The term ‘stressed skin’ is often used when describing aircraft construction.
What does it actually mean?
I can see how wires and struts hold a plane together, but how does ‘stressed skin’ provide strength – or is that done by stringers, formers, and the spar?
By: Hamtech - 17th December 2004 at 07:24
Seafuryfan,
A good point of research on the subject is the use of “monocoque” and “semi-monocoque” structures in construction.
I cant think off the top of my head an example of a pure monocoque machine but is just the skin and bulkheads only – no stringers or longerons.
A handful of wood and a couple of metal machines if memory serves use this.
Some reading here:
AC 65-15A, Download chapter one
– Hamtech.
PS: dhfan – Today I was handed a gorgeous, genuine Gipsy Major Maintenance and Overhaul manual sadly from a now departed former Engineer.
By: dhfan - 17th December 2004 at 03:14
AFAIK, with possibly a few exceptions the skin isn’t pre-stressed.
If you take an early Hurricane as an example, the primary internal structure is designed to be strong enough to take all the loads and stresses. In practice the fabric does add a certain amount of strength but I believe it’s fairly minimal.
Compare that with a Spitfire where the internal structure is nowhere near strong enough. The rigidity and strength only comes when the skin is rivetted on. Although the formers, bulkheads and stringers take some of the overall load, they’re as important to keep the skin the right shape.
By: Seafuryfan - 17th December 2004 at 00:13
How then is the skin ‘tensioned’ (or stressed), to help provide strength? It looks from my non-engineer view as if a sheet of metal is placed over the structure and rivetted on. How can the maufacturer tell if it is providing strength as opposed to just being rivetted on top?
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December 16, 2004 at 11:44 pm