Gottlieb, Robert

English

NASA Technical Reports Server

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 
ORIGINAllY ISSUED 
September 1942 as 
Restricted Bulletin 
TESTS OF A STRESS-CARRYING DOOR IN COMPRESSION 
By Robert Gottlieb 
Langley Memorial Aeronautical Laboratory 
Langley Field, Va. 
PR~?ERTY OF JET PROPULSION LABORATORY LIBRARY 
C lIh;t1 NIA Ir~STITUTE r, F TECHNOLOGY 
WASHINGTON 
NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of 
advance research results to an authorized group requiring them for the war effort. They were pre-
viously held under a security status but are now unclassified. Some of these reports were not tech-
nically edited. All have been reproduced without change in order to expedite general distribution. 
L - 253 
https://ntrs.nasa.gov/search.jsp?R=19930092543 2020-06-17T01:14:45+00:00Z
- ------- - -~ - ----
r 
\ . 
NATIONAL ADVISORY COMMITTEE FOR AERONAUTIC S 
RESTRICTED BULLETIN 
TESTS OF A STRESS- CARRYING DOOR IN COMPRESSION 
By Robert Gottlieb 
The results of torsional tests on a monocoque box 
containing a stress-carrying door were presented in ref -
erence 1 . The present pRper gives the results of bending 
teqts On the same box with the door on the compression 
side . The det a ils of the box and the location of the ap-
plied forces are shown in figure 1. Outside and inside 
views of the stress-carrying door are shown in figure 2 . 
Vertical loads of 1000, 2000 , 3000 , and 4000 pounds 
were applied at the free end of thA box . The chord~ise 
stress distribution at station 27 . 75 (see fig . 1) is 
shown in figure 3 for th e Case of cut-out, cut-out with 
door, and no cut-out . 
The effective ne ss of a stress-carrying door depends 
on the intended function of the door . If the function 
of the door is considered to be th a t of reducing the 
ma x i~um com p ressive stresses around the cut-out, a meas -
ure of t he effectiveness of the door is the ratio of the 
stresses a/b. (See fig. 3 . ) If the function of the 
door is considered to be that of carrying load from one 
end of the cut-out to the other, a measure of the effec -
tiveness of the door is the ratio of the areas 
double - shaded area 
entire shaded area 
The entire shaded ~rea represents the lo a d - carrying ca-
pacity that wa s loot when the cut-out was made; the 
double-shaded a rea shows the ~mount of this load-carrying 
capacit y that was recovered 'hen the door was placed in 
the cut-out . 
In fi gu re 4 t hese two meaSlres of the effectiveness 
of the door in com p ression are plotted against the ap~lied 
10a& at the tin of the box. These curves indicate that 
thp door bec ~me s effActive in carryin g loads across the 
cut-out at a load of approximately 1500 pounds and that 
it becomes effective in reducin g stresses at a load of 
--- ---- - -- - -~~-~ 
I 
I 
I 
I 
_J 
L 
approxim~tely 2300 pounds. The effectiveness increases 
rapidly as greater loads are applied. The door is inef-
fective at low loads becausp of the clearance provided 
between the door and door frame to allow easy removal of 
the door at zero lo~d. Before the door can become ef-
fective in comnrpssion, thD material on each side must be 
deformed suffiCiently to take up t~is cle~rance. 
Langley Memorial Aeronautical La oratory, 
National Advisory Committee for Aeronauticis, 
Langley Field, Va. 
RE~EREN CE 
1. Gottlieb, Robert: Test of a Stress-Carrying Door in 
Shear. NACA R.B. I Aug. 1942. 
I 
-------------~ 
.!.. 1-~I{.\'J 
, 1: ~ 
.!.. S ~tr~ 1- tee/ cl
eq 
tQpe" Qt)Sle 
Pi t) . 
*{'·b ,.!. 
1-~.\'t" 
, ll .... 
:t:-I" "ecj ~ St". Q"91 
,Ii=' E> 
hl ~ Sfh. 
"P 
G 
'1-;0-
~ 
<:)0 
0 .... 
q,.-
0°+ 
A.PPlied 
fOrCe 
C"G--t"" ..... 
°0" 
S-~,j 
<:Y" 
~~0 
0" se 
</ 
Figure 1. - Details of box and stress - carrying door. 
~ . 
I~ecl 
~a 
'-
0+ 
'<> 
0"-
«( 
Stiffe 
"'e" oS 
NATIONAL ADVISORY 
COMMITTEE. FOR AERONAUTIC:: 
L-253 
e~d 
x 
~xXX xX x 
·)S i Flib 
1t, .. O6~ 
IC~ 
III : : ~~ 
-Q-J '(q~~ 
z 
» 
n 
» 
..0 
... 
I 
~ 
• 
l 
j 
. , 
___________ J 
Fig. 2 
• 
a: 
0 
0 
• 
0 
w 
0 • C!' w z 
I en 
0 
... 
)0-
f ::> 
en a: 
0 Z a: 
< 
0 
I 
• 
II) 
-
II) 
< 
-
w 
-
CD IS: 
...- ... 
(f) 
• C\J 
w 
a: 
J 
C!' 
u.. 

NACA 
C 
CT 
if) 
-........... 
.D 
... 
(/) 
if) 
CY 
L 
+-
if) 
2000 
o 
4000 
2000 
o 
(0000 
4000 
2000 
0 
8000 
(0000 
4000 
2000 
---
ij/~\ I \ 
I 
b I 
I 
/ 
I 
I 
Chord) in. 
2000 
-------
r, 
'I \ 3000 ...D 
" '\ Il.J 
" 
\J 
" 
L 
"-
.... 0 
-
.... 
.... 
'--t--
-............. 
-U 
Q) 
-
0.. 
0.. 
« 
4000 
--- No cut-out 
-- Cut-out 
- - - - Cut-out with door 
Figure, J . - Chord wi se. -stress distr ibution ot station 27 15. 

'NACA Fig . 4 
o Loa d- carrying eff ectivenoss -I---- f-, 
.4 ---I " I str+_redLng K --+--
~ ·-r --Gff ectivon oss :::-.: - -+-+---1 
. 3 ~ _ _ L' 
(/J I I ~ I I 
.:: I i 
~ 1 - -1---- I --- ---
~.2 c-- -r-+--~t--~-. +--+-/ 
.l -_-!_+_!I ___ ~--I--
1 I )J ~. -J--t--I-t--
. I i / I 
i !/ : 
o ·--6--JL-_&--L-....L-_ --LI __ L-_ _ -...J 
o 1000 2000 3000 4000 
I 
Appli ed forc e , Ib 
Figur a 4. - Effec tivenes s of door. 
1 


Tests of a Stress-Carrying Door in Compression

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server