• Welcome aboard HomebuiltAirplanes.com, your destination for connecting with a thriving community of more than 10,000 active members, all passionate about home-built aviation. Dive into our comprehensive repository of knowledge, exchange technical insights, arrange get-togethers, and trade aircrafts/parts with like-minded enthusiasts. Unearth a wide-ranging collection of general and kit plane aviation subjects, enriched with engaging imagery, in-depth technical manuals, and rare archives.

    For a nominal fee of $99.99/year or $12.99/month, you can immerse yourself in this dynamic community and unparalleled treasure-trove of aviation knowledge.

    Embark on your journey now!

    Click Here to Become a Premium Member and Experience Homebuilt Airplanes to the Fullest!

Spar Failure

This site may earn a commission from merchant affiliate links, including eBay, Amazon, and others.

proppastie

Well-Known Member
Joined
Feb 19, 2012
Messages
6,390
Location
NJ
This is real...Background: Phil in Ireland is building a Carbon Dragon and testing his spar had a failure.

http://www.ihpa.ie/carbon-dragon/in...ress-on-phil-lardner-s-all-carbon-cd?start=60

He has decided to splice the center with Aluminum. This splice is similar to what I am doing with my Aluminum Dragon.

Now comes the question.:

When doing the stress analysis of a wing all the references show the moments for 1/2 the wing.

Is it possible the moment at the exact center is twice that.

Shown below is my "lineal FEA" (Grape)

sparcarrythrough1.jpg

The load on the wing is represented by 1919# at centroid of 110" shown is the whole wing.

The reaction at node 8 is 3838 (2x 1919) ....so the moment is 422180 in-lb at the exact center?
 
Back
Top