Improvements in Projectiles.
Year: 1896

page_text: Date of Application, 17th Nov., 1896
Complete Specification Left, 14th Sept., 1897- Accepted, 17th Dec., 1897
Improvements in Projectiles.
[, WILHELM THEODOR UNGE, of Villagatan No. 24, Stockholm, Sweden, Captain,
do hereby declare the nature of this invention to be as follows:-
This invention relates to a projectile which, like a rocket, encloses a gas-producing
composition, by which it may be set into motion without any shock and be driven
through the air almost soundless after being let off from a rotary cannon such as
described in the specification of Letters Patent granted to me and numbered 25005
of 1893, or from an ordinary rifled or unrifled cannon, or from an open or breech
closed tube or bore, or in some other way, for the purpose of giving the projectile
its initial direction and, it may be, initial rotation, and which can proceed through
the air in a given course, carrying a certain charge, which may consist of an
explosive sensitive to percussion a granate or grenade charge, or a lighting-charge,
with the purpose of hitting a spot at a certain distance so as to cause explosion,
shelling, or illumination.
This projectile, which I propose to call a flying torpedo, may also be used to curry
a line for saving purposes or wires for conducting electricity for the purpose of
developing electric power in the torpedo itself for steering or igniting the torpedo,
or for that of forming a telephonic connexion, or for some other purpose.
For a long time rockets have been used both for war-purposes and also as an aid
for saving life and signalling. To give the rocket increased certainty of aim,
greater amplitude of range, and increased carrying-power, has for a lengthy period
been the object of many experiments. Among these we may mention the abolition
of the steering-rod, and in its stead giving the rocket rotation on its longitudinal
axis, so as to cause it to proceed in a given direction. It has been endeavoured to
obtain the necessary rotation by applying screw-like wings along the outer cylin-
drical surface of the rocket, so that, when the rocket was in motion, atmospheric
pressure would cause rotation, and also by allowing the gas of the driving-
composition to stream out through short oblique openings in the periphery of the
botton or end piece, or against screw-shaped wings or blades arranged at the rear
of the rocket on its inner walls. These and other arrangements hitherto tried have
failed from various causes. By allowing, for instance, a certain quantity of the gas
to rush out directly from the composition in a straight line backwards either in the
direction of the rocket or through oblique holes, it happened that, by the
inequality of the development of the gas, such gas-jets constantly changed their
direction of efflux and thus disturbances arose in the course of the rocket or
projectile.
To give a flying torpedo an accurate course, the rotating device or gas-turbine
must consequently be constructed in quite a different manner from heretofore. The
gas must be compolled to equalize its pressure before leaving the projectile. This is
accomplished in my flying torpedo by arranging first, that, the oblique surfaces
designed for producing the rotation overlap each other considerably; secondly, that
the central part of the gus-stream produced in the gas-chamber shall be shut off by a

page_text: cone or rounded part (deflector), which, without any shook will distribute the gas to
the entire periphery of the turbine; and, finally, that the gas shut off between the
outlets shall be led by meaus of oblique guiding-planes without any shock to the
respective-outlets. For the same purpose the stream of gas may be somewhat com-
pressed before it reaches the turbine by a dished or concave ring placed in front of
and with its concavity towards, the turbine. In consequence of these arrangements
the gas has no opportunity of passing directly from the part of the composition
where it is developed into the air, and thus the pressure of the gas is perfectly
equalized before it escapes.
The reason why sufficient rotation and the desired amplitude of mnge and carrying-
power has not hitherto been obtained is that the gas-power has not been taken care
of to the necessary extent. By a faulty construction of projectiles of these kinds a
considerable part of the power was lost, partly through the shock against the bottom
of the projectile, partly through the fact that the escaping gas left the projectile at
too high a pressure, and partly through other causes. The oblique gas-channels
should therefore not as hitherto be made of the same size or of the same sectional
area from beginning to end, but the outlet-channels should be trumpet or wedge
like in form 1.6., from the inlet-end they should expand more and more and as much
as allowed by the space in the turbine, so that the gas escaping through the smaller
apertures may expand gradually and in the meantime exert a continuous re-action
on the opposing oblique surface 'intended for producing the rotation. In order that
no power shall be lost through shocks, the gas must not, as heretofore, be shut off
at the outlet-end by surfaces at right angles to the line of movement of the gas, an
arrangement which, moreover, has the disadvantage of causing the fastening and the
strength of the turbine to be unduly tried and increases the heating of the turbine.
