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ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...
MIL-R-7885D General Specification for Rivets, Blind, Structural, Mechanically Locked Spindle and Friction Locked Spindle
This specification covers mechanically locked spindle and  friction locked spindle ...
MIL-HDBK-132A Protective Finishes for Metal and Wood Surfaces
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NASA-TM-2006-214323

NASA-TM-2006-214323
  • Version
  • 105 Downloads
  • 2.11 MB File Size
  • 1 File Count
  • April 6, 2016 Create Date
  • April 6, 2016 Last Updated
Scroll for Details

Experimental Observation for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fasteners

NASA-TM-2006-214323 Experimental Observation for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fasteners

Aerospace structures utilize innovative, lightweight composite materials for exploration activities
in low—Earth orbit for the Space Shuttle and the International Space Station. Composite structures will
be used for future space exploration beyond low—Earth orbit to the moon, Mars, and other destinations
in crew exploration vehicles and habitats. These structural components will take advantage of the high
strength—to—weight ratio, good thermal characteristics, and tailorability offered by composite structures.
For a variety of reasons, including size limitations, manufacturing facilities, contractual obligations,
or particular design requirements, the joining of composite components will be required. Adhesively
bonded and mechanically fastened joints are common methodologies for joining composite components
that have analytical precedence and practical applications. In some applications both methods are simul—
taneously incorporated into the design. Guidelines and recommendations for establishing design criteria,
analyzing, and testing composites are readily available for engineers to adapt for their particular appli—
cations. However, guidelines and recommendations, based on analysis and testing, are not available
for specifying a fastener torque range used in joining composite components. The intent of this investi—
gation is to develop an initial process for determining the maximum torque values to apply to mechani—
cal fasteners used to join composite components and hence, the initiation of a recommended torque
limit that designers utilize when specifying torque values to join composite components with mechan—
ical fasteners.

The objective of this investigation is to develop an initial process for determining the maximum
torque values to apply to mechanical fasteners used to join composite components, and select an
acceptable nondestructive failure detection methodology to determine composite specimen failure.

The intent is to generate a recommended torque limit to apply to composite components joined with
mechanical fasteners that designers specify on manufacturing drawings.

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NASA-TM-2006-214323 Experimental Observation for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fasteners.pdfDownload 

NASA-TM-2006-214323

NASA-TM-2006-214323
  • Version
  • 105 Downloads
  • 2.11 MB File Size
  • 1 File Count
  • April 6, 2016 Create Date
  • April 6, 2016 Last Updated
Scroll for Details

Experimental Observation for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fasteners

NASA-TM-2006-214323 Experimental Observation for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fasteners

Aerospace structures utilize innovative, lightweight composite materials for exploration activities
in low—Earth orbit for the Space Shuttle and the International Space Station. Composite structures will
be used for future space exploration beyond low—Earth orbit to the moon, Mars, and other destinations
in crew exploration vehicles and habitats. These structural components will take advantage of the high
strength—to—weight ratio, good thermal characteristics, and tailorability offered by composite structures.
For a variety of reasons, including size limitations, manufacturing facilities, contractual obligations,
or particular design requirements, the joining of composite components will be required. Adhesively
bonded and mechanically fastened joints are common methodologies for joining composite components
that have analytical precedence and practical applications. In some applications both methods are simul—
taneously incorporated into the design. Guidelines and recommendations for establishing design criteria,
analyzing, and testing composites are readily available for engineers to adapt for their particular appli—
cations. However, guidelines and recommendations, based on analysis and testing, are not available
for specifying a fastener torque range used in joining composite components. The intent of this investi—
gation is to develop an initial process for determining the maximum torque values to apply to mechani—
cal fasteners used to join composite components and hence, the initiation of a recommended torque
limit that designers utilize when specifying torque values to join composite components with mechan—
ical fasteners.

The objective of this investigation is to develop an initial process for determining the maximum
torque values to apply to mechanical fasteners used to join composite components, and select an
acceptable nondestructive failure detection methodology to determine composite specimen failure.

The intent is to generate a recommended torque limit to apply to composite components joined with
mechanical fasteners that designers specify on manufacturing drawings.

FileAction
NASA-TM-2006-214323 Experimental Observation for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined with Fasteners.pdfDownload 
17,003 Documents in our Technical Library
1344582 Total Downloads

Search The Technical Library

Newest Additions

ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...
MIL-R-7885D General Specification for Rivets, Blind, Structural, Mechanically Locked Spindle and Friction Locked Spindle
This specification covers mechanically locked spindle and  friction locked spindle ...
MIL-HDBK-132A Protective Finishes for Metal and Wood Surfaces
The primary object of this handbook is to provide a ...