which point the continuity of solar system UV measurements will be lost. Scientific objectives critically dependent on UV capabilities include studies of exospheric and auroral emissions in planetary atmospheres and plumes. CHARISMA will also revolutionize our understanding of time-dependent phenomena in our solar system currently not supported by programs intended to observe and visit new targets. The time-domain phenomena to be explored by CHARISMA include interaction of planetary magnetospheres with the solar wind, Venus and giant planet atmospheric dynamics, icy satellite geologic activity and surface evolution, cometary evolution, and evolving ring phenomena. CHARISMA also enables a comprehensive survey of the spectral characterization of minor bodies across the solar system, which requires a large time allocation not supported by existing facilities. CHARISMA will examine the benefits of advanced in-Space Assembly (iSA) technologies that enable a 10-m class aperture at New-Frontiers cost. CHARISMA will have the greatest impacts on science objectives particularly sensitive to dynamically evolving phenomena.

C L Young↗
NASA NTRS1993

Automated assembly of large space structures using an expert system executive

NASA LaRC has developed a unique testbed for investigating the practical problems associated with the assembly of large space structures using robotic manipulators. The testbed is an interdisciplinary effort which considers the full spectrum of assembly problems from the design of mechanisms to the development of software. This paper will describe the automated structures assembly testbed and its operation, detail the expert system executive and its development, and discuss the planned system evolution. Emphasis will be placed on the expert system development of the program executive. The executive program must be capable of directing and reliably performing complex assembly tasks with the flexibility to recover from realistic system errors. By employing an expert system, information pertaining to the operation of the system was encapsulated concisely within a knowledge base. This lead to a substantial reduction in code, increased flexibility, eased software upgrades, and realized a savings in software maintenance costs.

Allen, Cheryl L.↗
NASA NTRS1990

Design of a prototype secondary mirror assembly for the Space Infrared Telescope Facility

The design of a liquid helium temperature prototype secondary mirror assembly (PSMA) under development for the NASA Space Infrared Telescope Facility (SIRTF) program is described. The SIRTF assembly must operate below 4 K and provide the functions of highly precise two-axis periodic tilting ('chopping') in addition to the conventional functions of focus and collimation adjustment. The PSMA design employs a fused quartz mirror kinematically attached at its center to an aluminum cruciform. The mirror/cruciform assembly is driven in tilt about its combined center of mass using an aluminum flexure pivot of unique design and a four-actuator control system with feedback provided by pairs of differential position sensors. The voice coil actuators are mounted on a second flexure-pivoted mass to enhance servosystem stability and isolate the telescope from vibration-induced disturbances. The mirror/cruciform and reaction mass are attached to opposite sides of an aluminum mounting plate whose position relative to the outer housing is controlled by a six-degree-of-freedom focus and centering mechanism using pivoted actuation levers driven by lead screw/harmonic drive/stepper motor assemblies.

Stier, Mark T.↗
NASA NTRS1979

EVA Assembly of Large Space Structure Neutral Buoyancy, Zero-Gravity Simulation: NASA-LaRC Nestable Columns and Joints

The film depicts an extravehicular activity (EVA) that involved the assembly of six "space-weight" columns into a regular tetrahedral cell by a team of two "space"-suited test subjects. This cell represents the fundamental "element" of a tetrahedral truss structure. The tests were conducted under simulated zero-gravity conditions, achieved by neutral buoyancy in water. The cell was assembled on an "outrigger" assembly aid off the side of a mockup of the Shuttle Orbiter cargo bay. Both manual and simulated remote manipulator system (RMS) modes were evaluated. The simulated RMS was used only to transfer stowed hardware from the cargo bay to the work sites. Articulation limits of the pressure suit and zero gravity could be accommodated by work stations with foot restraints. The results of this study have confirmed that astronaut EVA assembly of large, erectable space structur is well within man's capabilities.

TESTS↗
NASA NTRS2013

ISS-based Development of Elements and Operations for Robotic Assembly of A Space Solar Power Collector

We present a concept for an ISS-based optical system assembly demonstration designed to advance technologies related to future large in-space optical facilities deployment, including space solar power collectors and large-aperture astronomy telescopes. The large solar power collector problem is not unlike the large astronomical telescope problem, but at least conceptually it should be easier in principle, given the tolerances involved. We strive in this application to leverage heavily the work done on the NASA Optical Testbed Integration on ISS Experiment (OpTIIX) effort to erect a 1.5 m imaging telescope on the International Space Station (ISS). Specifically, we examine a robotic assembly sequence for constructing a large (meter diameter) slightly aspheric or spherical primary reflector, comprised of hexagonal mirror segments affixed to a lightweight rigidizing backplane structure. This approach, together with a structured robot assembler, will be shown to be scalable to the area and areal densities required for large-scale solar concentrator arrays.