In iny flying torpedo, on the other hand, I utilize the vis viva possessed
by the gas when it strikes the turbine. This is accomplished by the before
mentioned obliquity of the shutting-off surfaces between the outlets and a
prolongation of the aforesaid oblique or screw surfaces, in consequence of which the
vis viva contributes to the rotation, while at the same time shocks and the
unnecessary strain on and heating of the turbine is avoided. The shock of the central
part of the gas-stream is prevented by the above mentioned deflector.
Another disadvantage attending the self-propelling projectiles hitherto tried was
that the hot gas melted the outlet-channels and the oblique surfaces or vanes and
so constantly widened the outlet-area, with the result that the necessary gas-pressure
in the projectile could not be kept up. To avoid this disadvantage the flying torpedo
has special masses of metal or other suitable material placed before and on either or
each side of the outlets, so as to absorb the heat which might injure the outlet-
channel. These masses also form the above-mentioned guiding-planes and thus
there is formed an inlet-channel to the outlet-channel.
By the aforesaid gas-turbine of the flying torpedo the gas-pressure is thus equalized
before the gas passes through or out of the turbine, the gas is shut off or dammed
without any shock, and the gas causes rotation, partly owing to its via visa in the
inlet-channel, and partly by reaction in the outlet-channel, besides which the gns in
deprived by the heat-absorbing musses of so much heat that it cannot detrimentally
affect the form of the turbine nor the pressure of the gas enclosed in the projectile.
As in this gua-tarbine rotation is effected first by the passage of the gas through
the inlet-chanuels as in a jet-turbine and afterwards by the passage of the gas
through the outlet-channels as in a reaction-turbine, this turbine may be considered
as a double turbine; it follows, therefore, that rotation may be given to the
projectile by a turbine formed either solely of inlet-channels or of outlet-channels.
Other causes for the failure of all attempts to construct self-propelling projectiles
with the desired quantities or properties are that the walls of the projectiles or
rockets made have been too weak to be able to withstand the necessary pressure, or
else been too heavy, or that the walls could not withstand the influence of beat but
have been thereby weakened; that the manner of attaching the front and rear ends
have been unsatisfactory; and that the walls of the projectile have been too elastic

page_text: so that, in consequence of the gas-pressure, they have expanded so far that a space
has been formed between the walls and the composition and cracks have arisen in the
latter, causing explosion and other disadvantages.
In order to obtain projectile-walls of the requisite power of resistance, the flying
torpedo is made of steel or other strong material, the walls being protected against
the heat of the gas by being made thicker, but only in that part of the projectile.
where the hot gas comes into contact with it and in proportion to the time the
contact lasts, so that the walls do not become unneccessarily heavy; and in order
to prevent the walls of the flying torpedo from expanding under the gus-pressure, they
are given an initial resistance as in guns-i.e. by causing a tension in the outer
layers of the projectile.
Having now mentioned the chief reasons while a self-propelling projectile possess
ing certainty of aim combined with great amplitude of range and carrying power has
as yet not been constructed, and the principle on which such projectiles should be
constructed, I will now describe a projectile constructed according to my invention.
A flying torpedo according to this invention comprises a gas-light cylindrical or
conical tube made of steel or other suitable substance; the front or narrower end is
drawn out to a closed point and the internal space is divided by a gas-tight partition
into two chambers of which the front one with the point (the charging-chamber) is
designed to contain the explosive or other charge to be transported, and the rear one
(the gas-chainber) to contain the gas-developing substance or composition for pro-
pelling and rotating the projectile. The rear part of the gas-chamber from which
the gas is to escape, is closed by a gas-turbine constructed on the aforesaid principles.
