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Патент USA US2406560

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Agg. 27,1946.-
w. B. POPE
ROCKET MOTOR
Filed Dec. 30,' 1943
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IN VEN TOR
Winslow ß. pope .
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A TTORNE Y
Patented Aug. 27, 1946
- 2,406,560
UNITED STATES PATENT OFFICE f
ROCKET MOTOR
Winslow B. Pope,I Detroit, Mich., .assìgnon
by mesne assignments, to United States of
America
.
Application December 30, 1943, Serial No. 516,155
9 Claims. (Cl. 60-35.6)
2
1
mating rearwardly extending axial portions taf
pers radially inwardly from .the rearward edge
This invention relates to rocket-propelled de
vices, more particularly to improvements in the
design and construction of what may bertermed
the rocket motor.
\
thereof for a portion of its axial extent to pro
vide the conical face Il‘,vand at the portion. I8
,
between the face I‘I and the forward axial por
tion I5 is outwardly recessed. The casing is
The primary object of the present invention
is to provide a simplified arrangement for con
taining the propelling charge of a rocket-pro
pelled device and for forming the pressure de
provided with circumferentially spaced aperturesY
I9 through its Wall which open into the space or
Another object is to provide a casing and jet
arrangement which is so designed as to-.permit
chamber 20 deñned by the axial portion I5, the
forward edge of the face I1, the wall I8 andthe
tube I3. The tube I3 at the rearward side of
the apertures I9 and surrounded by the face
manufacture by lsimple machine turning opera
tions, and which is adapted for rapid assembly.
Il is tapered at 2l in the same direction as the
face I'I. ’I'he face I'I and wall I8 of the ele
veloping jets, which arrangement is particularly
adapted for quantity production.
A further object is to provide an improved 15 ment I-4 together with the face ¿2| of the casing
I3 thus form a Venturi passage which is in com,
munication with the interior lof the casing I_3
. With the above and other objects in view,
through the apertures I9.
which will be apparent from the vfollowing de
In the construction shown in Figure 2, the Vior
scription to those skilled in the art t0 which the
invention appertains, the present invention con 20 ward axial portions I5 of the half-sections .I4a
are >each formed with a radially inwardly extend
sists in certain features of construction and com
ing locking ridge 22 which when assembled on
binations of parts to be hereinafter ldescribed
the casing I3 snugly fits in a circumferential
with referenceY to theaccompanying drawing, and
groove 23 in the outer surface of the casing I3,
In the drawing which illustrates suitable -em 25 locking the half-sections against axial movement
relative to the casing I3. The two half-sections
bodiments of the invention,
multijet arrangement for rocket-propelled devices.
then claimed.
‘
,
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'
f
IdaI are provided in their external faces sub
stantially in transverse alignment with the ridges
Figure 1 is a longitudinal view of a rocket
propelled device in which` the features of the pres
with aligned grooves 24 which receive an end
ent invention' are incorporated;
Figure 2i is an enlarged sectional view of the 30 less locking ring 25. The locking ring 25is shrunk `
into the groove 24 in substantially the same man
charge-containing casing;
.
ner as a rotating band is applied to a shell, and
Figure 3 is a transverse section of the stabiliz
ing unit, taken substantiallyon Aline 3-3 of »Fig
when shrunk into place securely clamps the half
ure 2; and
sectîons Ida about the casing I3.
»
I
~
Preferably, in order to provide for tightñtting
engagement of .the half-sections with .the tube
ingmodi?led Venturi arrangements. _
I3, spacing shíms 26 are provided between the
Referring to the drawing, particularly to `Fig
mating portions of the half-sections Illa.
ures 1 and V2, the arrangement of the present in
The stabilizing element 42'I Vcomprises. `a plug
vention comprises a tubular element lIIl secured
through a threaded connection II at its forward 40 23 threaded into the rearward end of the casing
I3 and having a shouldered portion .29 to which
end to the device I2 to be propelled. The device
Figures 4 and`5 are fragmentary sections show
35
a plurality of radial sheet metal stabilizing -varies
3D are welded, the vvaries being surrounded by
I2 may consist of an explosive projectile, a chemi
cal or ñare device or any other device desired
vto be projected through space.
tightly fitting sheet metal ring 3l' which holds
.»
The tubular element; I0 embodies a tube I3 45 the same against deflection.
