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Publication numberUS2114214 A
Publication typeGrant
Publication dateApr 12, 1938
Filing dateMar 5, 1936
Priority dateMar 9, 1935
Publication numberUS 2114214 A, US 2114214A, US-A-2114214, US2114214 A, US2114214A
InventorsLouis Damblane
Original AssigneeLouis Damblane
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Self-propelling projectile
US 2114214 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

April 12, 1938.


SELF-PROPELLING PROJECTILE Louis Damblanc, Paris, France Application March 5, issaserial No. 67,403

In Belgium March 9, 1935 r 7 Claims.

The present invention relates to self-propelling projectiles,.that is to say projectiles which are l provided, in addition to their specic charge,

which may be of any nature whatever (for start- 5 ing a re, producing a smoke of a special kind, etc.), with a propelling charge the combustion Vof which imparts to said projectiles, along at least a portion of their path of travel, a certain impulse. The invention is more especially, al- 10 though not exclusively, concerned, among projectiles of this kind, with rockets.

The object of the present invention is to providea projectile of the kind above referred to which is better adapted to meet the requirements of practice, and in which, in particular, the combustion of the propelling charge contained in the projectile isutilized with an improved efficiency.

The essential feature of the present invention consists in devising the envelope of a projectile of the type above referred to in such manner that the length of said envelope is gradually reduced as the propelling charge is being gradually burnt. Other features of the present invention will result from the following detailed description of 25 some specific embodiments thereof. l

Preferred embodiments of the present invenftion will be hereinafter' described, with reference to the accompanying drawing, given merely by way -of example, and in which:

30. Fig. 1 is anelevatlonal view, partly in section, of a rocket made according to an embodiment of the present invention;

Figs. 2 and 3 are views, similar to Fig. 1, relating to other embodiments.

3'5 r'Ihe examples that will be hereinafter describedconcern the case of rockets in which the propelling charge lis divided into a plurality of stages of combustion.

Concerning, the general arrangement, with the 40 exception of the envelope containing the propelling charges, it is devised in any usual manner known in the art.

Concerning the stages, or chambers, of combustion, (which are supposed to be four in number in the following description), they rare advantageously superposed inV the direction of the longitudinal axis of the rocket,.which is for instance given the general shape of a cylinder.

I further provide, in the direction of the axis of each chamber I, 2, 3, or 4, a nozzle 5, consisting of a cavity or recess, preferably of the shape of a frustum of a cone, the dimensions of which will be moreparticularly referred to in what follows, said nozzleubeing intended to facilitate the propagation of combustion in the charge..

(c1. 1oz-2c) vAdvantageously, the 4respective chambers i, 2, 3 and 4 are separated from one another by means of annular elements 6, made for instance of cardboard, which prevent premature ignition of the successive charges of -said chambers.

As for the charges, they may consist of any 4suitable matters, for instance powder. Y

Concerning now the envelope to be provided, in d such a rocket for forming thevarious chambers of combustion', instead of making it of a metal (or any other matter) capable of withstanding without deterioration the temperatures resulting from the combustion of the powder, according to the present invention it is made in a different manner, as will be hereinafter explained. As a matter of fact, the use of -a metal capable of withstanding the temperatures of combustion of the charge would have the following drawbacks:

(a) Formation of eddies in the free part of the envelope or cartridge as the charges of the ilrst chambers disappear by combustion;

(b) Heating of said free part, due to the fact that it is no longer heat insulated by the presence of powder thereon;

(c) Reduction of the useful outlet pressure; and

(dlDead weight constituted by the parts of the envelope that -are no longer useful.

According to the present invention, said envelope or cartridge is devised in such manner that its length is gradually reduced as the propelling charge that it contains is being burnt.

This result can be obtained in various ways. For instance, according to an embodiment of the invention, illustrated by Fig. 1, the cartridge or envelope is constituted by the mere juxtaposition of annular elements 1, of copper for instance, said elements being kept in position owing to the cohesion of the charge of powder they surround.v With this arrangement, as it will be readily understood, the combustion of the charge of powder produces the successive elimination of annular elements 1.

However, I considerthat it is more advantageous to constitute the cartridge or envelope of the assembly of elements, the number of which is, for instance, equa'lto the number of chambers or stages of combustion, established, or connected together, in such manner that each of the ,elementary propelling charges produces, at the end of its combustion, the elimination, through partial or total melting, or through combustion, of the element of the cartridge or envelope that contained said elementary charge.

In order to carry out a rocket according to this embodiment of the invention, it is necessary to make use of a metal, or other material, which melts at a temperature lower than the tempera` ture of combustion of powder (about 300 CJ, while being sufficiently strong for' constituting the cartridge or envelope of the rocket.

'I'here exist,I at the present time, many alloys l which comply withvthese conditions, for instance the following:

Rose's metal (1 part of tin, 1 of lead, 2 of bis- -muth) the melting point of which is 110;

Woods metal (4 parts of tin, 8 of lead, 15' of bismuth and 4 of cadmium), the melting point of which is 70 C.; and

Lipowitz metal (4 parts of tin, 2 of lead, 16

of bismuth and 3 of cadmium), the melting pointof which is`60 C.

