2-6 August 03
A test wing
section to check our build process. This was made in glass rather than
carbon to better see the quality of the laminate. The spar is completed
in the classical way by gluing the shear web into flanges on the lower
shell as the moulds are closed. Interesting questions also include ideas
about bleed rate through the PVC holes, PVC bonding, PVC stiffness affecting
the compaction of outer laminate. Tom may do a small report on this test
section.
July 03
A measuring device was made by young engineers Craig Player and Peter
Howard. It was nicknamed Mr Klause.
April 03
Wing spar caps were laid up in the wing moulds between wooden dams. The
"spar bridge" moulds shown here.
Caps for this prototype are layers of unidirectional carbon cut dry to
the spar planform. After initial cure they were demoulded and will be
secondary bonded into the shells.
April 03
Three 900mmx45mmx35mm test spars were made to test the materials, design
and fabrication methods to be used in the wing. Whilst we can't really
determine the failure mode and material properties this way we can at
least see the failure loads.
Control surface and tailplane plugs. Tailplane has a straight part line
on the fin well below the intersection.
Fuselage moulds showing the styrofoam mould insert for the canopy sill.
The styrofoam was hotwired to shape then abraded with a formed block.
Many small cuts allow the bending.
Preparing fuselage
plug, moulds and cradle.
Making wing plugs and
moulds.
Making fuselage plug.