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Патент USA US2409428

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EQUILIBRATED ROCKET SHELL`
Filed July il.,l
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Patented Oct. 15, y1946
2,409,427
UNITED STATES PATENT
OFFICE
2,409,427
EQUILIBRATED ROCKET SHELL
Zygmunt Fonberg, New York, N. Y.
Application July 1, 1943, Serial No. 493,023
5 Claims.
(Cl. 102-49)
1
2
This invention relates to a special type of '
equilibrated rocket-shell which is to be used as
an effective recoilless weapon in form of shell
similar in effect to ordinary gun shells or in form
rotates on the ball bearing M4. This rotative
action is of major importance because it elimi
nates imperfectness of choke and propulsive
action does lnot affect the bombing accuracy.
of aerial bomb.
`
5 Slight gyroscopic effect given by the choke’s rota
Figure 1 is a vertical sectional View of Figure 3.
tion can be eliminated by steering wings K4 which
Figure 2 is a vertical sectional View of Figure 4.
will turn the bomb in opposite direction of the
Figure 3 is a fragmentary longitudinal sec
rotation of choke H4.
tional view of an embodiment of the invention.
Figure 2 represents shell or bomb in action
Figure 4 is a fragmentary longitudinal secL 10 similar to that represented in Figure 1 but
tional view of another embodiment of the in
mounted on slide D5.
vention.
'
For the purpose of avoiding needless repeti
The present equilibrated rocket shell can be
tion, the second embodiment of the invention
made in several slightly different types. The
shown in Figures 2 and 4, has parts thereof which
principle of its action is as follows: the pro 15 correspond to the first embodiment of the inven
pulsive material ignites in chamber A4, see Figure
tion given the same reference character with
3, and generates high pressure gases which are
the addition of the exponent 5 as a suffix. Its
emitted through the choke H4 giving, by the
action is as following: The propulsive material
law of reaction, propulsive motion to the shell.
generated in chamber A5 gives propulsive motion
A portion of the gases escapes through the choke 20 to the shell without delayed action and at the
E4, giving the shell a rotative movement which
same time rotates choke H5 by means of spades
gives the advantage of >maintaining it on a
C5 placed at that choke. This shell can be used
straight trajectory regardless of imperfections
both as aerial bomb placed vertically on the
and the defects in its manufacture. This rota
racks of aircrafts or can be ñred from the slide
tive movement provides the possibility of main 25 D5 in any direction.
.
taining propulsive action after the shell has
It is claimed and desired to secure by Letters
started on its course of travel without the danger
Patent:
of affecting the direction of the shell’s initial
1. A rocket shell comprising: a chamber hav
movement.
ing propulsive material therein adapted to pro
30
It is known that up to now rocket shells have
duce gas at high pressure; a principal choke
been very inaccurate if the action of propul
sion has been maintained after the shell has
left the slide or barrel which has directed the
Yshell’s initial movement. The present arrange
ment of giving a rocket shell a rotative move
rotatably mounted on said chamber and through
which said gas is emitted; a secondary choke
angularly disposed with respect to the axis of
rotation of the primary choke and adapted to
35 emit a portion of said gas to cause rotation of
ment eliminates the above mentioned incon
said principal choke; and means to rotate said
venience. The shell’s rotative movement can be
chamber in a direction opposite to the direction
produced by spades K4 placed at a proper angle
of rotation of the principal choke wherebyv the
as shown in Figure 1 and the initial direction
gyroscopic action of the rotative principal choke
can be given by a well known barrel (not shown) 40 is compensated for.
inside of which the shell moves. The shell has
2. A rocket shell comprising: a chamber hav
to be given sufficient propulsion and rotative
ing propulsive material therein adapted to pro
movement while in said barrel to maintain its
duce gas at high pressure; a choke rotatably
direction.
Figure 1 represents the arrangement of rota 45 mounted on said chamber and through which
said gas is emitted; first means to rotate said
tive_ choke H4 which can be used with special
choke in one direction and second means to
advantage in aerial bombs. It action is as fol
rotate said chamber in an opposite direction;
lowing: After the bomb leaves the racks of the
whereby the gyroscopic effect of said rotative
aircraft, propulsive material in chamber A4 is
ignited with sufficient delay and gases escaping 50 choke in rotating is counter-acted by the counter
rotation of the chamber.
by the rotative choke H4 and acting in con
3. A rocket device comprising: a chamber hav
junction With force of gravity give propulsive
ing propulsive material therein adapted to pro
motion to the bomb. Part of those gases acts
through chokes E4 which give a fast rotative ’
duce gas at high pressure; a choke rotatably
movement 'to the principal choke H4, which 55 mounted on said chamber and through which
2,409,427
3
said gas is emitted; first means to rotate said
choke in one direction; and second means in
cluding steering wings, to rotate said chamber
in an opposite direction; whereby the gyroscopic
eifect of said rotative choke is counter-acted
by the reverse rotation of the chamber.
4. A rocket shell comprising: a chamber hav
ing propulsive material therein adapted to pro
4
5. A rocket shell comprising: a chamber hav
ing a propulsive material therein adapted to
produce gas at high pressure; a principal choke
rotatably mounted on said chamber and through
which a portion of said gas is emitted; a sec
ondary choke angularly disposed with respect to
the axis of rotation of the principal choke and
adapted to emit a portion of said gas to cause
rotation of saidrprincipalchoke; and a steering
duce gas at high pressure; a principal choke
rotatably mounted on said chamber and through 10 wing connected to said chamber and in the path
of the gas emitted by the secondary choke, a
which a portion of said gas is emitted; a sec
ondary choke angularly disposed with respect toY
Vportion of said steering wing being arranged at
an angle to the line of flight of the rocket shell,
the aXis of rotation of the principal choke and
whereby the gas emitted by the secondary choke
adapted to emit a portion of said gas to cause
rotation of said principal choke; anda steering 15 and the air through which the rocket shell takes
flight cause the wing to rotate and hence the
wing connected to said chamber and in the path
of gas emitted by the secondary choke, whereby `> chamber‘to >rotate in the same direction and
oppositely to the direction of rotation of the
said wing and hence the chamber is caused to
said principal choke, so that the gyroscopic effect
rotate in a direction opposite to the direction of
rotation of the principal choke, so that the gyro 20 of the rotation of the principal choke is reduced.
scopic effect of the principal choke is counter
ZYGMLUN T FONBERG.
acted.
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