This turbine, like the above mentioned partition is fixed to the walls of the tube or
projectile by powerful flat screw-thrends, screw-rivets, or in some other sure or
certain manner.
To prevent the walls of the gas-chamber from giving way when gas-pressure arises,
they are given outer tensions, which may be accomplished by hardening or by
shrinking one or more rings or casings on them, or by winding wires or coils round
them or in any other suitable mannor. Lu order that the hot gas may not glow or
render red hot or weaken the walls of the gas-chamber, these walls may be made
thickest next to the gas-turbine and decrease in thickness towards the other end. The
outer or the inner surface (or both) of the gas-chamber or of the whole torpedo may
therefore be advantageously made of conical form.
To render possible the use of charging chambers of different size and with various
contents, and to make the flying torpedo more suitable for transport, the charging-
chamber can be separated from or fastened to the rear part. For this purpose the
gas-chamber is somewhat prolonged in front of the gas-tight end and provided with
screw-threads, or other means of coupling.
At the rear end of the flying torpedo, as previously mentioned there is inserted
the gas turbine, which serves to shut off or dain the gas, thereby causing the desired
pressure to arise therein to effect rotation and, it may be, to contain an additional
driving-charge and an igniting-device. This gas-turbine, constructed on the
principles already set forth may be made of a solid cylinder of metal or other
substance not easily melted, which fills the rear end of the tube of the projectile.
Along the outside of this cylinder are made two or more channels arranged helically
in relation to the axis of the cylinder and leaving a solid core in the centre. Each
of the said channels consists of two wedge-shaped parts with the sin iller apertures
(minimum outlets) turned towards each other and is formed in such a manner that
the surface opposed to the stream of gas forins what may be regarded as a continuous
screw-plane. In order to distribute the stream of gas the front end of the core is
provided with a cone or rounded off part (the deflector) so that the central part of
the stream of gas is deflected towards the periphery into the mouths of the above-
mentioned channels. The entire gas-turbine is surrounded by a casing and held in
place by a shoulder and screws. The casing is intended for fixing the turbine to the
end of the tube of the torpedo. The outer surface of this casing may be screw-threaded
and the turbine screwed into the torpedo-tube.

page_text: The casing may be prolonged backwards so as to afford accommodation behind the
turbine for a driving charge to be used as an assistance in starting, and also forwards
as a protection against the heat and pressure of the gas. Through the centre of the
core the igniting-channel passes to the driving-composition for the purpose of
igniting the torpedo, which may be done by a safety-fuse or by an electric or other
ignitor fitted in the rear part of the core. When an additional driving-charge is
used the firing may be so arranged (in order to ensure that the torpedo cannot be
ejected by the said charge in case the composition from any cause have not been
ignited) that the composition will be first ignited and that its gas will then ignite
the additional driving-charge. To effect this the driving-charge may be made in
the form of a ring, or be provided with an aperture through which an insulated
safety-fuse may be carried, or through which the firing-device may be accessible for
an electric contact or other means of ignition.
By way of recapitulation it may be said that the gas-turbine in its entirety may
comprise two or more outlet-chaunels with oblique planes which force the escaping
gas to deflect; for every outlet-channel, a guiding plane or inlet-channel provided
with a mass for the guidance of the gas to the ontlet-channels and for absorbing the
heat of the gas, a deflector for distributing the central part of the gas-stream to the
periphery; a core with an igniting-device; and a casing, which may he provided
with a rearward prolongation for forming a chamber for an additional driving-charge
and a forward prolongation adapted to serve as a protector for the projectile.
If it be so desired, the slope of the guiding-planes and the size of the heat-
absorbing pieces may be lessened or entirely dispensed with, in which latter case, as
previously mentioned, the turbine will produce rotation simply by the gas-pressure
in the outlet channels.