The >propelling charge is in the form of a plu
internally threaded at its rearward end Aand one
rality of .axially aligned annular .combustible ele
or more surrounding jet-forming elements I4,
depending upon the numberr of> propulsion jets
mentsy .32 separated by spacers 33, the group of
desired.
elements 32 being mounted on a headed rod 34
Y
Each jet-forming element I4'is comprised of 50 and arranged within the casing I3. The rod
34 is threaded into a boss-like projection V35 form
two mating semi-circular half-shells Ma -each
having a forward axial portion I5 engaging the ` ing an axial .extension of the stabilizer plug .28.
Inasmuch as the means for igniting the propel
' tube I3 and a rearwardly extending axial p_ortion
ling charge forms no part of the present inven
IS circumferentially spaced from the tube I3.
TheY inner circumferential face formed bythe
55
tion, the same is „not shown in the drawing.
. aéoaseò
4
the Venturi wall 3| directly in the casing i3, this '
half-sections about said casing at said one side,
said sections and the casing at said one side hav
ing interñtting circumferential ridge and groove
wall, designated 2Ia, is formed by the outer face
of an annular- ring .42 `shrunk into position on the
portions.
4.y Ay tubular casing for a'rockÍet-propelled de-V
casing I3, the ring 42'and casing ~having inter-V
vice, adapted to‘contain‘ a' combustible propelling
locking ridge and groove portions 43 and`44, rel- .
spectively. The wall 2 I a is machine tapered
after the ring 42 is shrunk into position.
.
axially divided to provide semi-circular half
sections, and means for securely clamping said
In the modiñed construction of Figure 4, the
ridge 22 and groove 23 are reversely arranged.
Also, instead of machining or otherwise forming
charge and having in a circumferential zone at
10 least one aperture through the Wall thereof for
"
discharging from the interior thereof gases re
In the modified construction shown in Figure _5, l
the element I4 is in the form of a single-piece l
sulting from the burning of the propelling charge,
annular >member surrounding said casing and
by
ring
suitable
slippeddowels
over the
45 extending
casing I3V therethrough'into
and held in place " ‘ - an
closely fitting said casing at one side of said Zone
and extending from said one side axially over and
apertures provided in the casing I3. The 'smaller ‘
ring 42 may also be held in position by Similar.` __ substantiallybeyond said Zone in circumferen
tially spaced relation, said annular member being
dowel-s 46.
`
axially divided to provide semi-circular half
It will ybe obvious from the drawing and the `
sections, said _sections having Acircumferential
I foregoing description that the tube I3 and Ven- .
grooves in the'e'xternal Walls thereofl each cir
turi-forming elements .I4 can »be easily lformed ~
cumferentially aligned with the other, and a con
from tubular stcckby simple machine turning
tinuous. shrunk-in band in said aligned grooves
. operations and are so designed as to facilitate as- 1
clamping said sections about said casing at said
l sembly operations, all of which provide for rapid
.
quantity'production.
’
one
.
side.
.
.
I
`
g
5. A tubular casing for a rocket-propelled de
Y n will be obvious to those skilled in the art to
Í ¿which the invention appertains that various
vice, adapted to contain a combustiblel propelling
l changes maybe made in the detailed construction
charge and having in a circumferential Zone at
Vleast one aperture through the Wall thereof for
discharging from the interior thereof ygases re~
g 'and arrangement of parts Without departing from
1 the spirit and substance of the invention, the i
l Scope of which is defined by the appended claims. 30 sulting from the burning of the propelling charge.
What is claimed is:
.
an annular member surrounding said casing and
closely ñtting »said casing at one side of said zone
and extending from said one side axially over and
.f
¿1. A tubular casing for a rocket-propelled de
Í
l
`
l
`
vice, adapted to contain a combustible propelling
charge andl having in a circumferential zone at
least one aperture through the Wall thereof for
discharging from the interior thereof gases re-~
sulting from’the burning of the propelling charge,
`
\
Y substantially beyond said Zone in circumferential
35
j
1
ly spaced. relation,v said annular Vmember being
axially divided to vprovide semi-circular half
sections, and means for securely clamping said
and means associated with said casing and form
half-sections about said casing at said one side,
l ¿ing therewith an axially directed annularpropul
said casing in the circumferential region` at the
sion jet, said means comprising a pairof semi 40 other side of said zone, and the circumferential
circular shells iittingv together about said casing . 'portion of Athe innenwall of said annular member
` to form a continuousl ring-like element having an `
3 vaxial extent including .said vapertured zone'and
regions of substantial'axial extent vat each side
î Vof said Zone, said shells beingcircumferentially
Y
Aspaced from the ca'singbeing contoured to pro
vide an annular Venturi passage.
v »
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V6. A'tubulary casing fora _rocket-propelled de
vice, adapted to contain a combustible propelling
charge and having in a circumferential zone at
3 spaced from-both said apertured regionand one i
Aof said side- regions and closely engaged with said
i ‘casing -at theï other sideregion, vand means for
least one aperture through the Wall thereof for
clamping ï saidshells about said casing >at said
sulting from the burning of the propelling charge,
f
ïother side region.
