aeroplane123
New Member
Hello, and thank you for viewing my question.
Just a query I have regarding composites (has to be manufacturing using 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)?
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.
Many thanks in advance for your response!
Just a query I have regarding composites (has to be manufacturing using 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)?
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.
Many thanks in advance for your response!
