... use of this
technology. The application for the solution of the problem of cracking in the fuel
drain holes in wing of the
C -14 1
is credited with maintaining the viability of this
fleet.
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...
... 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
provides little inherent corrosion protection. Although the use of a few rub...
... account for this characteristic
10 0
Advances in the bonded composite repair
of
metallic aircraft structure
4.5.4.
Fickean diffusion coeflcients for moisture absorption
Althof
[24]
gives the ... strain gauge outputs for the cyclic strain response
to various cyclic loads for one of the strain gauges. The initiation load for this
specimen was 24.2kN using the...
...
[(Et),,,,h/(Et),kin)]
is referred to as the stiffening ratio for the patch. In addition,
the process of deducing the bonded overlap
1
in
Eq.
(8.8)
as the sum
of
the lengths
of the load-transfer zone(s) ... practice, however,
structures to be reinforced may be finite in size or constrained by the surrounding
structure.
To
quantify the effect of this const...
...
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
[
&apos ;1
in the ...
For the repaired specimens it was not possible to monitor the crack for more than
approximately
10 -1
1
mm of growth due to interference from the outer edge...
...
tt-'
is the
height for step
k.
280
Advances in the bonded composite repair of metallic aircraft structure
Table
10 .1
Geometric details for patch on one side of plate for non-
uniform ... Section 10 .1, for the design of a typical bonded reinforcement to a
component, there are two particular regions of concern for the adhesive layer. These
Chapter...
... at the boundary are given by
Eq.
(11 .16 ):
(11 .65)
The constants of integration
C,
and
C3
are now found from the solution of
Eqs.
(11 .18 , 11 .19 , 11 .63).
If the edge restraint factor ... result of the difference in thermal
coefficients
of
expansion. The following equations will be given for a simple double
overlap joint whose geometry is given in Figur...
... ~1 1 (1 (1. 111 1. (1. l l l~ ~l~ l ~
Advances in the bonded composite repair of metallic uircruft structure
Fig. 15 .10 ,
Effect
of
patch type
and defects
on
rate of fatigue crack
growth ... Beninati,
0.
(19 97) Repair efficiency in composite patched panels after removal of
9.
Baker, A.A. (19 97). On the certification of bonded composite repairs t...
... in addition to fasteners, the lap joints are
bonded together, either using hot or cold setting adhesives. This
is
done for the
purpose of increasing the fatigue life of the joint. In service, ... pp. 4 214 38.
Martinus Nijhoff, pp. 10 7 -17 3.
CP-550, pp. 3 .1- 3 .12 .
Conf.,
USAF.
ConA,
USAF.
Integrity
Conf.,
USAF.
480
Advances in the bonded composite r...
... the bonded composite repair of metallic aircraft structure
21. Roach, D.P. (20 01) . Commercial application
of
composite doublers for DC-IO fuselage repairs,
Int’l.
SAMPE Synzp.
on
Composites ... in one piece.
Chapter
1
I.
Damage tolerance assessment
of
bonded composite doubler repairs
4 91
Application
of
impact damage
to
composite
coupons
Followin...