'
Y
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»
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discharging from the interior thereof Vgases re- .
van annular member surrounding said casing and
Y
g -vice, adapted to contain acombustiblepropelling i
closelygñtting said, casing at one side ofY said
zone and extendingvrfrom. said one side axially
ì charge and having in a circumferential zone at
over and substantially beyond said Zone in cir
.- f 2. A tubularr casing for a rocket-propelled` de
vcurnferentially spaced relation, .said annular
member being axially divided to provide semi
.circular half-„sections and means for. securely
clamping said half-sections about said casing at
>closely fitting said casing at one side of said Zone `
said one side, said casing _in the .circumferential
and extending from said one side axially over and
region at the other side of said Zone'and the cir
cumferential portion of the Iinner Wall of saidv
i substantially beyond said zone in circumferen
annular member spaced vfrom the casing being
. tially spaced relation, said annular member-being
axially dividedto provide semi-circular half
_contoured to provide an annular Venturi pas
sage, said circumferential regionof said casing
1 sections, and means for securely clamping said
Qïleast one aperture thr-ough the .wall thereof for »f
`:discharging from theu interiorthereof gases re
1 `>sulting from the burning ofI the propelling charge,
ï an annular member surrounding Vsaid casing and
1 half-sectionsl about said casing at said one side..3. A tubular casing for a rocket-propelled de- v ;
Í~vice, adapted to'contain a combustible propelling `
>charge and having in Va circumferential zone at
i -leastlone aperture through the wallr thereof-.for `
Y
discharging from'. the interior thereof gases re-`
at .said other side being conical in form and
taperingradially outwardly in a direction away
from said'apertured Zone, and the surrounding
said' circumferential 'portion beingA correspond
ingly taperedvto a greater degree.
, V 7._ Agtubularcasingfor‘ a rocket-propelled de
` sulting from the burning of the propelling charge,
»,vice, adapted to contain a combustible propelling
<anannular ‘member surrounding said casing and § `chargeV and having in agcircumferential zone at Y
Ä-c'losely fitting said casing at one side of saidfzone Y lleast-»one-aperture- through the wall thereof for
`'discharging' from' theginterior thereof ¿gases re
substantially beyondsaid'zone in. circumferen-"è ¿sulting from' the burningpof the propelling charge,
band extending from saidzone side axially over. and' >
I tially spaced relation, said annular member being
75
an annular member surrounding said casing and
2,406,560
5
with said casing an axially directed propulsion
closely iitting said casing at one side of said
jet communicating with the interior of said cas
Zone and extending from said one side axially
over and substantially beyond said zone in cír
cumferentially spaced relation, the external sur
face of said casing at the other side of said zone
for the region surrounded by said annular mem
ber being conical in form and tapering radially
outwardly in a direction away from said aper
tured zone, said conical surface and the inner Wall
of the spaced portion of said annular member to
gether deñning an annular Venturi passage.
8. A tubular casing for a rocket-propelled de
vice, adapted to contain a combustible propelling
charge and having at each of a plurality of axi
ing through the apertures of the surrounded zone,
each of said elements being axially divided to
provide semi-circular half-sections, and means
for securely clamping said sections around said
casing.
"
9. A tubular casing for a rocket-propelled de
vice, -adapted to contain a combustible propelling
10 charge and having in a circumferential Zone at
least one aperture through the Wall thereof for
discharging from the interior thereof gases re
sulting from the burning of the propelling charge,
an annular member surrounding said casing and
ally spaced circumferential zones one or more 15 closely ñtting said casing at one side of said
zone and extending from said one side axially
apertures through the wall thereof for the dis
over and substantially beyond said Zone in cir
charge> from the interior of the casing of gases
resulting from the burning of the propelling
charge, and spaced external annular elements
surrounding said casing, each closely ñtting said 20
cumferentially spaced relation, and a plurality
of radially extending dowei pins extending
through said annular member into said casing
casing at one side of an aperturedrzone, and
extending axially over and beyond said zone in
movement on said casing.
circumferentially spaced relation and deñning
at said one side for locking said member against
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WINSLOW B. POPE.
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