Fig. 1 of the accompanying drawings represents a cross section through the
minimum apertures of a gas-turbine according to this invention. Fig. 2 shows the
cylindrical surface of the turbine developed on a plane: A, A, are the inlet-channels
and B, B, The outlet channels, which may both be of another form as, e.g. shown
by dotted lines; C, C,. . . are the minimum apertures, DN, D N,... the guiding-
planes; NE, NE,.. the oblique planes of the turbine; and D NO, D NO...
the heat-absorbing masses. Fig. 3 represents a side-view of the turbine: F is the
casing (shown in section) with the driving-charge chair ber G and the projectile-
protector H; K is the core with the deflector L; and M is a concave piece (shown
in section) which may be placed in front of the turbine. Fig. 4 is a front view of
the turbine and concave piece.
Doted this 17th day of Nov 1906
I, WILHELM THEODOR UNGE, of Villagatan No. 24, Stockholm, Sweden, Captain
do hereby declare the nature of this invention and in what manner the same is to
be performed to be particularly described and ascertained in and by the following
statement :-
This invention relates to a projectile which, like a rocket, encloses a gas-producing
composition, by which it may be set into motion without any shock and be driven
through the air almost soundless after being let off from a rotary cannon such as
described in the Specification of Letters Patent granted to me and numbered 25005

page_text: of 1893, or from an ordinary rifled or unrified cannon, or from an open or breech
closed tube, or in some other way, for the purpose of giving the projectile its initial
direction and, it may be, initial rotation, and which can proceed through the air in a
given course, carrying a certain charge, which may consist of an explosive sensitive
to percussion, a grenade-charge or a lightning charge, with the purpose of hitting a
certain spot at a distance so as to cause explosion, shelling, or illumination.
This projectile, which I propose to call a "flying torpedo," may also be used to
carry a line for saving-purposes or wires for conducting electricity for the purpose of
developing electric power in the torpedo itself for steering or igniting the torpedo, or
for that of forming a telephonic connection, or for some other purpose.
For a long time rockets have been used both for war purposes and also as an aid
for saving life and signalling. To give the rocket increased certainty of aim, greater
amplitude of range, and increased carrying-power, has for a lengthy period been the
object of many experiments. Among these we may mention the abolition of the
steering-rod, and in its stead giving the rocket rotation on its longitudinal axis, so as
to cause it to proceed in a given direction. It has been endeavoured to obtain the
necessary rotation by applying screw-like wings along the outer cylindrical surface of
the rocket, so that, when the rocket was in motion, atmospheric pressure would cause
rotation, and also by allowing the gas of the driving-composition to stream out through
short oblique openings in the periphery of the bottom or end piece, or against screw-
shaped wings or blades arranged at the rear of the rocket on its inner walls. These
and other arrangements hitherto tried have failed from various causes. By allowing,
for instance, a certain quantity of the gas to rush out directly from the composition
in a straight line backwards either in the direction of the rocket or through oblique
holes, it happened that, by the inequality of the development of the gas, such
gas-jets constantly changed their direction of efflux and thus disturbances arose in the
course of the rocket or projectile.
To give a self-propelling and self-rotating torpedo an accurate course, the rotating
device or gas-turbine must consequently be constructed in quite a different manner
from hertofore. The gas must be compelled to equalize its pressure before leaving
the projectile. This is accomplished in my flying torpedo by arranging first, that the
entrance mouth and the outlet mouth of each channel of the turbine overlap each
other so much-i.e., are so far from opposite each other-that no gas can pass
through the turbine in the direction of the axis of the turbine; secondly, that the
central part of the gas-streamn produced in the gas-chamber shall be shut off by a cone
or rounded part (deflector), which, without any shock, will deflect the gas to the
entire periphery of the turbine; and, finally, that the gas shut-off or dammed-in
between the outlet-openings shall be led by means of oblique guiding-planes without
any shock to the respective outlet-openings. For the same purpose the stream of
gas may be somewhat compressed before it reaches the turbine by an annular
partition, placed in front of the turbine and having its central opening of about the
same diameter as the deflector. In consequence of these arrangements the gas has
no opportunity of passing directly from the part of the composition where it is
developed into the air, and thus the pressure of the gas is perfectly equalized before
it escapes.
