close

Вход

Забыли?

вход по аккаунту

?

Патент USA US2407481

код для вставки
_ Sept. 10, 1946.
-
A, G, DEAN
2,407,480
AIRCRAFT FUSELAGE AND WING CONSTRUCTION
I Filed Sept. 13, 1944
3‘Sheets-Sheet l
I‘PIG.
IN VEN TOR.
Albert G. Dean n
BY
Wm Pfmw'
ATZfQR/VEY
Sept. 10, 1946.
. _ A__ G, DEAN
I
2,407,480
;
AIRCRAFT FUSELAGE AND WING fCONSTBUC'I'JéON '
I Filed Sept. 13,‘ 1944
s Sheéts-Sheét_ _2
‘
p‘ 2.
IINVENTOR
Albert G. Dean
BY
>
‘
,
‘
ATTORNEY
v.
~ Sept. 10, 1946.
2,407,480
- A. ca. DEAN
AIRCRAFT FUSELAGE AND ,wme co?swrtuc?on
SSheeis-Sheet 5
> Filed-Se?. 1a, 1944
p m. >w
INVENTOR
Albert G. Dean
BY
41516.5
.
FIG. 6
I
-
ATTORNEY
2,407,480
Patented Sept. 10, 1946
‘UNITED’ STAT Es‘, PATENT
OFFICE _
2,407,480
AIRCRAFT FUSELAGE AND WING Y
CONSTRUCTION
v'
Q
- " Albert G. Dean, Narberth, Pa., assignor tov’The
'
Budd Company, Philadelphia, Pa., a corpora
tion of Pennsylvania
7 Application September 13, 1944; Serial No. 553,890
'2 4 Claims. (01. 244-419)
1.
in this art.
on the line ‘l0—l0 ofFigure 1.
they are secured to the side‘bulkheads 3 which
constitute parts of a strong girdle surrounding an
open cargo compartment 4. ‘The girdle also com
ment upon that disclosed in the copending appli
'
prises an upper or roof girder 5 and a lower or
?oor girder 6.
skin blankets ‘I, 8 and Srespectively. The string
ers of the top and bottom-blakets are through
which constitute the full sides of body girdles and 2
are secured.
There the bulkheads are formed
each by a ?at sheet of metal together with
?anges and stiffening struts which» are welded
thereto; in thepresent construction the bulk
heads are formed by one or a laminated pair of
pressed full-size elements which include inte
gral ?anges and stiffening struts.
There the
.spar web was secured to the bulkhead web by a
splice plate; here the spar web isdirectly over
The, top, sides,‘ and bottom of
10 the fuselage are covered by stringer-reinforced
In the present, asin the former construction,
there are a number of ‘bulkheads ‘(?ve shown)
to which the spars and skin blankets of the wings
_
secured to the sides of a fuselage 2v. Speci?cally
‘
tion.
-
The , airfoils or wings I of the aircraft are
The presentinvention constitutes an imp-rove- v
cation of Michael Watter and Albert G. Dean,
Serial Number 492,494, ?led June 28, 1943, and
assigned to the assignee of the present applica
2
Figure 10 is an enlarged vertical section taken
. ''This invention relates to aircraft; particularly
‘to airfoil-to-body connections for aircraft,jand
has for an object the provision of improvements
running, while those "of the sides are intercostal
between the several bulkheads. The ?oor is des
ignated by the numeral W. The fuselage sections
are reinforced and joined by pairs of .mating
longerons II on the corners.
'
,-
'
The wings comprise spars [2 each including a
sheet web 13, chords or cap strips l4 and sti?en
ing struts [5. The wings are covered ‘by stressed’
'20 stringer-reinforced skin blanketsl? which be
tween the spars are directly connected through
certain stringer ends or splicers to the interme
diate bulkheads. These projecting stringers or
lapped with the ,web or webs of the, bukhead.
There the upper and lower ends of the‘bulkhead 25stringer splicers correspond to and are connected
like the spar cap strips illustrated and described
were connected by splicing gussets'to the girdle
girders; here the ends of the monolithic bulkhead ‘ herein, hence'the, stringer connections need not
be described in detail. This analogy is evident
are'extended to overlapfthe ends of the girders
fronr the copending application. referred to.
to which they are secured. ‘
' .7
Over and above these speci?c improvements 30 Upper fairing strips l1 and- lower fairing strips
[8 close the space between wing and fuselage
the present invention provides various other
improvements in detail which will be evident
The upper girder ,5 (Figure 3) comprises a plate
from the following description ofan exemplary
web‘ I9 and cap strips 20 and may be formed as a
embodiment thereof, reference‘ being made to
channel-section member with integral web and
the accompanying drawings, wherein:
cap strips or ?anges.
~ Figure l is a transverse section through
The bottom girder ,(Figure 10) comprises a
aircraft fuselage and wings'in the connecting
plate web 2| andcap strips 22.
'
,
‘ ‘
bulkhead region, one of the wings being shown
Each‘ bulkhead comprises a monolithic pressed
in preassembly position;
7
p
‘
r '1
plate having a plate web 23‘ and'edge ?anges 24.
‘Figure 2 is a side elevation of a single pressed 40 Preferably‘ two mating plates are provided and
bulkhead sub-assembly alone;
welded together. The edge flanges are discon
Figure 3 is an enlarged vertical section taken
tinued where the spar cap strips Ill overlap and
on the line 3—3 of Figure 1;
at the upper and lower laterally projecting ends
Figure 4 is an enlarged inclined section taken
25, 26 respectively, where the ends of girders 5
on the line 4-4 of Figure 1;
45
and
6, respectively, overlap.
Figure 5 is an enlarged inclined section taken
On the outeror tension side the bulkhead
on the line 5-5 of Figure 1;
plates may be left ?at within the edge ?anges,»
Figure 6 is an enlarged vertical section taken
but on the compression side they are preferably
on the line 6—6 of Figure 1;
‘
Figure 7 is an enlarged horizontal section 50 pressed out to form wales or ridges. 21 which form
a hollow box section between them. If the side
taken on the line ‘l---'! of Figure 2;
edges are left in spaced relation they may be
Figure 8 is an enlarged horizontal section taken
connected by an edge cover plate 28, which itself
on the line 8-8 of Figure 2;
may be corrugated, as at 29.
'