astronomy↗
NASA NTRS1993

Aeroelastic dynamics of mistuned blade assemblies with closely spaced blade modes

The aeroelastic characteristics of tuned and randomly mistuned blade assemblies which possess two blade-alone natural modes with close frequencies are studied. Modal interactions among the two blade modes are shown to be come extremely significant for small frequency separation. The two distinct loci of the aeroelastic eigenvalues, which characterize an assembly with well separated modes, fully merge into a single root locus as the blade-mode frequency separation vanishes. Also, while in the case of well separated blade modes the introduction of random mistuning into one blade mode affects only the assembly modes which are predominantly of that blade-mode type, mistuning results in the localization of all the assembly modes when the blade-alone natural frequencies are close. Results indicate that in the case of closely-spaced blade modes a single-degree of freedom blade model yields qualitatively erroneous results and that an N-blade assembly with two close blade modes behaves like an equivalent 2Nb-blade assembly with a single blade mode.

Pierre, Christophe↗
NASA NTRS1982

Large area space solar cell assemblies

Results of the development of a 34.3 sq cm space solar cell and integral glass cover are presented. Average AM(0) cell efficiency is 14 percent. The cell design includes a high performance back surface reflector yielding a thermal alpha of approximately 0.66. A novel process is described which integrates cell fabrication and encapsulation thereby achieving a reduction of encapsulation cost. Test results indicate the potential of this new technology.

Nowlan, M. J.↗
NASA NTRSDate not supplied

Spectral characterization of the Roman Space Telescope Grism and Prism assemblies

The Roman Space Telescope (RST) Wide Field Instrument (WFI) recently completed its thermal vacuum (TVAC) campaign in Boulder, CO. This campaign, which concludes multiple years of preparation, represented the last opportunity for characterization and verification of the Grism and Prism spectral properties before launch; currently scheduled for late-2026. To this end, a highly-automated series of measurements were performed to acquire images of calibration spectra at many field points. Features that were measured during these efforts include dispersion scale, blue/red bandpass edges, diffraction order radiometry, and ghost images. A summary of the techniques and results for several of these efforts is provided here.

Astronomy↗
NASA NTRS2004

Bounding the risk of crew loss following orbital debris penetration of the International Space Station at assembly stages 1J and 1E

Orbital debris impacts on the International Space Station occur frequently. To date, none of the impacting particles has been large enough to penetrate manned pressurized volumes. We used the Manned Spacecraft Crew Survivability code to evaluate the risk to crew of penetrations of pressurized modules at two assembly stages: after Flight 1J, when the pressurized elements of Kibo, the Japanese Experiment Module, are present, and after Flight 1E, when the European Columbus Module is present. Our code is a Monte-Carlo simulation of impacts on the Station that considers several potential event types that could lead to crew loss. Among the statistics tabulated by the program is the probability of death of one or more crew members in the event of a penetration, expressed as the risk factor, R. This risk factor is dependent on details of crew operations during both ordinary circumstances and decompression emergencies, as well as on details of internal module configurations. We conducted trade studies considering these procedure and configuration details to determine the bounds on R at the 1J and 1E stages in the assembly sequence. Here we compare the R-factor bounds, and procedures could that reduce R at these stages. Published by Elsevier Ltd on behalf of COSPAR.

Models, Theoretical↗
NASA NTRSDate not supplied

On-orbit/On-surface Servicing, Assembly, and Manufacturing (OSAM) Architecture Simulation System (OASiS)

On-orbit/on-surface servicing, assembly, and manufacturing (OSAM) –recently renamed“in-space servicing, assembly, and manufacturing”(ISAM) –will aid in the development of vital research-enabling structuresin space, such as the In-space Assembled Telescope, the Lunar Gateway, and the Lunar Safe Haven. As these structures become larger and more complex, developers will need new methods for verifying and validating their OSAM mission architectures at full-scale prior to launch, without paying for extensive facility upgrades or additional hardware prototypes. Under the OSAM Architecture Simulation System (OASiS) project, modular OSAM modeling and simulation capabilities were developed to help rapidly prototype and evaluate OSAM technologies and operational concepts.Theywerethenusedto demonstrate and evaluate data from the simulation of a simpleOSAM operation against ananaloghardware setup. Using collected test data, the teamevaluatedthe accuracy of the simulation environment against the behavior of real hardwareandgainedinsight on how to further improve OSAM modeling and simulation. With thesenewcapabilities and many more to come, developers will be able to test complex OSAM operations on multiple scales, iterate on technology designs faster, achieve higher operational accuracy, and ultimately reduce mission development costs. A comprehensive, high-fidelity simulation environment will ensure the successful servicing, assembly, and manufacturing of structures that help us study and explore our universe.