The reason why sufficient rotation and the desired amplitude of range and carrying-
power have not hitherto been obtained is that the gas-power has not been taken care
of to the necessary extent. By a faulty construction of projectiles of these kinds a
considerable part of the power was lost, partly through the shock against the bottom
of the projectile, partly through the fact that the escaping gas left the projectile at
too high a pressure, and partly through other causes. The oblique gas-channels
should therefore not as hitherto be made of the same size or of the same sectional
area from beginning to end, but the outlet channels should be trumpet or wedge like
in form i.e. from the inlet-end they should expand more and more the wall opposite
the oblique surface gradually receding, as much as allowed by the space in the
turbine, so that the gas escaping through the small aperture may expand gradually

page_text: and in the meantime exert a continuous re-action on the oblique surface intended
for producing the rotation.
In order that no power shall be lost through shocks, the gas must not, as hereto-
fore, be shut off at the outlet-end by surfaces at right angles to the line of movement
of the gas, an arrangement wbich, moreover, has the disadvantage of causing the
fastenings and the strength of the turbine to be unduly tried and increases the heating
of the turbine.
In my flying torpedo, on the other hand, 1 utilize the via viva possessed by the
gas when it strikes the turbine. This is accomplished by the fact that the shutting-off
surfaces between the outlet-openings are, as before mentioned, oblique and prolonga-
tions of the aforesaid oblique or screw surfaces, in consequence of which the vis viva
contributes to the rotation, while at the same time shocks and the unnecessary strain
on and heating of the turbine is avoided. The shock of the central part of the
gas-strean is prevented by the above mentioned deflector.
Another disadvantage attending the self-propelling projectiles heretofore tried was
that the hot gas melted the outlet-channels and the oblique surfaces or vanes and so
constantly widened the outlet-area, with the result that the necessary gas-pressure in
the projectile could not be kept up. To avoid this disadvantage the flying torpedo
has special masses of metal or other suitable material placed before and on each side
of the outlet-openings, so as to absorb the heat which might injure the outlet-
channel. These masses also form the above-mentioned guiding-planes and thus there
are formed inlet-channels to the outlet-openings.
By the aforesaid gas-turbine of the flying torpedo the gas-pressure is thus equalized
before the gas passes through or out of the turbine, the gas is shut off or dammed
without any shock, and the gas causes rotation, partly owing to its via viva in the
inlet-channels, and partly by reaction in the outlet-channels, besides which the gas
is deprived, by the heat-absorbing masses, of so much heat that it cannot detrimentally
affect the form of the turbine nor the pressure of the gas enclosed in the projectile.
As in this gas-turbine rotation is affected first by the passage of the gas through the
inlet-channels as in a jet-turbine and afterwards by the passage of the gas through
the outlet-channels as in a reaction turbine, this turbine may be considered as a
double turbine; it follows, therefore, that rotation may be given to the projectile by
a turbine formed either solely of inlet channels or solely of outlet-channels.
Other causes for the failure of all attempts to construct self-propelling projectiles
with the desired properties are that the walls of the projectiles or rockets made have
been too weak to be able to withstand the necessary pressure, or been too heavy, or
that the walls could not withstand the influence of heat but have been thereby
weakened; that the manner of attaching the front and rear ends have been
unsatisfactory; and that the walls of the projectile have been too elastic, so that, in
consequence of the gas-pressure, they have expanded so far that a space has been
formed between the walls and the composition, and cracks have arisen in the latter,
causing explosion and other disadvantages.
In order to obtain projectile-walls of the requisite power of resistance, the flying
torpedo is made of steel or other strong material, the walls being protected
against the beat of the gas by being made thicker, but only in that part of the
projectile where the hot gas comes into contact with it and in proportion to the
time the contact lasts, so that the walls do not become unnecessarily heavy; and
in order to prevent the walls of the flying torpedo from expanding under the
gas-pressure, they are given an initial resistance as in guns, i.e. by causing a
contractile tension in the outer layers of the projectile.
Having mentioned the chief reasons why a self-propelling projectile possessing
certainty of aim combined with great amplitude of range and carrying power has
as yet not been constructed, and the principles on which such projectiles should
be constructed, I will now describe a projectile constructed according to my
invention.
