...
Introduction
The design of a bonded repair is often more demanding than the
ab initio
design
of a bonded structure. For example, secondary bending in the repair, often induced
by the repair ...
borodepoxy
outer. One layer
of cocured
FM 73
on
bonding
surface.
Fig.
5.8.
Schematic
of
the skin doubler specimen (not
to
scale).
128
Advances
in
the bo...
... in the
bonded
composite repair of metallic aircraft structure
ioo.0
Fig.
10.22.
Typical auxiliary model used in the shape optimisation procedure for
F/ A-18
aileron hinge,
showing point ... function by transferring some portion of the load from the
reinforced component through the adhesive bond layer, thereby reducing the range
and mean
of
the cyclic st...
...
Advances
in
the
bonded
composite
repair
of metallic uircraft structure
Following the development
of
a bonded- composite repair for
MSD
in the
fuselage lap-joint of wide bodied transport aircraft ...
is
done for the
purpose of increasing the fatigue life of the joint. In service, environmental
degradation may cause this bond to become ineffective,...
... have also benefited from the use of this
technology. The application for the solution of the problem of cracking in the fuel
drain holes in wing of the
C-141
is credited with maintaining the ... determine the economic life of the airframe.
Unfortunately, management of corrosion by the setting of inspection intervals is
not always effective since the location of...
... Keeping void contents low is a matter of recognising
the origins of the voids and ensuring that appropriate procedures are used. If the
64
Advances in the bonded composite repair of metallic aircraft ...
Advances in the bonded composite repair
of
metallic aircraft structure
current understanding and the complexity of the bonded joint, there is...
... practice, however,
structures to be reinforced may be finite in size or constrained by the surrounding
structure.
To
quantify the effect of this constraint, consider the configuration
shown in Figure ... even though the load transfer through
the bonded joint around the periphery of the patch
is
not
instantaneous in the
manner of the inclusion model, it is
s...
... then decay
linearly to zero at the free surface of the skin (or plane of symmetry in the case of a
patch on both sides
of
the skin). This results in the matrix
D
having the form:
D
=fO ...
joints were far more prone to fatigue failures, where the skins butted together, than
the nominally equally stressed portions
of
the skins.)
8. 13.
Remaining challenges invo...
... (referring to Chapter 13 for
more details). In the following, we will focus our attention on the influence of
thermal residual stress only.
For
an orthotropic composite patch bonded to an isotropic ...
Application of analysis
to
large repairs of aircraft wings
The object
of
this section is to determine the applicability of a closed form
solution to the large repa...
...
aluminium alloy structures; it contains nine main sections covering repair of thin
skin components, repair of thick sections, gr/ep versus b/ep patches, effect
of
bondline defects, effect of impact ...
microstrain. Since strain capacity of the boron/epoxy is measured to be about
730 0
microstrain, the conclusion is that failure was probably a result of initial
failure of the...
... assessment
of
bonded composite doubler repairs
491
Application
of
impact damage
to
composite
coupons
Following the composite doubler installation and prior to environmental
conditioning, ...
Advances
in
the bonded composite repair of metallic aircraft structure
2.
The load was increased, using displacement mode control, at a continuous rate
of O. OSin...