17,004 Documents in our Technical Library
2089351 Total Downloads

Newest Additions

AA-CP-20212-001
AA-CP-20212-001
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 ...

NACA-TN-1051

NACA-TN-1051
  • Version
  • 956 Downloads
  • 34.41 MB File Size
  • 1 File Count
  • April 19, 2016 Create Date
  • April 19, 2016 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Technical Notes - Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints
NACA-TN-1051 Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints
A general solution is presented for the determina-
tion of loads carried by individual bolts in symmetrical
butt joints. Expressions for bolt behavior are given by
which the general solution may be readily adapted to the
numerical calculation of bolt loading in joints made of
any of several combinations of materials common to air-
plane construction, and an example is solved to illustrate
the numerical procedure. All expressions are confined to
the range of elastic action of joint components.
From the tests of three—bolt joints, agreement within
about 10 percent was found between theoretical and experi—
mental bolt loads within the elastic range. Although the
bolts carried markedly unequal loads in the elastic range
(as indicated by theory), it was found for such joints
(containing not more than three bolts in the line of
stress) that a process of bolt-load equalization took
place beyond the limit of elastic action which for practi—
cal nurooses caused the bolts to be loaded equally at
joint failure. Information is needed with respect to
multirow joints, however, because in the elastic range
the bolts in the first rows carry far greater loads
than interior bolts and joint failure may occur before
complete equalization of bolt loads is realized.
In recent years the need for more rational means of
design and analysis of connections has been emphasized by
the exacting requirements of modern airplane construction.
The methods of joint analysis are far more antiquated than
those employed for other parts of the aircraft structure.
Improved methods for predicting joint strength offer a
means of reducing weight if they are adapted to make more
efficient use of all connectors within a joint.  From the
production viewpoint, Jenkins (reference 1) has shown that
approximately 50 percent of the total cost of the all—
metal airplane frame is due to connecting the various
components of the structure and that the cost of riveting
and bolting constitutes between 80 and 90 percent of the
total cost of connections. These conditions suggest a
promising field for investigation.

Comment On This Post

Your email address will not be published. Required fields are marked *

FileAction
NACA-TN-1051 Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints.pdfDownload 

NACA-TN-1051

NACA-TN-1051
  • Version
  • 956 Downloads
  • 34.41 MB File Size
  • 1 File Count
  • April 19, 2016 Create Date
  • April 19, 2016 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Technical Notes - Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints
NACA-TN-1051 Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints
A general solution is presented for the determina-
tion of loads carried by individual bolts in symmetrical
butt joints. Expressions for bolt behavior are given by
which the general solution may be readily adapted to the
numerical calculation of bolt loading in joints made of
any of several combinations of materials common to air-
plane construction, and an example is solved to illustrate
the numerical procedure. All expressions are confined to
the range of elastic action of joint components.
From the tests of three—bolt joints, agreement within
about 10 percent was found between theoretical and experi—
mental bolt loads within the elastic range. Although the
bolts carried markedly unequal loads in the elastic range
(as indicated by theory), it was found for such joints
(containing not more than three bolts in the line of
stress) that a process of bolt-load equalization took
place beyond the limit of elastic action which for practi—
cal nurooses caused the bolts to be loaded equally at
joint failure. Information is needed with respect to
multirow joints, however, because in the elastic range
the bolts in the first rows carry far greater loads
than interior bolts and joint failure may occur before
complete equalization of bolt loads is realized.
In recent years the need for more rational means of
design and analysis of connections has been emphasized by
the exacting requirements of modern airplane construction.
The methods of joint analysis are far more antiquated than
those employed for other parts of the aircraft structure.
Improved methods for predicting joint strength offer a
means of reducing weight if they are adapted to make more
efficient use of all connectors within a joint.  From the
production viewpoint, Jenkins (reference 1) has shown that
approximately 50 percent of the total cost of the all—
metal airplane frame is due to connecting the various
components of the structure and that the cost of riveting
and bolting constitutes between 80 and 90 percent of the
total cost of connections. These conditions suggest a
promising field for investigation.

FileAction
NACA-TN-1051 Preliminary Investigation of the Loads Carried by Individual Bolts in Bolted Joints.pdfDownload 
17,004 Documents in our Technical Library
2089351 Total Downloads

Search The Technical Library

Newest Additions

AA-CP-20212-001
AA-CP-20212-001
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 ...