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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 1,387 records · Page 77
All sourcesNASA NTRSDOE OSTI
NASA NTRS1988

Some instrumentation requirement issues for the Space Station structural characterization experiment

The Space Station will provide unique opportunities to the research and technology community as a national in-space research facility. Opportunities will exist for technology experiments in a variety of disciplines, including dynamics and control of large space structures (LSS). The Space Station Structural Characterization Experiment (SSSCE) is an early space station technology experiment now under development. The objective of the experiment is to instrument and use the Space Station as a generic research test article, in support of research and technology activities in the areas of structural dynamics and control/structure interaction (CSI). Tests will be conducted, potentially, on each assembly flight configuration, as well as on the phase 1 configuration. Structural dynamic response data will be measured and transferred to the ground for analysis. These measurements will support the development and in-space verification of system identification and analytical modeling techniques for future LSS, including the evolutionary Space Station. The paper begins by restating the principal objective of SSSCE, along with the basic approach that will be used. The body of the paper deals with instrumentation requirement issues. The paper closes with several questions concerning modal-testing objectives and limitations, a brief review of a previous on-orbit experiment, the Solar Array Flight Experiment, and concluding remarks.

Pappa, Richard S.↗
NASA NTRSDate not supplied

Recent Langley Aerothermodynamic Laboratory Testing (2019-2022)

In support of flight programs, multiple wind tunnel entries were conducted on reentry vehicle configurations to investigate blunt body aeroheating environments. Blunt body block thermal protection system (TPS) roughness, the Low-Earth Orbit Flight Test of an Inflatable Decelerator aeroshell scalloping, and a woven TPS all were tested to determine the effects of those parameters on increased surface heating to the vehicle. Commercial Crew Program studies also utilized the speed and ease of testing in the LAL to analyze parametric databases of low-earth reentry configurations, like the Boeing CST-100, and vehicles designed to travel to the moon or Mars, such as the SpaceX Starship. LAL wind tunnel investigations also supported several DoD and AFRL flight projects, such as HIFiRE 6 and BOLT. External customers leveraged the LAL testing capability to advance their research programs, including UPSTAR, RocketLab, and Lawrence Livermore National Laboratory. Academia groups benefitted from the inexpensive cost to test in the tunnels for many university collaborations, such as studies conducted in partnership with the University of Maryland on a flat plate, using a pressure rake and investigating fluid structure interactions. Multiple studies in collaboration with Purdue considered boundary layer transition on various cone configurations. Another study was conducted using a cone with shaped roughness elements borrowed from the Arnold Engineering Development Complex. Internal testing included studies using a phosphor thermography system that can measure higher temperatures than the current LAL phosphor capability and a characterization study of the noise in the wind tunnel flow. The breadth of testing across research and commercial paradigms, both internal and external to NASA, different configurations, a variety of test techniques and aerodynamic and aerothermal environments will be discussed in this overview presentation of the recent work conducted in the LAL.

wind tunnel test↗
NASA NTRS1997

Report on Cosmic Dust Capture Research and Development for the Exobiology Program

Collaboration with Ames' personnel was in: 1) grant administration, 2) intellectual science support, 3) collaboration with the University of Paris for the Mir flight experiment, and 4) arranging scanning and X-ray probe analytical support from UCB and SUNYP. LNIMS provided access to: 1) analytical research instruments, 2) chemical analyses support, 3) cleanroom facilities, and 4) design and fabrication expertise of hardware and electronics. They also supported the hypervelocity testing along with test data acquisition and its reduction for the breadboard instrument. A&M Associates provided technical expertise and support on determining the expected charges on orbital particles and a conceptual design for a breadboard particle charge detection sensor. University of California provided analytical support for the recovered Mir flight modules using their unique scanning capability to detect particle tracks in the aerogel. SUNYP, along with help from the University of Chicago, analyzed particle tracks found in the aerogel for biogenic compounds using an x-ray probe instrument. Dr. Schultz provided access to his experiments and the benefits of his considerable hyper-velocity testing expertise at the Ames hypervelocity gun facility, and this proved beneficial to our development testing, significantly reducing the test time and cost for the breadboard instrument development testing. The participants in this activity acknowledge and thank the National Aeronautics and Space Administration and its Ames Research Center for providing the necessary support and resources to conduct this investigation on instrument technology for exobiology application and being able to acquire some interesting results. Primarily, the newly identified technology problems for future research are the important results of this research.

