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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 127 records · Page 7
All sourcesNASA NTRSDOE OSTI
NASA NTRS1985

Automatic Fastening Large Structures: a New Approach

The external tank (ET) intertank structure for the space shuttle, a 27.5 ft diameter 22.5 ft long externally stiffened mechanically fastened skin-stringer-frame structure, was a labor intensitive manual structure built on a modified Saturn tooling position. A new approach was developed based on half-section subassemblies. The heart of this manufacturing approach will be 33 ft high vertical automatic riveting system with a 28 ft rotary positioner coming on-line in mid 1985. The Automatic Riveting System incorporates many of the latest automatic riveting technologies. Key features include: vertical columns with two sets of independently operating CNC drill-riveting heads; capability of drill, insert and upset any one piece fastener up to 3/8 inch diameter including slugs without displacing the workpiece offset bucking ram with programmable rotation and deep retraction; vision system for automatic parts program re-synchronization and part edge margin control; and an automatic rivet selection/handling system.

Lumley, D. F.↗
NASA NTRS1991

Quick-Connect Truss Fastener

Quick-connect fastener actuated by simple motion of hexagonal wrench. Enables assembly of truss by heavily gloved technician or by robot. Originally designed for use by Astronaut or robot assembling a truss in outer space, fastener also adapts to various connection applications requiring quick assembly or disassembly.

Sheridan, Philip L.↗
NASA NTRS1992

Fastener For Hot, Oxidizing Environments

Threaded halves of metallic collar fit around tapered shank of body of fastener. Retaining ring holds collar on body. Ceramic coat gives fastener its resistance to oxidation. Assembled and disassembled quickly from outside.

Dunn, Thomas J.↗
NASA NTRS1992

"Easy-on, Easy-off" Blanket Fastener

Fasteners hold flexible blanket on set of posts on supporting structure. Disk of silicone rubber cast on disk of Mylar, fastened to blanket and press-fit over post to nest securely in groove. No tools needed for installation or removal.

Kolecki, Ronald E.↗
NASA NTRS1992

Hidden Fastening-And-Unfastening Mechanism

Proposed mechanism placed behind panel fastens panel to, or unfastens it from, underlying structure. Electric motor and gearbox drives bolt to engage or disengage captive floating nut. Used where head at outer end of bolt or other fastener covered with protective outer layer on panel and inner end of bolt inaccessible.

Macconochie, Ian O.↗
NASA NTRS1992

Carbon/Carbon Fasteners For Use At High Temperatures

Fasteners made of advanced carbon/carbon material perform well at ambient and high temperatures. Exhibit shear strengths of more than 10 kpsi at room temperature and 13 kpsi at temperature of 2,700 degrees F. However, fasteners exhibited poor tensile strength at room temperature. Best suited to applications in which exposed to shear loads with minimal tension loads. Parts reused after thermal cycling.

Bohlmann, Frank J.↗
NASA NTRS1992

Effects of long-term exposure on LDEF fastener assemblies

This presentation summarizes the Systems Special Investigations Group (SIG) findings from testing and analysis of fastener assemblies used on the Long Duration Exposure Facility (LDEF) structure, the tray mounting clamps, and by the various experimenters. The LDEF deintegration team and several experimenters noted severe fastener damage and hardware removal difficulties during post-flight activities. The System SIG has investigated all reported instances, and in all cases examined to date, the difficulties were attributed to galling during installation or post-flight removal. To date, no evidence of coldwelding was found. Correct selection of materials and lubricants as well as proper mechanical procedures is essential to ensure successful on-orbit or post-flight installation and removal of hardware.

Spear, Steve↗
NASA NTRS1997

Fastener Design Course

Richard T. Barrett, Senior Aerospace Engineer of NASA Lewis Research Center presents a comprehensive course on fastener design. A recognized expert in the field of fastener technology Mr. Barrett combines lecture, charts, illustrations with real-world experiences. Topics covered include: materials, plantings and coatings, locking methods threads, joint stiffness, rivets, inserts, nut plates, thread lubricants, design criteria, etc. A workbook accompanies the DVD.

Barrett, Richard T.↗
NASA NTRS2006

Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined With Fasteners (MSFC Center Director's Discretionary Fund Final Report, Proj. 03-13}

Aerospace structures utilize innovative, lightweight composite materials for exploration activities. These structural components, due to various reasons including size limitations, manufacturing facilities, contractual obligations, or particular design requirements, will have to be joined. The common methodologies for joining composite components are the adhesively bonded and mechanically fastened joints and, in certain instances, both methods are simultaneously incorporated into the design. Guidelines and recommendations exist for engineers to develop design criteria and analyze and test composites. However, there are no guidelines or recommendations based on analysis or test data to specify a torque or torque range to apply to metallic mechanical fasteners used to join composite components. Utilizing the torque tension machine at NASA s Marshall Space Flight Center, an initial series of tests were conducted to determine the maximum torque that could be applied to a composite specimen. Acoustic emissions were used to nondestructively assess the specimens during the tests and thermographic imaging after the tests.