A flying torpedo according to this invention comprises a gas-tight cylindrical or
conical tube made of steel or other suitable material; the front end is drawn out to

page_text: a closed point and the internal space is divided by a gas-tight partition into two
chambers of which the front one with the point (the charging-chamber) is designed
to contain the explosive or other charge to be transported, and the rear one (the
gas chamber) to contain the gas-developing substance or composition for propelling
and rotating the projectile. The rear part or the gas-chamber from which the
gas is to escape, is closed by a gas-turbine constructed ou the aforesaid principles.
This turbine, like the abovo mentioned partition, is fixed to the walls of the inbo
or projectile by powerful flat screw-threads, screw-rivets, or in some other sure or
certain manner.
To prevent the walls of the gua-ohamber from giving way when gas pressure
arises, they are given outer tensions, which may be accomplished by hardening or
by shrinking one or more rings or casings on them, or by winding wires or coils
round then, or in any other suitable manner. In order that the hot gas may
not reuder red hot or weaken the walls of the gas-chamber, these walls may be
inade thickest next to the gas-turbine and decrease in thickness towards the
other end. The outer or the inner surface (or both) of the gas-chamber or of
the whole torpedo may therefore be advantageously made of conical form.
To render possible the use of charging-members of different sizes and with
various contente, and to make the flying torpedo, more suitable for transport, the
charging-chamber can be separated from or fastened to the rear part. For this
purpose the gas-chamber is somewhat prolonged in front of the gas-tight end
and provided with screw-threads or other means of coupling.
At the rear end of the flying torpedo, as previously mentioned, there is inserted
the gas-turbine, which serves to shut off or dam the gas, thereby causing the
desired pressure to arise therein to effect rotation and, and, it may be, to contain an
additional driving-charge or throw-charge (hereinafter referred to as a throw-charge)
and an igniting-device. This gas-turbine, coustructed on the principles already set
forth, may be made of a solid cylinder of metal or other substance not easily melted,
which fills the rear end of the tube of the projectile. Along the outside of this
cylinder are made two or more channels arranged helically in relation to the axis of
the cylinder and leaving a solid core in the centre. Each of the said
channels consists of two wedge-shaped parts with the smaller apertures
(minimum openings) turned towards each other and is formed in auch a
manner that the surface opposed to the stream of gas forms what may be
regarded as a continuous screw-plane. In order to distribute the stream of gas the
front end of the core is provided with a cone or rounded-off part (the deflector) so
that the central part of the stream of gas is deflected towards the periphery into the
above-mentioned outlet-openings. The entire gas-turbine is surrounded by a casing
and held in place by a shoulder and screws. The casing is intended for fixing the
turbine to the end of the gas-chamber or of the tube of the torpedo. The outer
surface of this casing may be screw-threaded and the turbine screwed into the
torpedo tube.
The casing may be prolonged backwards so as to afford accommodation behind
the turbine for a throw-charge to be used as an assistance in starting, and also
forwards as a protection against the heat and pressure of the gas, as also
a support for the driving composition and at the same time to form a
space between the driving composition and the turbine. Instead of prolonging
the casing forwarda a short piece of a tube may be inserted directly in
front of the turbine for the same purpose. Through the core the igniting channel or
channels passes or pass to the driving-composition for the purpose of igniting
the torpedo, which may be done by a safety-fuse or by an electrio or other ignitor
fitted in the rear part of the core. When a throw-charge is used the firing may he
so arranged (in order to ensure that the torpedo cannot be ejected by the said charge
in case the composition from any cause had not been ignited) that the composition
will be first ignited and that its gas will then ignite the throw-charge. To effect
this the throw-charge may be made in the form of a ring, or be provided with an
aperture through which an insulated safety fuse may be carried, or through which

page_text: the firing-device may be accessible for an electric contact or other means of igniting.
