1/7th F-14D Scratch build thread *building started*
06-20-2013, 02:42 PM
#1128
RE: [Deleted]
ITS HERE!!!!!!!!
3lbs even once the flashing was trimmed off! And it has already been stress tested and been shown to support 200lbs positive and negative forces. (I put either end on a chair and SAT on it with my feet off the ground!). I will post the video on youtube later to prove it!
Also, the stress testing was continued as well. What better way to stress test something than to give it to a two year old! Lol
I have no concerns about this wing not being strong enough. Matter of fact, i am pretty confident i can get it 1/2 to 3/4 of a pound lighter while still maintaining the same strength.
3lbs even once the flashing was trimmed off! And it has already been stress tested and been shown to support 200lbs positive and negative forces. (I put either end on a chair and SAT on it with my feet off the ground!). I will post the video on youtube later to prove it!
Also, the stress testing was continued as well. What better way to stress test something than to give it to a two year old! Lol
I have no concerns about this wing not being strong enough. Matter of fact, i am pretty confident i can get it 1/2 to 3/4 of a pound lighter while still maintaining the same strength.
06-20-2013, 11:48 PM
#1133
RE: [Deleted]
Looking good Thomas. As John said, the real load test will be the one with the full airframe loaded with sand or flour bags.
You'll probably need to load her up to 350 lbs for a 6 G test...
You'll probably need to load her up to 350 lbs for a 6 G test...
06-21-2013, 12:05 AM
#1134
RE: [Deleted]
ORIGINAL: invertmast
The primary wing spar is NOT the big piece of wood you see going around the aluminum bearing holder. Matter of fact, if you take one molded wing skin (just a top OR bottom), the primary wing spar is already in the wing skin.
The primary wing spar is NOT the big piece of wood you see going around the aluminum bearing holder. Matter of fact, if you take one molded wing skin (just a top OR bottom), the primary wing spar is already in the wing skin.
Just a quick vocabulary consideration.
The primary wing spar is not the carbon fiber you have moulded into the wing neither.
The spar is a beam structure with horizontal plates ( carbon in the skin ) and vertical webbing ( balsa core ). The vertical webbing is as important as the horizontal plates.
You did it extremely well by the way, with proper thickness/ grain of balsa core. This is where most Chinese manufacturer fail to understand the concept of beam structure. They either fit a honeycomb collapsible webbing ( useless ) or horizontal grain balsa ( a bit better ).
At rupture effort, it is always the webbing that fails in compression first. This is why it is so important to address correctly, which you have done.
08-09-2013, 12:15 PM
#1144
Peter,
that makes two of us! Unfortunately, I leave sunday for 7-10 days for work, then as soon as I get back, i Have a Horten to infuse and join for a customer.. AND we have to start packing for a 1000 mile move. So it will probably be 2-3 months before I get around to using this stuff..
that makes two of us! Unfortunately, I leave sunday for 7-10 days for work, then as soon as I get back, i Have a Horten to infuse and join for a customer.. AND we have to start packing for a 1000 mile move. So it will probably be 2-3 months before I get around to using this stuff..
08-28-2013, 11:23 AM
#1145
I got a photo of the prototype main landing gear rim front half sent to me by a company providing me with some samples of these parts.. As you can see, the detail is amazing, I am very pleased with the look, as these as Dead on perfect when compared to the late model F-14 tomcat main rims:
08-28-2013, 10:05 PM
#1149
Can't wait to see the whole package, but I'm eager to see the whole wing sweep mechanism with related videos!!!!!!!
09-12-2013, 06:36 PM
#1150
If you have ever wondered what it would be like to take the top fuselage skins, one wing panel, and a pair of vertical stab skins off a F-14 and lay them flat on a table, here ya go.
About 6 hours of work to get to this point, but all of the airex templates are made and ready for cutting out of plastic for the top fuselage, vertical fins, and one wing panel.
I still have to do the bottom fuselage templates, flaps, slats, gear doors, 2nd wing panel and horizontal stabs.
Then they all have to be cut from the plastic. AND then I get to do it all over again with fiberglass and carbon fiber layers.
About 6 hours of work to get to this point, but all of the airex templates are made and ready for cutting out of plastic for the top fuselage, vertical fins, and one wing panel.
I still have to do the bottom fuselage templates, flaps, slats, gear doors, 2nd wing panel and horizontal stabs.
Then they all have to be cut from the plastic. AND then I get to do it all over again with fiberglass and carbon fiber layers.