Thomas, F. P.↗
NASA NTRS2000

Fastener

A fastener body comprises a head and a shank fabricated from a composite material. The head has at least one side which extends beyond the side of the shank and has two other sides coplanar with the shank. A fastener for engaging a liner has perpendicular lengthwise and widthwise reference axes and a head and a shank, with the shank extending in a first lengthwise direction away from the head, the head further having at least one extension that extends in the widthwise direction beyond the shank for engaging the liner, wherein substantially all lengthwise directed load components transmitted from the liner to the head are transmitted through the extension.

Miller, Robert J.↗
NASA NTRS2011

Performance Characterization of Loctite (Registered Trademark) 242 and 271 Liquid Locking Compounds (LLCs) as a Secondary Locking Feature for International Space Station (ISS) Fasteners

Several International Space Station (ISS) hardware components use Loctite (and other polymer based liquid locking compounds (LLCs)) as a means of meeting the secondary (redundant) locking feature requirement for fasteners. The primary locking method is the fastener preload, with the application of the Loctite compound which when cured is intended to resist preload reduction. The reliability of these compounds has been questioned due to a number of failures during ground testing. The ISS Program Manager requested the NASA Engineering and Safety Center (NESC) to characterize and quantify sensitivities of Loctite being used as a secondary locking feature. The findings and recommendations provided in this investigation apply to the anaerobic LLCs Loctite 242 and 271. No other anaerobic LLCs were evaluated for this investigation. This document contains the findings and recommendations of the NESC investigation

Dube, Michael J.↗
NASA NTRS1997

Fastener Design Course [Workbook]

Richard T. Barrett, Senior Aerospace Engineer of NASA Lewis Research Center presents a comprehensive course on fastener design. A recognized expert in the field of fastener technology Mr. Barrett combines lecture, charts, illustrations with real-world experiences. Topics covered include: materials, plantings and coatings, locking methods threads, joint stiffness, rivets, inserts, nut plates, thread lubricants, design criteria, etc. These presentation slides accompany the DVD.

Barrett, Richart T.↗
NASA NTRS2014

Torque Tension Testing of Fasteners used for NASA Flight Hardware Applications

The effect of various lubricants and other compounds on fastener torque-tension relationships is evaluated. Testing was performed using a unique test apparatus developed by Posey at the NASA Goddard Space Flight Center. A description of the test methodology, including associated data collection and analysis will be presented. Test results for 300 series CRES and A286 heat resistant fasteners, torqued into various types of inserts will be presented. The primary objective of this testing was to obtain torque-tension data for use on NASA flight projects.

Hemminger, Ed↗
NASA NTRS2018

Characterization and Analysis of Aerosol Particle Retention and Re-aerosolization from Hook-and-Loop Fasteners on the International Space Station

The extensive use of hook and loop fasteners aboard the International Space Station warrants careful examination of its contribution to indoor air pollution, as its fine fibers catch aerosol particles then re-aerosolize them upon being pulled apart, often within the breathing zone of astronauts. This problem is expanded by the lack of gravity because airborne particles larger than 1 micrometer do not settle. Instead these aerosols remain in the air until removed by filtration. Aerosol inhalation can have negative health effects, ranging from acute symptoms to long-term consequences, depending on particle sizes, mass and material composition. This study characterizes the size distribution, number concentration, and mass concentration of re-aerosolized debris generated by hook and loop fasteners taken from the stray light cover of the Microgravity Science Glovebox in the U.S. Laboratory of the ISS to understand the extent of its impact on air quality. Transmission electron microscopy (TEM) and scanning transmission electron microscopy (STEM), in conjunction with energy dispersive spectroscopy (EDS) were also used to characterize the morphology and composition of the particles.

Boyajian, Barbara↗
NASA NTRS2019

Evaluation of LS-DYNA MAT162 for Modeling Composite Fastener Joints for High Rates of Loading

In the present work, the behavior of composite-fastener joints in bearing failure at dynamic stroke rates of 500 in/s, 300 in/s and 100 in/s has been evaluated through progressive damage analysis (PDA) material model in LS-DYNA, namely MAT162. Two joint types: titanium pin and Hi-Lok® fastener were analyzed to identify the differences between without and with preload conditions. A meso-level approach where each lamina was modeled separately was employed and a contact definition based on fracture toughness data was defined to represent composite delamination behavior. Test fixture had been modeled in a detailed manner to account for the dynamic effects and the simulation results were validated against experimental data. Preliminary test-analysis correlation indicated that MAT162 predicted results conservatively when compared to tests. Debris accumulation were observed to greatly affect the test results which were not considered in the current modelling strategies.

Kona, A.↗