>From (with a bit of rewording and symbol changing for ascii sake)
Designation: F 2245 - 04
Standard Specification for Design and Performance of a Light Sport Airplane
the load factor for the wheels (nf) is
nf = (h + d/3) / (ef * d)
where h = drop height in inches = 3.6 * sqrt( W/S) with W/S in lbs per
square feet, but h must be larger than 9 inches
d = total shock absorber travel in inches = d tire plus d shock
ef = shock efficiency
(ef * d) = 0.5 * d for tire and rubber or spring shocks or
= (0.5 * d tire) + (0.65 * d shock) for hydraulic shock
absorbers
5.8.1.2 If nj is larger than 3.33, all concentrated masses (engine, fuel
tanks, occupant seats, ballast, etc.) must be substantiated for a limit
landing load factor of nj + 0.67 = n which is greater than 4.
5.8.1.3 The usual ultimate factor of safety of 1.5 applies to these
conditions, unless a drop test from the reserve energy height, hr = 1.44h,
shows that a lower factor may be used. If the shock absorber is of a fast
energy absorbing type, the ultimate loads are the limit load multiplied by
the conservative reserve energy factor of 1.2.
--
Wesley Scott
Bryan, TX
k...@spottedowl.biz
>
> Message: 2
> Date: Fri, 3 Feb 2006 23:13:58 -0600
> From: "Larry H." <lah...@yahoo.com>
> Subject: KR> LANDING GEAR
> To: "KRNET" <kr...@mylist.net>
> Message-ID: <005f01c62949$cfa6e2d0$6f01a8c0@boss1>
> Content-Type: text/plain; charset="Windows-1252"
>
> Anyone know what the standard g rating drop test for certified aircraft
is? Height ? + Weight? = ? g/s or what ?
>
> Anyone had success with main landing gear, other than the Diehl
fiberglass? If so what did you use, what dimensions and how many survived
hard landings?
>
> Thanks
> Larry H.
