cappy208 wrote:Although my experience is 25 yrs ago, some underlying thoughts are still true.
The delamination of the panels (in whatever vehicle) are generally caused by 3 things:
1. poor layup/ adheshive mixture.
2. too large a panel, with no recurring connection between inside and outside lams.
3. No/ failed adhesion between core and skins.
After many many many destructions repairs I found many examples of NO connection between the inside and outside lams, regardless of plywood, foam, balcore, airex, honeycomb paper. If there was too large an area of a panel, there MUST be frequent stitching between the inside and outside skins to maintain a panels integrity. However that is done is up to the laminator. But Some of the ways done are: small core panels, with tapered sides, saw cuts through frequently to allow eposy/ester resin to connect between inner and outer skins, and holes with fabric brought through, and incorporated into each side skin.
I’m with you on 1 and 3, but 2 is not a reason for failure if the panel skins are sized correctly. Now, it may be true that once a delamination starts, that the strain level in the panel is such that the delamination grows, but size of the panel itself is not a failure reason. The scarfing of the core as you suggest, or the pocking of holes at 50 mm intervals as suggested by the core manufacturer (and discussed previously) should act to prevent the core from failing in a tension-type failure mode between the skin and the core. In the case of honeycomb core, the resin drips down the cell walls and prevents this type of failure better than most other core products, but is it quite expensive. Cheaper would be to score or poke holes in the foam core to allow resin to get a grip for out-of-plane loading.
cappy208 wrote: The failed laminations are GOING to happen regardless of how you make it. The trick is making the panel size small enough or with cuts through the core panel so there is frequent attachments all over the panels. then what you have is a series of small localized delams, which don't effect the structural strength of the panel as a unit.
Again, if the panel is sized properly for the loads, it shouldn’t delaminate (not that your suggestions of scoring the panel are good ones BTW). Delaminations generally (for thin facesheets) are caused due to facesheet wrinkling, which will exhibit itself as a delamination between the core and facesheet, but the separation may not be due to merely an adhesive failure. If the facesheet has bits of foam stuck to it (which I have seen on man test specimens) then it’s not an adhesive failure but due to a facesheet overload (for the given thickness) the core actually fails. The facesheet wrinkling is influenced by the core stiffness (denser cores are more stiff), laminate stiffness, and laminate thickness. So, it’s not always easy to determine the exact cause, but the skin thickness and layup (stiffness) overall has a bigger impact. Delaminations can also occur do to impact loading, for instance (especially on a boat that may smack rocks, docks, or other boats). I have the equations, if anyone is interested, but I don’t think they are so useful for the average user.
cappy208 wrote:The cost of the particular core material is directly related to its marketability to the use. That may sound dumb, but balcore (for instance since its the oldest, most well known) has tensile strength, is adherable (both by epoxy and ester resin) progressing through the other known core material, until you get to the blue/orange board being discussed frequently on this forum. These dow poly iso, or styrene boards have -0- holding power, NO structural significance, and must only be looked upon as the means to provide separation between skins.
It is NOT the foam core that is providing any structural strength. it is the "channel" of two skins, separated by space. We used to use cardboard tubes, to lay on the hull to glass over, to make a channel to stiffen hulls (and also provide wiring/pipe runs down the hull) so even an open space between layers of glass forms a strong panel!
I have to completely disagree with your statement on the home depot foam since I know of several planes that are flying that use it as well as another friend that is building one now that has already successfully gone through full-scale testing of the wing.
It’s more proper to say that the strength is not high, but it is known and it can be design with those allowable in mind. Without the core in fact, the skins are quite weak – especially in the transverse shear direction. It can’t be used willy-nilly without thought for the expected failure modes, but it can be made to work (there have already been a couple of tears built that way, so it actually not a particularly new approach). What is helpful to understand is that it probably isn’t adequate for high local load introduction (which has already been discussed in detail). In that case, plywood plugs (or epoxy pucks, as we call them)) should be buried in the core to transfer that concentrated load.
I’m not trying to say you are not bringing up good points, and in fact, the scarfing or poking of the foam core is critical to getting good out of plane adhesion, so your points about that are well taken. However, the 2 lb/ft cu. core does have structural properties and when properly designed can be relatively robust. Whether it would work for your particular application is something I couldn’t answer