isam↗
NASA NTRS2002

Bounding the Risk of Crew Loss Following Orbital Debris Penetration of the International Space Station at Assembly Stages 1J and 1E

Orbital debris impacts on the International Space Station occur frequently. To date, none of the impacting particles has been sufficiently large to penetrate manned pressurized volumes. We used the Manned Spacecraft Crew Survivability code to evaluate the risk to crew of penetrations of pressurized modules at two assembly stages: after Flight lJ, when the pressurized elements of Kibo, the Japanese Experiment Module, are present, and after Flight lE, when the European Columbus Module is present. Our code is a Monte Carlo simulation of impacts on the Station that considers several potential event types that could lead to crew loss. Among the statistics tabulated by the program is the probability of death of one or more crew members, expressed as the risk factor, R. This risk factor is dependent on details of crew operations during both ordinary circumstances and decompression emergencies, as well as on details of internal module configurations. We conducted trade studies considering these procedure and configuration details to determine the bounds on R at the 1J and 1E stages in the assembly sequence. Here we compare the R-factor bounds, and procedures and configurations that reduce R at these stages.

Evans, S.↗
NASA NTRS2011

The Era of International Space Station Research: Discoveries and Potential of an Unprecedented Laboratory in Space

The assembly of the International Space Station was completed in early 2011. Its largest research instrument, the Alpha Magnetic Spectrometer is planned for launch in late April. Unlike any previous laboratory in space, the ISS offers a long term platform where scientists can operate experiments rapidly after developing a new research question, and extend their experiments based on early results. This presentation will explain why having a laboratory in orbit is important for a wide variety of experiments that cannot be done on Earth. Some of the most important results from early experiments are already having impacts in areas such as health care, telemedicine, and disaster response. The coming decade of full utilization offers the promise of new understanding of the nature of physical and biological processes and even of matter itself.

Robinson, Julie A.↗
NASA NTRS1990

Automated assembly of large space structures

A research program to evaluate telerobotic methods for inspace assembly of large truss structures has been initiated at the NASA Langley Research Center. A commercial robot is mounted on a carriage positioning system and a tetrahedral truss, which is composed of 102 members each 2 m long, is assembled on a rotating motion-base. The facility system is described including details of characterization tests on the truss structure. The current status of the assembly tests is discussed and observations from these tests indicate that no problems have been encountered that would prohibit automated telerobotic assembly from being a viable inspace construction method.

Rhodes, Marvin D.↗
NASA NTRS1989

Heavy lift vehicles for transportation to a low earth orbit Space Station for assembly of a Human to Mars Mission

Heavy lift vehicle configurations are proposed which will meet the requirements for transporting the elements of a Human to Mars Mission to a low earth orbit Space Station for assembly. Both near term derivative type vehiles as well as advanced technology vehicles are considered. The capability of these vehicles to accommodate the precursor missions are also examined. The implications on launch vehicle payload accommodation design and orbital operations are discussed.

Swalley, Frank E.↗
NASA NTRS2013

Cryogenic Optical Performance of a Light-weight Mirror Assembly for Future Space Astronomical Telescopes: Optical Test Results and Thermal Optical Model

A 40 cm diameter mirror assembly was interferometrically tested at room temperature down to 250 degrees Kelvin for thermal deformation. The 2.5 m radius of curvature spherical mirror assembly was constructed by low temperature fusing three abrasive waterjet core sections between two face sheets. The 93% lightweighted Corning ULE mirror assembly represents the current state of the art for future UV, optical, near IR space telescopes. During the multiple thermal test cycles, test results of interferometric test, thermal IR images of the front face were recorded in order to validate thermal optical model.

Eng, Ron↗
NASA NTRS1991

Automated assembly of large space structures

The topics are presented in viewgraph form and include: the Telerobotic Assembly Facility; joint components; the robot end effector; assembly projected time; typical truss assembly breakdown; the Automated Structures Assembly Facility's current control hierarchy; an assembly problem summary; observations and results; sensor monitoring and error recovery; recommendations and conclusions; and current plans and development.

Marvin D Rhodes↗