close

Вход

Забыли?

вход по аккаунту

?

код для вставки
Dec. 3l, 1946.
R. A. woLF ETAL
SEAL FOR AIRCRAFT CONTROL RODS
Filed Aug- 15.1942
2 Sheets-Sheet 1
mgl,
@G1435
WM
4
De¢.'31, _1946.
R. A. woLF Er Al.
_
2,413,671»
SEAL FOR AÍRCRAFT CONTROL RODS
Filed Aug. 1:5, 1942. `
` 2 sheets-snee; 2'
A 48
Y
NEYS
lilìtll
Íâatented Dec. 31, 1946
UNITED STATES PATENT-OFFICE
2,413,671
SEAL FOR AIRCRAFT CONTROL RODS
Robert A. Wolf and Herbert'L. Bowers, Kenmore,
N. Y., assignors to Bell Aircraft Corporation,
Buffalo, N. Y.
Application August 13, 1942/, Serial No. 4545630
2 Claims. (Cl. 286-15)
l
2
c
.
Fig. 3 is a cross sectional view through an air~
This invention relates to improvements in air
craft body and control structure.
craft wall showing a modified form of sealing
means in elevation; and
In aircraft constmction it is necessary to ar- ‘
range control means in such fashion that they
Fig. 4 is a fragmentary, longitudinal cross sec~
may be manipulated from within the aircraft
to accomplish control functions exteriorly there~
of. To this> end it is required that certain por
tional View through the right-hand end of the
sea-ling means of Fig. 3.
Like characters oi reference denote like parts
throughout the several iigures' of the drawings
and in Fig. -1- the numeral lil designates a portieri
tions of the control means extend through the
aircraft wall' structure in such fashion as to be
movable with respect tov such wall. In aircraft
designed to be used at high altitudes= or under
anyl conditions where the atmosphere is sufñ
ciently rariiied as to require the maintenance of
of an- aircraft wall and numeral It indicates a
control element extending therethrough. The
opening of the wall lll through which the control
element Il extends (not shown) is- considerably
>larger than the. control element itself.
a pressure higher than that of thesurrounding
atmosphere within the -aircraftbodu the problem 15 A collar I2 is disposed against the inner side
of the wall Il) and has -av basey flange ,-l-S which is
'riveted to the wall' or otherwise secured in fluid
tight relation. A ilexible tube lél- has one of its
of extending control means through the wall of
the aircraftA body is complicated by the necessity
for preventing fluid passage thereabout.
The »present invention provides an arrangement
- ends disposed about the outer end ci' the collar
l2 and may» be secured in position by a conven
whereby aircraft control means may be projected
' tional hose clamp iii, or the like.
through the-wall of an aircraft-fuselage or other
The opposite endy of theI tube' it’ is disposed
body portion in such fashion as to insure against
about a collar Il and. a second hose cla-mp lli-- is
ñuid leak through such wall, while at the same
providedv for maintaining» the' proper assembly'.
time providing- a» construction affording- the ut
most in ease, sensitivity and facility of move 25 If desired, the collars l2 and l? may be formed
with peripheral ridges as at t9, to insure against
ment- of the control element. It is desi-red' that
axial displacement of the parts; rIfhe coliar il’
such control element be movable both axially to
has inner annular formations for receiving and
and fro in said wall and bodily about» axes ap->
seatinga pair of` spaced annular bearing elements
proximately in the plane of the aircraft wall. It
is4 further desired ythat thevv control element be 30 20 and 2l having clamped therebetween a. sealing
assembly designated generally 22. The bea-rings
freely rotatable about its own-l axis;
2|l`»and 2|»y and., the sealing assembly 22 are re
According tothe present invention the sea-lling
tained inthek collar I-lby a screw-threadedv gland
element'which prevents fluid passage through the
231
aircraft wall at the point oi control emergence
is so arranged as not to be subject to loads or 35
As-appears fromr'g». 2, the sealing assembly
comprises a pair of complementary annular cage
deiiections of any sort, regardless oi the kind of
elements 2e, and 25 whichl retain a flexible an
movements or forces which may be applied to
nular ring 2t which may be of a material having
the control element itself.
the characteristics of leather or rubber. It wili be
Several forms of the improved aircraft control
supporting and wall-sealing structure are shown 40 noted that the inner portion of the sealing ring
26 is disposed obliquely against the `control ele
and described in detail herein but it is to be un
ment Il and the desired form of the sealing
derstood that various mechanical modiñcations
element 26 is insured by the presence of an en- are within the province of those skilled in the
circling coil spring, 2l.
art and that the invention is not to be consid
It will be noted from the foregoing that the
ered limited otherwise than as defined in the 45
bearing elements 20 and 2l insure permanent and
appended claims.
accurate concentricity as between the collar ll
In the drawings:
and the control element il. At no time can ma
Fig. 1 is a fragmentary cross sectional view
nipulative forces applied to the control element
through an aircraft body wall showing a control
Il dellect or in any other way affect the sealing
element extending therethrough and one form
relationship of the flexible annulai- element 26.
of the improved’ means forJ supporting the control
In the form shown in Figs. 1 and 2, the tube ffl
element and sealing the aircraft wall;
is formed of rubber or the like and has embedded
Fig. 2 is a fragmentary, longitudinal cross sec
therein a helical coil spring the convolutions of
