Carbon/epoxy Composite Manufacture, Aerospace

[aeroplane123]

Hello, and thank you for viewing my question.

Just a query I have regarding composites (carbon/epoxy, 0/90 degree orientation)

When designing a composite wing skin, to stiffen it, I propose to either have thicker geometry, insert a core (not sure which one) or add stringers. Am I correct in thinking all 3 methods would provide adequate stiffness?

To manufacture the wing skin, would the integration of a core be the best option in your opinion? How should it be manufactured (any production problems you think could occur)?

Many thanks in advance for your response!

[Answerprancer]

Give me a couple of days - I have friend who is a structural engineer for NASA, I'll ask him. I assume this is a model you're talking about (?)

[aeroplane123]

That would be much appreciated! It's just a proposal for a university composites design project. My investigation is the upper section of the wing (military fighter jet). I have to identify the best method of stiffening the wing and propose a manufacture method. Thanks again Answerprancer.

[Clanad]

You haven't stated which skin you propose to design, the upper or lower, neither have you stated whether the wing is swept or not. Finally, I think you're going to have to at least estimate the wing loading requirements.

Regardless, I think you'll find that the design is primarily based on the bays built into the wing structure in which case the usual stiffening method (if there is a usual method) is to design in what you refer to as "stringers". These are most often, in my experience (I'm not an engineer, BTW) used as stiffeners but are separated (by many factors) into "J", "Z", "Hat", "I" or "V" for design element considerations. (There are other, more exotic stringer designs I've heard discussed).

[Clanad]

Apologies, I see, on re-reading the questions, that you have stipulated upper skin, which is designed with "compression stress" considerations as well as maximum flex allowances...