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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 55 records · Page 3
All sourcesNASA NTRSDOE OSTI
NASA NTRS2018

Technology Demonstration Mission (TDM) evolvable Cryogenics (eCryo) Project Structural Heat Intercept, Insulation and Vibration Evaluation Rig (SHIIVER) Diode Rake Assembly and Installation

NASA designed, assembled and installed a temperature diode rake into the SHIIVER test article for use of measuring liquid and gaseous hydrogen temperatures. Several special steps were taken to ensure that fluid temperatures were measured as opposed to structural temperatures. This document outlines design practices and methodologies that have become standard practice at Glenn Research Center to ensure the measurement of fluid temperatures for cryogenic systems research.

Cryogenic Fluid Management↗
NASA NTRS1994

Structural damping studies at cryogenic temperatures

Results of an engineering study to measure changes in structural damping properties of two cryogenic wind tunnel model systems and two metallic test specimens at cryogenic temperatures are presented. Data are presented which indicate overall, a trend toward reduced structural damping at cryogenic temperatures (-250 degrees F) when compared with room temperature damping properties. The study was focused on structures and materials used for model systems tested in the National Transonic Facility (NTF). The study suggests that the significant reductions in damping at extremely cold temperatures are most likely associated with changes in mechanical joint compliance damping rather than changes in material (solid) damping.

Young, Clarence P., Jr.↗
NASA NTRS2020

Technology Demonstration Mission (TDM) Evolvable Cryogenics (eCryo) Project: Structural Heat Intercept, Insulation, and Vibration Evaluation Rig (SHIIVER) - Test Plan

The initial test of the SHIIVER system includes multilayer insulation and vapor cooled structure. Testing will occur in the In-Space Propulsion Facility (thermal/vacuum) and RATF (acoustic) facilities at Plum Brook Station in Sandusky Ohio. The testing will demonstrate the performance benefits of multilayer insulation and vapor based heat intercept on a “large scale” test article in a manner befitting large upper stages.

Large Scale Hydrogen Testing, Cryogenics, Multilay↗
NASA NTRS1982

Development of Rene 41 honeycomb structure as an integral cryogenic tankage/fuselage concept for future space transportation systems

The status of the structural development of an integral cryogenic-tankage/hot-fuselage concept for future space transportation systems is reviewed. The concept comprises a honeycomb sandwich structure that serves the combined functions of containing the cryogenic fuel, supporting the vehicle loads, and protecting the spacecraft from entry heating. The inner face sheet is exposed to cryogenic temperature of -423 F during boost; the outer face sheet, which is slotted to reduce thermal stress, is exposed to a maximum temperature of 1400 F during a high-altitude gliding entry. Attention is given to the development of a fabrication process for a Rene 41 honeycomb sandwich panel with a core density of less than 1 percent that is consistent with desirable heat treatment processes for high strength.

Shideler, J. L.↗
NASA NTRS1982

Development of Rene' 41 honeycomb structure as an integral cryogenic tankage/fuselage concept for future space transportation systems

The status of the structural development of an integral cryogenic-tankage/hot-fuselage concept for future space transportation systems (STS) is discussed. The concept consists of a honeycomb sandwich structure which serves the combined functions of containment of cryogenic fuel, support of vehicle loads, and thermal protection from an entry heating environment. The inner face sheet is exposed to a cryogenic (LH2) temperature of -423 F during boost; and the outer face sheet, which is slotted to reduce thermal stress, is exposed to a maximum temperature of 1400 F during a high altitude, gliding entry. A fabrication process for a Rene' 41 honeycomb sandwich panel with a core density less than 1 percent was developed which is consistent with desirable heat treatment processes for high strength.

Shideler, J. J.↗
NASA NTRS1992

Screening programme to select a resin for Gravity Probe-B composites

The Gravity Probe-B (GP-B) program undertook a screening program to select a possible replacement resin for the E-787 resin currently used in composite neck tubes and support struts. The goal was to find a resin with good cryogenic and structural properties, low-helium permeation and an easily repeatable fabrication process. Cycom 92, SCI REZ 081 and RS-3 were selected for comparison with E-787. Identical composite tubes made from each resin and gamma-alumina fiber (85 percent Al2O3, 15 percent SiO2) were evaluated for cryogenic and structural performance and for processability. Cryogenic performance was evaluated by measuring low-temperature permeation and leaks to determine cryogenic strain behavior. Structural performance was evaluated by comparing the resin-dominated shear strength of the composites. Processability was evaluated from fabrication comments and GP-B's own experience. SCI REZ 081 was selected as the best overall resin with superior strength and cryogenic performance and consistent processability.

Will, E. T.↗
NASA NTRS2004

Tensile Properties of Polymeric Matrix Composites Subjected to Cryogenic Environments

Polymer matrix composites (PMC s) have seen limited use as structural materials in cryogenic environments. One reason for the limited use of PMC s in cryogenic structures is a design philosophy that typically requires a large, validated database of material properties in order to ensure a reliable and defect free structure. It is the intent of this paper to provide an initial set of mechanical properties developed from experimental data of an advanced PMC (IM7/PETI-5) exposed to cryogenic temperatures and mechanical loading. The application of this data is to assist in the materials down-select and design of cryogenic fuel tanks for future reusable space vehicles. The details of the material system, test program, and experimental methods will be outlined. Tension modulus and strength were measured at room temperature, -196 C, and -269 C on five different laminates. These properties were also tested after aging at -186 C with and without loading applied. Microcracking was observed in one laminate.

Whitley, Karen S.↗
NASA NTRS2000

Integrated Design and Analysis Overview

The objectives of the project this viewgraph presentation summarizes (integrated design and analysis) include the following: (1) Develop methodology for assessing the effects of manufacturing defects; (2) Develop damage tolerance criteria and damage tolerance database for reusable launch vehicle cryogenic tank structures, including impact, pressure leakage, cryogenic permeation, and validated damage prediction tools; and (3) Develop repair technology.

Gates, Tom S.↗
NASA NTRS2013

Method and apparatus for conducting structural health monitoring in a cryogenic, high vibration environment

Sensors affixed to various such structures, where the sensors can withstand, remain affixed, and operate while undergoing both cryogenic temperatures and high vibrations. In particular, piezoelectric single crystal transducers are utilized, and these sensors are coupled to the structure via a low temperature, heat cured epoxy. This allows the transducers to monitor the structure while the engine is operating, even despite the harsh operating conditions. Aspects of the invention thus allow for real time monitoring and analysis of structures that operate in conditions that previously did not permit such analysis. A further aspect of the invention relates to use of piezoelectric single crystal transducers. In particular, use of such transducers allows the same elements to be used as both sensors and actuators.

Qing, Xinlin↗