By way of recapitulation it may be said that the gas-turbine in its entirety may
comprise two or more outlet channels with oblique surfaces against which the escaping
gas acts by impact on the fore part and by reaction on the hind part; a guiding
plane for every outlet channel for the guidance of the gas to said channel and for
receiving part of the vis viva of the gas-stream, thereby augmenting the velocity of
rotation of the projectile; a metal mass behind every guiding plane for absorbing
the heat of the gas; a deflector for distributing the central part of the gas-stream
to the periphery ; core with an igniting device; and a casing, which may be
provided with a rearward prolongation for forming a chamber for a throw charge and
a forward prolongation for forming a gas-space and a protector for the projectile.
If it be so desired, the slope of the guiding-plane and the size of the heat-
absorbing pieces may be lessened or entirely dispensed with, in which latter case, as
previously mentioned, the turbine will produce rotation by the gas-pressure in the
outlet-channels only.
Fig. 1 of the accompanying drawings represents a cross section through the
minimum apertures or outlets of a gas-turbine according to this invention;
Fig. 2 shows the cylindrical surface of the turbine developed on a plane.
Fig. 3 represents a side view of the turbine with surrounding parts in section;
Fig. 4 is a front elevation of the same.
Fig. 5 is a side elevation of a projectile.
a a are the inlet channels and b b the outlet channels, which may both be of
another form as e.g. shown by dotted lines in Fig. 2; co are the minimum apertures
or outlets; d n d n the guiding planes; ne, ne the oblique surfaces of the turbine;
and d no, d no the heat absorbing masses. f the cusing shown in section (with
the throw charge chamber g and the projectile-protector h; kis the core with the
deflector ; and m is a partition with a central aperture which may be placed in front
of the turbine; p are narrow channels through which the ignition of the main
driving charge is produced from the chamber g in the core, in which the igniting
device is placed. Fig. 5 shows by dotted lines the outer form of a projectile the
walls of the gas-chamber of which decrease in thickness from back to front in order
to reduce the weight.
Having now particularly described and ascertained the nature of the said inven-
tion and in what manner the same is to be performed I declare that what I
claim is:-
1. A self-propelling and self-rotating projectile comprising a turbine fixed in the
rear end of the projectile behind the gas-producing composition and made of a solid
cylinder of metal or other substauce not easily melted along the outside of which two
or more channels are cut out to a certain depth leaving a solid core in the centre,the said
channels being arranged symmetrically round the circumference and passing helically
from the fore ond of the cylinder to the rear end of the same and being of such a
form that each of them widens or expands either backwards or forwards or both
backwards and forwards from a minimum opening, and that the surface against which
the gas-stream from the ignited composition strikes is formed as a screw-surface with
constant or varying pitch, substantially as and for the purposes set forth.
2. A self-propelling and self-rotating projectile of the kind referred to in the
preceding claim, in which the front end of the core is provided with a cone or
rounded-off part, substantially as and for the purpose set forth.
3. A self-propelling and self-rotating projectile of the kind referred to in claim 1,
provided with a cavity in the rear end of the core for an igniting composition or an
electric or other ignitor and communicating with the gas-chamber of the
projectile, substantially as and for the purpose set forth.
4. A self-propelling and self-rotating projectile of the kind referred to in claim I
in which the turbine is inserted and fixed in a casing which is provided with a
supporting shoulder and fixed in the back part of the projectile, and is somewhat

page_text: longer than the turbine so that spaces are formed either behind or before or both
behind and before the turbine, substantially as and for the purposes set forth.
5. A self-propelling and self-rotating projectile of the kind referred to in claim 1
having a partition provided with a central aperture arranged before the turbine
substantially as and for the purpose set forth.
6. A self-propelling and self-rotating projectile of the kind referred to in claim 1
in which the thickness of the walls of the gas-chamber decreases from the turbine
forward, substantially as and for the purpose set forth.
7. A self-propelling and self-rotating projectile constructed arranged and operating
substantially as herein described with reference to and shown in the drawings
annexed.
Dated this 14th day of September 1897.
For the Applicant
W. LLOYD WISE
46 Lincoln's Inn Fields, London, W.C. Chartered Patent Agent.