Honeycomb Beam & Panel Calculations



This spreadsheet has been developed to allow design engineers to quickly size honeycomb panels with a minimum of work. The calculation is driven from 'Home' worksheet using a simple 5 step process.

1) SELECT Core material from drop down box:
2) SELECT skin material from drop down box:
3) SELECT Panel Loading condition from drop down box:
? Beam, Simple Support with Uniform Load Distribution
? Beam, Both Ends Fixed with Uniform Load Distribution
? Beam, Simple Support with Central Load
? Beam, Both Ends Fixed with Central Load
? Beam, Cantilever with Uniform Load Distribution
? Beam, Cantilever with Load at End
? Rectangular plate, simply supported, uniform load.
? Rectangular plate, clamped, uniform load.
? Rectangular plate, simply supported, concentrate load over small area
? Rectangular plate, clamped, concentrate load over small area
? Circular plate, simply supported under uniform distributed load
? Circular plate, clamped under uniform distributed load
? Circular plate, simply supported under central force
? Circular plate, clamped under central force
4) INPUT Panel dimensions and total load
5) READ Results - Green ticks indicate an acceptable result. Red crosses indicate an unacceptable result.
Although it is only necessary to use the 'Home' worksheet all supporting data and detailed calculations are given on other worksheets.

Calculation Reference
Honeycomb Panel Design
Composite Panel Design
Designing with Lightweight Materials

Calculation Preview

Submitted On:
23 Jul 2020
File Size:
383.94 Kb
File Version:
File Author:
John Doyle

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Comments: 8
katzalex2 11 days ago
Could you send me please file to mail katzalex2@gmail.com
adongkidd 19 days ago
Hi John,
can u pls send me this file to my mail.
Tom Deiters 1 year ago
Hello John,
I recently ran across a problem where the honeycomb panel was composed of different upper and lower face sheet thicknesses, for instance, upper face sheet was 1.27mm lower face sheet was .635mm. The upper face will be in compression whilst the lower is in tension. To create a minimum weight panel the face sheets were optimized. This occurs on Embraer floor panels. This creates a bit of an analysis challenge. Can you offer a suggestion?
TimAcland 1 year ago
Hi John,
I couldn't find any reference of where you got the material properties from, especially the face/skin materials. I tried to google the description names of the skin materials but couldn't find anything useful not even on hexcel's company website. Can you please provide the source of your material data? I want to find the datasheets of the different materials. Thanks
JohnDoyle[Admin] 5 years ago
Corrected the following error reported in by T181:
JohnDoyle[Admin] 5 years ago
Version 1.2 has just been uploaded.
JohnDoyle[Admin] 5 years ago
You are correct T181 I afraid there is an error in the core shear stress for cases 11 and 12. I will make the correction and upload a new version. Thanks for reporting this in :)
JohnDoyle[Admin] 8 years ago
I'm afraid the wrong calculation was posted to the site which did not include formulas for face stress so the calculation only showed a fixed value.
The face stress values are fixed in this new version.