Figure 9 is an enlarged horizontal section taken
The bulkhead plates are; strengthened and
on the line 9-9 of Flame 1; and
blankets.
>
c
->
'
2,407,480‘
3
4
stiffened by forming transverse pressed strut
like wales or ridges 30 in them, the matching
wales of the paired plates forming box sections
between them.
been illustrated by Way of example, it is to be
understood that there may be various embodi
ments within the limits of the prior art and the
If desired, the metal may be cut
out between the wales for lightness, leaving a
scope of the subjoined claims.
5
triangulated skeleton between the tension and
What is claimed is:
1. An airplane comprising a generally triangu
lar pressed metal bulkhead element with edge re
compression sides. At places where the wales
are omitted from the strut-like connections the
inforcing portions and intermediate triangu
angle strips, such as the spar cap strips I4, which
lated reinforcing hollow rib portions, the edge re
are welded in overlapping relation to the strut 10 inforcing portion being omitted at certain places,
connections serve the same purpose as the wales.
and wing and girder elements connected in shear
Figure 3 shows the connection between the pro
to said bulkhead element, said wing and girder
jecting end 25 of the bulkhead plates 23 and the
elements being overlapped with the sides of said
web I9 of the top girder. The edge ?anges 24
bulkhead element where the edge reinforcing
are omitted at the top of the bulkhead plates and
portions are omitted and some of the overlapped
the upper spar (or wing blanket stringer, as the
elements constituting part of the triangulated
case may be) chord i4 is run through along the
reinforcing portions of said bulkhead.
upper edge of the bulkhead and overlaps the end
2. An airplane comprising a‘body girdle formed
of the girder.
-.
of top and bottom girders and side bulkheads,
Figure 4 shows the connection between the end 20 said bulkheads being formed of mating ?anged
of the spar web [3 and the bulkhead plates, the
and ribbed plates secured together to form box
web being sandwiched between the plates where
section ribbed reinforcement. on one side edge of
spread apart at joggles and welded to them.
the bulkhead and at intervals across its width
Figure 5 shows a typical bulkhead strut Wale
and also oppositely directed lateral edge ?anges,
N) UK
certain of said body girders being overlapped with
plate material. This bulkhead shape is quite
clearly shown in Figure 2.
Figure 10 shows the connection of the bulkhead
to the bottom girder, the web 2| and cap strips‘ 40
22 being overlapped and welded to the webs 23
of the bulkhead plates. The girder end extends
well back of the laterally protruding end portion
and also oppositely directed lateral edge ?anges,
certain of said body girders being overlapped with
ments and triangulated integral strut elements
and also oppositely directed lateral edge ?anges,
certain of said body girders being overlapped with
section.
'
Figure 6 shows the connection between the
and secured in shear to said bulkhead, wing cap
lower spar (or blanket) chord l4 and the webs
strips overlapped with and secured in shear to
of the bulkhead plates. Here the chord I4 is
said bulkhead, and a wing spar web plate over
strengthened by a nesting angle-section splice
lapped with and secured in shear to said bulk
strip which may be considered as part of it.
>
30 head.
Figures '7 and 8 are typical transverse sections
3. An airplane comprising a body girdle formed
through the bulkhead.
of .top and bottom girders and side bulkheads,
Figure 9 shows the bulkhead in section just
said bulkheads being formed of mating, ?anged
above its lower end, indicating how the wales on
and ribbed plates secured together to form bOX~
the compression side and .the corrugation in the
section ribbed reinforcement on one side edge of
edge cover strip 28 have run out to leave ?at
the bulkhead and at intervals across its width
and secured in shear to said bulkhead, wing cap
‘strips overlapped with and secured» in shear to
said bulkhead, and a wing spar web plate over
lappedv with and secured in shear to said bulk
head, said spar web plate being sandwiched be
26 to form a connection with the main body of
tween the webs of the mating bulkhead plates.
the bulkhead web. This is well illustrated inwfs. , 4. An airplane comprising a body girdle formed
Figures 1 and 9.
of top and bottom girders and side bulkheads,
It is thus seen that the invention provides a
said bulkheads being formed of mating, ?anged
very simple and light but strong and dependable
and ribbed plates secured together to form box
wing-to-body construction. The one-piece tri
section ribbed reinforcement on- one side edge
angular bulkheads with integral edge reinforce 50 of the bulkhead and at intervals across its width
provide a very rigid connection. The structure
of the bulkhead and its connection with the spar
chords and web and with the ends of the girders
are also of a simple but highly e?icient charac
ter. In a light airplane construction a single
bulkhead plate may be used, or lighter laminated
plates, but in larger airplanes the laminated con
struction with oppositely ?anged and box section
elements is very e?‘ioient.
so
While one embodiment of the invention has
and secured in shear to said bulkhead, wing cap
strips overlapped With and secured in shear to
said bulkhead, and a wing spar web plate over
lapped with and secured in shear to said bulk
head, said bulkhead also including an edge cover
plate secured to the ?anges on the side having
the ribbed reinforcement.
ALBERT G. DEAN.
Документ
Категория
Без категории
Просмотров
0
Размер файла
429 Кб
Теги
1/--страниц
Пожаловаться на содержимое документа