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Ch05 - Fuselage Sides

The sides are constructed on a Duratex, I will use a leaf of MDF of 4mm. The longerons will be confectioned in freijó, I am waiting my shipment to arrive from Pará.

Nothing of shipment, funny that I live 400 km of the Amazonia Forest, and I would have to buy the freijó in Brasilia DC at 1000km. To broad beans with freijó, I used the cedroarana, is lighter, much better. The wood longerons are not structural, the only purpose is to screw things in them.

In a fiber aircraft is important to have some core between the laminates, can until being that washer bushing that your beloved mom played outside. Experimetal prove “almost” of everything.

	06/02/2008 Vance Atkinson Fuel Sight Gauges.
	07/03/2008 After accurate 30 days without making anything, there are the upper longerons. Confectioned in cedroarana.
	Shape was perfect, I leave 3 days to pop off. They are glued ones to the others only with Epoxy. Forgive me the dirt shop, hihihi.
	The reinforcements are glued with flox. Still it lacks one reinforcement.
	20/03/2008 I go to build first one side, and after the other. Thus I can laminate alone, and not necessary to continuously work 9 hours.
	15/04/2008 The new Home. The workshop is well great 3.70m X 4.90m, had fit all the apparatuses. I don`t know if I go to break the window to take out the fuselage.
	Back in the deep one pequi tree, now it is alone to catch in the yard and to place in the rice, sô! Pequi is one fruit of the cerrado, one kind of vegetation terrain, very hot and dry climate with little trees. The pequi savoury very good, and is tasty. But inside the seed have small sharp points, just appreciate but don`t bite the seed.
	Already I placed two fabrics UND of 30 crossed degrees, and installed the superior longeron. It notices the doubler that supports the F28 and the canard. In it also I will fix the hinges of canopy. The circle is bevels of 8 " hand clearance to the stick. I did not obtain enough vacuum in this part, it had some bubbles, which I had that to inject Epoxy.
	Here is the electric wire duct, and the bevel to the fuel site gauge.
	16/04/2008 The longeron lamination in plans is 4 ply UNI 7715. I made mine with 2 ply of carbon tape. Over than I put 1 ply of aramide KK205 45/-45 , therefore if the carbon fractures extremely dangerous swords are formed. Aramide, for its characteristic of high safe tenacity hold the carbon points. This technique or composition, aramide over carbon, is used in all the space vehicles to protect the crew. As my canopy will be of carbon and aramide don`t matter the thermal coefficients.
	The substitution was not made in lack of calculations, is clearly that in composites all the structure is reached when a modification becomes. Below is one table of calculations. Remembering that I will not search reduction of weight in this case, therefore they are the reinforcements on the wood that make of this a structural element. Easily 1 ply of carbon would substitute the 4 ply of glass, is clearly, with the aid of the aramide one.
	Peel ply over aramide. The doubler was reinforced with 1 ply 45/45 Carbon BID 3k, Finally, the small extra weight brings me the benefit to have non leaks of water or air inside the airplane and will support mine canopy with security. Beyond superior rigidity, and I believe better commands response.
	17/04/2008 Inferior longeron with flox and wire duct with 1ply BID. An important detail is to leaves the inferior foam 1/4" greater, therefore some constructors had had a gap in the laterals due to a small opening.
	18/04/2008 LWX and LWY flox and 1 ply BID @ 45.
	19/04/2008 I used a cardboard piece to verify the contours of the panel that is situated at 19,25" of the beginning of the longeron.
	Cd marker pen.
	Very good fit.
	One more.
	Seat back contour.
	All done, make these in ch05 help me in the 6.
	Aft side of the seat back.
	21/04/2008 I decided that it would be more easy and practical to mold the duct in the foam, instead of making one plug.
	I carved the depression and after put 1ply BID.
	23/04/2008 Left side finished with 6 ply BID @ 45 over the duct area.
	2904/2008 The reason of the construction in composites to be delayed is because you need to wait that one has left cures to continue with the other, and this takes 24h. Meanwhile I watch my films of canards. I continue constructing the right lateral, I believe that more two days will be enough.
	04/05/2008 The weights are 5.413g and 5.472g. To the 6...

Comparação de peso e cargas do UNI 7715, KK205 e Tape de Carbono 32U
	Weights g/m²	Wrap Rupture Force Kgf/cm	Fill Rupture Force Kgf/cm
Carbontape 32U da Texiglass	696	680	10
Carbontape 32U da Texiglass - 2 ply	1392	1360	20
Aramide KK205 da Texiglass - 1 ply	200	200	200
Total	1592	1560	220
UNI 7715 da Hexcel	247	80	14
UNI 7715 da Hexcel - 4 ply	988	320	56
Diference UNI to Composition C/A	-604	+1240	+164

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