Today's Message Index:
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1. 05:47 AM - glass or carbon (Kayberg@aol.com)
2. 05:58 AM - Re: glass or carbon (georgiemun)
3. 07:20 AM - Re: Re: glass or carbon (nick otterback)
4. 08:22 AM - Re: glass or carbon (georgiemun)
5. 11:10 AM - construction questions (Tex Mantell)
6. 01:52 PM - Re: Re: glass or carbon (Kayberg@AOL.COM)
Message 1
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I undestand that when you make absolute statements you can be found wrong
sometimes, but the cut and paste below came from the Arion website,
"Specifications" page.
Construction Vacuum infused oven post cured fiberglass
I was also basing my conclusions from my own hands-on building of our first
Lightning. We did the preliminary assemble in Shelbyville next to a
carbon-fiber build of an Esqual. Quite an obvious difference in color and texture
of
the cloth. There are a couple items on a Lightning that may be carbon fiber,
but they are not major airframe components.
But I am feeling a bit suckered. If the static load was taken to 5 gs and
the design was higher yet, I would not personally care if it was constructed
of banana peels and peanut butter. But it isn't. Vacuum infused, oven post
cured fiberglass is the industry standard, not only for airplanes but a
whole universe of stuff.
When I visited the Pulsar factory, they were doing VACUUM INFUSED OVEN POST
CURED FIBERGLASS!
(in a bit of an archaic manner, which is why they are no longer significant
players) Their shop forman had gained his experience doing VACUUM INFUSED
OVEN POST CURED FIBERGLASS in the Phillipines working for LANCAIR.
If the Arion folks want to throw some carbon cloth in the epoxy, that is
fine with me. I wouldnt care if the edges flapped in the breeze before I ground
them off. I would like to see some testing if they want to use banana peels.
Doug Koenigsberg
Message 2
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Subject: | Re: glass or carbon |
Hey, no problem; I'm just trying to learn as much as I can about the construction
of the aircraft that I might be buying. I do have a question for Nick tho...
One that I asked earlier, but was overlooked.
Why does the carbon fiber stop at the root of the wing and does not continue through
to the tip of the spar? Is there a reason for this?
Also, it appears then that the spar is of a somewhat hollow construction with the
foam creating the cavity? I guess this is done to save weight for the a solid
wing spar is not necessary in this case?
Thanks for any clarification that you guys can give.
Kayberg(at)aol.com wrote:
> I undestand that when you make absolute statements you can be found wrong sometimes
Read this topic online here:
http://forums.matronics.com/viewtopic.php?p=92780#92780
Message 3
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Subject: | Re: glass or carbon |
The wing spar is of fiberglass, carbon fiber, foam , and wood construction.....the
root end which is in the fuselage is 1/16 per laminet wood core being 1" thick
this stops at the wing root and is than a fibergalss foam woven core... this
mean the the foam core has woven fiberglass in it for more strength....the
wood is used as a high density light filler at the root end.....the spar caps
ar 1"by1" rolled unidirectional glass which tapers down to 1"by 1/2" at the tip.....The
material thru out the spar is heavier at the root end and lightens
up at the tip as to be expected....... yes there is a carbon fiber laminte in
the spar... this runs from just inside of the outboard spar bolt hole and out
in to the wing some 48"...again something hard to tell from a picture unless you
have seen it built or designed the wing!... There is absolutly no problem with
the use of a carbon structure use in conjunction with a fiberglass one and
i would be very leary of anything else that maybe
discussed by the earlier mentioned forwarded post......We all know what assuming
does for us and it is best to get information form the horses mouth....again
my opinion but we all have them..
Nick
georgiemun <georgiemun@yahoo.com> wrote:
Hey, no problem; I'm just trying to learn as much as I can about the construction
of the aircraft that I might be buying. I do have a question for Nick tho...
One that I asked earlier, but was overlooked.
Why does the carbon fiber stop at the root of the wing and does not continue through
to the tip of the spar? Is there a reason for this?
Also, it appears then that the spar is of a somewhat hollow construction with the
foam creating the cavity? I guess this is done to save weight for the a solid
wing spar is not necessary in this case?
Thanks for any clarification that you guys can give.
Kayberg(at)aol.com wrote:
> I undestand that when you make absolute statements you can be found wrong sometimes
Read this topic online here:
http://forums.matronics.com/viewtopic.php?p=92780#92780
---------------------------------
Food fight? Enjoy some healthy debate
in the Yahoo! Answers Food & Drink Q&A.
Message 4
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Subject: | Re: glass or carbon |
Thanks Nick for that detiailed explaination. While I do not understand all of
the technical ramafications, I appreciate you taking the time to help me understand
how the aircraft is put together.
pequeajim:
I will shoot you an email soon and then as you suggested, we can both go down to
Green Landings so I can see the aircraft in person and perhaps get a ride in
it too.
Georgie
Read this topic online here:
http://forums.matronics.com/viewtopic.php?p=92809#92809
Message 5
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Subject: | construction questions |
I have a few questions on the building of the Lighting.
1. Page 23-2 (rudder hinge installation) a picture shows the support on
the elevator below the mating bracket which is on the vertical fin. Does
the lower bracket also go below the its mating bracket?
2. The bearings for the brackets on the rudder are .650 in diameter. The
holes are .625. What has anybody addressed this so far?
3. When doing the firewall, you need to put a slight radius bend into
the edge all around. What tool have you used?
Thanks for your reply. TEX
Message 6
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Subject: | Re: glass or carbon |
And I stand corrected.
Thanks Nick
doug
In a message dated 2/4/2007 10:23:22 AM Eastern Standard Time,
vettin74@yahoo.com writes:
The wing spar is of fiberglass, carbon fiber, foam , and wood
construction.....the root end which is in the fuselage is 1/16 per laminet wood
core being
1" thick this stops at the wing root and is than a fibergalss foam woven
core... this mean the the foam core has woven fiberglass in it for more
strength....the wood is used as a high density light filler at the root end.....the
spar caps ar 1"by1" rolled unidirectional glass which tapers down to 1"by 1/2"
at the tip.....The material thru out the spar is heavier at the root end and
lightens up at the tip as to be expected....... yes there is a carbon fiber
laminte in the spar... this runs from just inside of the outboard spar bolt
hole and out in to the wing some 48"...again something hard to tell from a
picture unless you have seen it built or designed the wing!... There is absolutly
no problem with the use of a carbon structure use in conjunction with a
fiberglass one and i would be very leary of anything else that maybe discussed
by
the earlier mentioned forwarded post......We all know what assuming does for
us and it is best to get information form the horses mouth....again my
opinion but we all have them..
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