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Dee-10, 1946.
Filed Feb. '22, 1944
Reginald W?oagland
Patented Dec. 10, 1946 '
Reginald W. Hoagland, Detroit, Mich". assignor,
by mesne assignments, to United States of '
America ‘
Application February 22, 1944, Serial No. 523,412
2 Claims. (Cl. 102-49)
invention relates to reaction propelled
‘devices, such as, for example, _explosive.projecr
tiles, smoke or chemicalshells, ?ares andthe,
Various devices of this type, commonly known
as “rocket shells,” have been proposed heretofore,
among which is. one‘ that embodies a tubular
casing secured to the rearward end of the pro
jectile body and having its rearward end swaged
2 ‘o
which is in the form of sticks I! of slow burning
powder or other suitable combustible material is
‘ carried by the cage ll.’
The rearward end of the casing 8 is swaged
' down or otherwise reduced in diameter to provide
an axially opening Ventu‘ri passage I5, which
from its throat l8 ?ares rearwardly and out‘
wardly in gradually increasing diameter, the wall
thickness of the casing remaining substantially
or otherwise reduced in diameter to provide an 10 the same throughout theulength of the casing.
axially opening Venturi passage, the wall of the
As is well known, the expansion of the gases
casing being of substantially uniform thickness
resulting‘ from the burning of the propelling
throughout. As a__ result of the reduction in
charge and flowing through the Venturi passage
diameter of the rearwardv end of the casing, a
l5 creates the propelling pressure.
circumferential pocket is formed which, due to 15
In accordance with ‘the present invention, a I
the vacuum produced therein during ?ight, tends
number ‘of vanes l8 are secured by weld material
to slow up the speed of travel of the projectile.
I‘! to the rearward end of the casing as shown
One of the objects of the present invention is
in the drawing, the same following the‘contour
to provide a novel means for relieving a rocket
of the region of reduced diameter." These vanes
shell of the above type of the vacuum produced 20 are arranged at an angle to *the axis of the pro- -
by the circumferential rocket whereby to de
crease its ?ight resistance.
jectile and each pair form with the external sur- _
face of the reduced end region a pocket or chan
Another object is to provide a rocket shell with
nel l9 open at its rearward end. The wall of the
a novel arrangement for utilizing a portion of
casing where the latter starts to reduce in diam
the propelling medium to rotate the shell con 25 eter is provided with a numberiof circumferen
tinuously during ?ight whereby to stabilize the
shell to. insure truer ?ight and to eliminate the
necessity of providing stabilizing ?ns extending V
outwardly from the body of the projectile.
With the above and other objects in view which
will be apparent from the following description
to those skilled in the art to which the invention
appertains, the present'invention consists of cer
tially spaced apertures 20, there being one such
aperture for each such channel. Each aperturew
20 is closelyadjacent to the forward end of one‘
vane of each pair. A'portiomof the gases re
sulting from the burning of the propellant thus
?ow under pressure through the apertures 20 and
by reason of the angularrelation of the vanes
- with respect to the axis of the projectile im
tain features of construction and combinations"
pinge upon the vanes 18 and thus cause- the
of parts to be hereinafter described with reference 35 projectile to rotate during its ?ight whereby to
to the accompanying drawing, and then claimed.
stabilize itself for true ?ight. The axially rear
In the drawing which illustrates a suitable
wardly ?aring external surface of the reduced
embodiment of the present invention:
end portion and the vanes provide in effect chan
Figure 1. is a side elevation of the projectile, '
partially in section to show the interior arrange 40 nels for the smooth evenly distributed ?ow of
the products of combustion. discharging from the
ment of the same, and
apertures 20.
Figure 2 is an enlarged section taken‘approxi
been described in '
mately on the line 2-2 of Figure 1.
connection with an explosive projectile it is to
Referring to the accompanying drawing, the
reaction propulsion device shown for illustration 45 be understood that the .same is equally as ap
plicable to any device of the rocket type adapted
includes a main projectile body 5 having a cham
to be projected through space, and that the vanes ,
ber liltherein for the reception of an explosive
l8 and apertures 20 may be arranged at locations
charge, not shown, and a rearwardly extending
burster tube ‘I.
other than at the rearward end of the casing.
Threadedly or-otherwise suitably secured to the 50' It is to be understood that various changes
base end of the body 5 is a tubular casing 8 hav
may be‘ made in' the detailed construction and
ing anintemal shoulder 9 at its forward end
arrangement of the parts described without de
which supports a plate Ill. The plate In supports
parting from the spirit and substance of the in
a cage Ii composed of rods I2 and an intercon
vention, the scope of which is de?ned by the ap
necting end ring l3. The propulsion charge 55 pended claims.
What is claimed is;
a .
1. In a reaction propulsion device, a tubul
casing adapted to contain a combustible pro
pelling charge, one end oi’ said casing being of
Products of combustion of said charge from said
casing, the external surface of said reduced and
' ?aring outwardly and axially away from the body
of said casing, said casing having a plurality
of. apertures through the wall thereof adjacent
reduced cross-section and providing an axially
said reduced end for discharging a portion oi’ said
opening Venturi passage for the discharge oi the
products of combustion about said reduced end,
products of combustion of said charge from said
and a plurality of circumferentially'spaced out
casing, the external surface 01’ said reduced end
wardly extending vanes joined to the external
?aring outwardly and axially away from the body
of said casing, said casing having a plurality of 10 wall of said reduced end and providing a plu
rality of channels, said apertures being disposed
apertures through the wall thereof adjacent said
to discharge products of combustion into said
reduced end for discharging a portion of said.
said vanes being angularly disposed
products of combustion about said reduced-end. - channels,
the axis of said casing and in the
2. In a reaction propulsion device. a tubular
path of discharge of the products of combustion
casing adapted to contain a combustible pro
from said apertures whereby to impart rotation‘
pelling charge, one end of said casing being of
to said device.‘
reduced cross-section and providing an axially
opening Venturi passage for the discharge of the
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