Nishioka, Kenji↗
DOE OSTI2021

PELICAN Design, Test Planning, and Commissioning Results

To support design efforts for the Versatile Test Reactor (VTR) core assemblies, an experimental facility has been designed and constructed at Argonne National Laboratory to match the hydraulic flow conditions within the VTR’s primary heat transport system (PHTS). This facility, the Pressure drop Experimental Loop for Investigations of Core Assemblies in advanced Nuclear reactors, PELICAN, provides the ability to measure pressure drop across a full-scale fuel assembly containing prototypic axial reflectors, fuel, and plena components. The PELICAN facility was designed and built to offer maximum flexibility, allowing testing from short sub-sections all the way to the full-length core fuel assemblies. The report presents the high-level program objectives, a summary of the facility design, instrumentation, and control systems, and the testing procedure. The outcomes from facility characterization efforts and first test matrix results are then presented and then, finally, the conclusion contains a summary of the future work to be performed. This test facility was designed to match the hydraulic conditions of the flowing sodium in the VTR using water as a surrogate fluid. To do so, the water is elevated to a temperature of 110°C where its viscosity matches that of sodium, and with a 50-HP centrifugal pump, is capable of generating full scale flow rates to achieve prototypic Reynolds and Euler number flow conditions. To prevent boiling, the system is maintained at elevated pressure of at least 2.7-3.0 bar (40-44 psig). A set of 15 tests have been used to perform checkout activities in order to commission the device, survey the capabilities of PELICAN, and generate experimental data at isothermal conditions and over a range of flow rates up to 44 kg/s (700 GPM) to produce datasets used in the verification and validation of VTR design and modeling efforts. Initial testing focused on facility characterization, which assessed the operational capabilities of various control systems. The thermal control system was qualified, including the thermal response of the loop to the heat added by self- and auxiliary heaters, the chiller and heat exchanger systems for removing excess heat, and their coupled ability to maintain steady-state isothermal conditions as desired. Additionally, the pressure control system was verified to ensure necessary operating environments that promote pump health and prevent boiling of loop inventory at high temperatures could be met. With these systems in place, the first set of matrix tests have been carried out using orifice plates with inner diameters of 2.25-inches and 2.5-inches. Orifice plate flow behavior is well covered in scientific literature, and the results find good agreement with the measured pressure drop vs flow rate and those of theoretical predictions. This initial testing not only helps to validate the experiment, but it also produces a high quality data set for a geometry that is easily reproducible for simulations. Finally, the report is concluded with a discussion of the work to come and provides a snapshot of the test articles in the experimental pipeline whose designs are being inspired by the current designs from the VTR.

22 GENERAL STUDIES OF NUCLEAR REACTORS↗
NASA NTRS1975

Real-time data acquisition system assists engine test program

The mixed-fuels program examined included two major phases: the development of a reformer that would provide an onboard source of hydrogen, and the testing of induction systems and mixed fuels on a conventional V8 engine to verify the concept and define the system's potential. The discussion is limited to the engine testing phase. The testing program is reviewed and the effectiveness of an IDAC data acquisition system in supporting the engine testing program is demonstrated. The data system's application is illustrated by examples.

Griffin, D. C., Jr.↗
NASA NTRS1976

MIUS integration and subsystems test program

The MIUS Integration and Subsystems Test (MIST) facility at the Lyndon B. Johnson Space Center was completed and ready in May 1974 for conducting specific tests in direct support of the Modular Integrated Utility System (MIUS). A series of subsystems and integrated tests was conducted since that time, culminating in a series of 24-hour dynamic tests to further demonstrate the capabilities of the MIUS Program concepts to meet typical utility load profiles for a residential area. Results of the MIST Program are presented which achieved demonstrated plant thermal efficiencies ranging from 57 to 65 percent.

