... 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...
... 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...
... 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 corrosion and its rate of ... 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 viab...
... 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...
...
Advances in the bonded composite repair
of
metallic aircraft structure
4.5.4.
Fickean diffusion coeflcients for moisture absorption
Althof
[24]
gives the following data for the diffusion coefficients ...
The adhesive to metal or composite interface
0
The adhesive to primer interface
0
The surface matrix resin of the composite
0
The near-surface pli...
... 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 ... program, reported in reference
[I6],
have
confirmed this need. Indeed, the tendency for the centroid of the skin/patch
combination to align itself with the plane of acti...
...
mm from the centre of the lower lug and continued to the
end
of
the “horizontal” section around the lug, as indicated in Figure 10. 24. The first
ply of the boron/epoxy reinforcement was then ... 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/...
... the first being the isotropic solution and the second the
orthotropic solution. Application of a closed form solution to the repair of an
aircraft wing requires an assumption of the value of ...
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 repair o...
...
DERA
research on bonded composite patch repair
of
aluminium alloy structures; it contains nine main sections covering repair of thin
skin components, repair of thick sections, gr/ep versus ...
(1997) Repair efficiency in composite patched panels after removal of
9.
Baker, A.A. (1997). On the certification of bonded composite repairs to primary aircraft structu...
...
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,...