tional view through the left--hand portion of the
Àwhich appear at 30 in Fig. 2. The spring 3e
sealing means of Fig. 1;
2,413,671
prevents collapse of tube I4 due to fluid pressure
forces exerted against the exterior surface there
of. In the form shown in Fig. 2 the tube I4 is of
increased thickness at the convolutions of spring
33 as indicated at 3l.
ing the aircraft body will urge the inner periph
ery of the sealing rings into more intimate sealing
contact with the surfaces of the associated con»
-
In the form of the invention illustrated in Figs.
3 and 4 the control element sealing means is
functionally the same as in Figs. 1 and 2, the
chief diiîerence being in the structure of the
ñexible tube, designated generally by the numeral 10
35 in Fig. 3. In Fig. 3 the numeral 31 designates '
an aircraft Wall portion and numeral 38 desig
nates a control element in the form of a shaft
having operative connection with an arm 39 dis
posed outside the aircraft body.
15
Here, again, the opening in the wall 31 is not
shown but is considerably larger than the control
trol elements.
We claim:
1. An aircraft structure comprising an aircraft
wall having a control aperture formed therein,
an elongated control element disposed Within
said aperture and adapted to have a limited
amount of movement in substantially all direc
tions, said aperture being of a size considerably
greater than the size of said element whereby the
latter may be free to have unrestricted iioating
movement within said aperture, an elongated flex
ible tubular member ñxed at one end to said Wall
in registration with said aperture, said member
projecting only forwardly from said aperture and
having an inner diameter substantially equal to
the diameter of said aperture, sealing means
spaced from said wall and carried by the end oi
said member which is remote from said Wall, said
means comprising packing means in sealing en
gagement with said member, and bearing iianges
carried by said tubular member independently of
said packing means and axially spaced from each
other and from said packing means for support
ing said element centrally Within the remote end
of said tubular member and for relatively guiding
said element in its reciprocating movement
therein.
parts which are to extend therethrough. Over
such opening at the inner side of the Wall 31
there is a collar 40 which is secured to the aircraft 20
wall 31 by means of a base flange 4I which in
this instance seats against the outer surface of
the wall 31. In Figs. 3 and 4 numeral 43 desig~
nates a collar which is the counterpart of the
collar l1 of Fig. 2 and which is connected to the
collar 40 by a tube section 43 having ears 43 at
its opposite ends for pivotal connection with com
plementary ears 41 and 48 formed on the collars
43 and 43, respectively. Pivot pins 50 provide
articulated connection between the collars 43 and 30
43 and the tube section 45 and the joints therebe
2. An aircraft structure comprising an aircraft
tween are sealed by ñexible sleeves 53, each of
wall having a control aperture formed therein,
which has an intermediate annular accordion
an elongated control element disposed Within said
pleated portion 54, to permit free articulation of
aperture
and adapted to have a limited amount
the joints between the collars 43 and 43 andthe
o1“ movement in substantially ali directions, said
tube section 45. The opposite ends of each sleeve
aperture being of a size considerably greater than
53 are disposed about the collars 40 and 43 and
.
the
size of said element whereby the latter may
the tube section 45 and may be secured by means
be free to have unrestricted ñoating movement
of conventional hose clamps 51.
The collar 43 isy stepped and formed at its inner 40 within said aperture, an elongated flexible tubular
member ñxed at one end to said wall in registra
periphery to receive a pair of spaced annular
tion with said aperture, said member projecting
bearing elements 63 and 3| having a fluid sealing
only forwardly from said aperture and having an
assembly 62 engaged therebetween. A screw
inner diameter substantially equal to the diame
threaded gland 63 is provided for retaining the
ter of said aperture, sealing means spaced from
bearings 60 and 6| and the sealing assembly 32.
said Wall and carried by the end of said member
The fluid seal of Fig. 4 is the same as that of
which is remote from said Wall, said means com
Fig. 2 save that a resilient ring 34 is provided
prising a collar secured to and in sealing engage
for giving shape to a flexible sealing ring 35 and
ment within said member, packing means car
for urging it into sealing engagement with the
ried by said collar, and bearing ñanges secured
control element 33.
in said collar independently of said packing
It will be noted that in both forms of the in
means and axially spaced from each other and
vention the inner portion of the annular sealing
from said packing means ior supporting said ele
rings 26 and 35 are directed obliquely along the
ment centrally` Within the remote end of said
control elements Il and 33, respectively, in a
tubular member and for relatively guiding said
direction toward the interior of the aircraft body.
element in its reciprocating movement therein.
By virtue of this construction, fluid pressure with
ROBERT A. WOLF.
in the aircraft body in excess of those surround
HERBERT L. BOWERS.
Документ
Категория
Без категории
Просмотров
0
Размер файла
380 Кб
Теги
1/--страниц
Пожаловаться на содержимое документа