Beckham, W. S., Jr.↗
NASA NTRS2009

Testing Large Structures in the Field

Field testing large structures creates unique challenges such as limited choices for boundary conditions and the fact that natural excitation sources cannot be removed. Several critical developments in field testing of large structures are reviewed, including: step relaxation testing which has been developed into a useful technique to apply large forces to operational systems by careful windowing; the capability of large structures testing with free support conditions which has been expanded by implementing modeling of the support structure; natural excitation which has been developed as a viable approach to field testing; and the hybrid approach which has been developed to allow forces to be estimated in operating structures. These developments have increased the ability to extract information from large structures and are highlighted in this presentation.

James, George↗
NASA NTRS2013

Lessons Learned During Instrument Testing for the Thermal Infrared Sensor (TIRS)

The Themal InfraRed Sensor (TIRS) instrument, set to launch on the Landsat Data Continuity Mission in 2013, features a passively cooled telescope and IR detectors which are actively cooled by a two stage cryocooler. In order to proceed to the instrument level test campaign, at least one full functional test was required, necessitating a thermal vacuum test to sufficiently cool the detectors and demonstrate performance. This was fairly unique in that this test occurred before the Pre Environmental Review, but yielded significant knowledge gains before the planned instrument level test. During the pre-PER test, numerous discrepancies were found between the model and the actual hardware, which were revealed by poor correlation between model predictions and test data. With the inclusion of pseudo-balance points, the test also provided an opportunity to perform a pre-correlation to test data prior to the instrument level test campaign. Various lessons were learned during this test related to modeling and design of both the flight hardware and the Ground Support Equipment and test setup. The lessons learned in the pre-PER test resulted in a better test setup for the nstrument level test and the completion of the final instrument model correlation in a shorter period of time. Upon completion of the correlation, the flight predictions were generated including the full suite of off-nominal cases, including some new cases defined by the spacecraft. For some of these ·new cases, some components now revealed limit exceedances, in particular for a portion of the hardware that could not be tested due to its size and chamber limitations.. Further lessons were learned during the completion of flight predictions. With a correlated detalled instrument model, significant efforts were made to generate a reduced model suitable for observatory level analyses. This proved a major effort both to generate an appropriate network as well as to convert to the final model to the required format and yielded additional lessons learned. In spite of all the challenges encountered by TIRS, the instrument was successfully delivered to the spacecraft and will soon be tested at observatory level in preparation for a successful mission launch.

Peabody, Hume L.↗
DOE OSTI2025

STEM Professional Development Program for Nuclear Security Science and Technology Consortium

This oral presentation captures the technical and developmental aspect of the program in support of UNLV. The goal of this project is to develop a steady pipeline of STEM educated professionals in area of national and international nuclear security. The goal is to train university students at NNSS laboratories in studies motivated by global nuclear security topics ranging from nuclear emergency response and management to physics experiments for stockpile stewardship program.

96 KNOWLEDGE MANAGEMENT AND PRESERVATION↗
NASA NTRS1994

Satellite Test of the Equivalence Principle (STEP)

This grant provided support for the STEP (Satellite Test of the Equivalence Principle) program between October 1991 and September 1993. STEP, previously supported by NASA under Grant NAG8-837 'A Satellite Test of the Equivalence Principle,' was selected by the European Space Agency for a Phase A study as a candidate for ESA's next medium size mission (M2). STEP was conceived as a joint NASA/ESA mission with equal participation by both agencies. ESA's contribution to the program would be the spacecraft; NASA would provide the launcher and half of the instrument, while the other half of the instrument would be provided by various European agencies. STEP was in competition with three other programs, INTEGRAL, PRISMA, and MARSNET. The final selection of a single mission for M2 took place in April 1993. STEP was not selected for M2 but made a very close second. The program is continuing in modified form.

Worden, Paul↗