According to the present invention, I may, fo

instance, provide annular parts separating the envelope into a plurality of elements, said annular separating parts being made of one of these metals.

` According to the embodiment illustrated by Fig. 2, the elements 8, 9, I0 and Il ofthe envelope are made of Woods metal.

These elements are connected with one another and with the nose l2 of the4 rocket throughan element containing still a certain amount of powder. Experiments proved, from this point of View, that it suffices, when nozzle 5 is axial and of the shape' of a frustum of a cone, to give it an apical angle of about 10.

It is further necessary to provide', between the end ofthe apex of each nozzle 5 and the corresponding ring 6, a thickness of powder sufficient in `order that the next element should not start burning before the first element, containing said nozzle 5, i-s wholly emptied of powder.

It will be readily understood that, with such an arrangement, oncecombustion of the powder lshall have been started, this combustion taking vbe made in various manners. ning to my invention, they should preferably conplace along concentric zones, the disengagement of heat produced by the combustion of the charge of chamber l for instance shall not act on element 8 as long as there remains upon the wall of said element a slight layer of powder' which constitutes a heat insulation, whereas, immediately after the combustion of this layer, said heat causes the element in question to melt.

of the invention, provide elements of the cartridge or envelope made of any metal, said elements consisting, as shown by Fig. 3, of four sleeves 8', 9', I0', Il' of copper,`or preferably of magnesium or of a light alloy oi.' this metal, said sleeves being connected with one another and with the nose of the rocket by annular elements made, at least partly, of Woods metal.

"Ihese elements made of Woods metal ,may

However, accordsist, as shown by Fig. 3, of rings I4 clamped to each of the two adjacent elements vto be assembled together.

Nozzle 5 must then be given a size .such that the particles of powder in contact with ring I4' given oiby the vvexhaust gases ensure a continuous or discontinuous elimination of these elements.

Finally, the projectile above described may further includel any suitable stabilizing device, such for instance as ribs or ns which are carried either by the elements intended to be eliminated, or by the portion of said projectile that is intended to remainas long as said projectile is moving along its path oi.'I travel.

The projectile above described avoids all the drawbacks above mentioned and it further presents many advantages, the chief of which are the following: v

It may include a number of combustion chambers as high as it is desired;

Furthermore, its construction is both simple and cheap..

A rocket according to the present invention may be combined with various devices, such, for

instance, as the following:

(a) Objects to be transported, for example the Y' end of a cable, or a message, introduced, for this purpose, in a recess provided in the head of the rocket: l

(b) Luminous signals: A

(c) Atmospheric or stratospheric sounding devices; and so on. H

Of' course, although the rocket shown by the drawing is of cylindrical shape, this is by no means a necessity, as the whole may of course be made of any desired shape.

Furthermore, the projectile might include not l. A rocket having a charge of powder divided into a plurality of parts, each of such parts having a recess therein, a casing surrounding said parts and formed of a plurality of metallic elements associated with the respective charge 'parts I may also, according to another embodiment.

some of which are fusible at the combustion temperature `of the powder forming the charge, said recesses being so located in each part of the charge that betweenveach recess and the associated fusible metallic element there is a layer of powder of sufcient thickness to prevent the melting of each fusible element until the part of the charge which corresponds thereto has been substantially completely burned.

2. A rocket having a. charge, of powder dividedr into a vplurality of parta-each of such parts having a recess therein, a casing surrounding said parts and formed of a plurality of metallic eleausgew o! the powder forming the charge. and iniusible rings joining said elements, said recesses being so located in each part-oi' the charge that between the recess and thewall of the fusible metallic element there is a layer of powder of suiicient thickness to prevent the melting of each fusible metallic element until the part of the charge ring there is a. layer of powder oi suicient thickness to prevent the melting of leach fusible ring until the part of the charge which is contained in the corresponding influsible section has been substantially completely burned.

4. A device as claimed in claim 3, in which said rings are formed of Woods metal.

5. A device as claimed in claim 3, vin which said infusible sections are formed of a light metal alloy.

6. A device as claimed in claim 3, in which said infusible sections are formed of magnesium.

7. In a device as claimed in claim 3, said recesses being so located that substantially all'the powder in each lsection burns before the burning of the powder in contact with the fusible rings. i


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2424934 *Nov 17, 1944Jul 29, 1947Kasper Melvin EProjectile
US2454096 *Jul 22, 1944Nov 16, 1948Schermuly Pistol Rocket AppMeans for discharging rockets
US2600678 *Mar 11, 1949Jun 17, 1952Olin Ind IncRocket powder
US2749705 *Jan 3, 1951Jun 12, 1956Gen ElectricFusible link jet motor control
US2920443 *May 25, 1955Jan 12, 1960Higginson JohnRocket propellant grain with helically grooved perforation
US2956401 *Jun 12, 1959Oct 18, 1960Kane Ernest MVariable thrust rocket motor
US3000597 *Aug 15, 1951Sep 19, 1961Bell Alfred JRocket-propelled missile
US3017746 *Jun 16, 1958Jan 23, 1962Phillips Petroleum CoDisposable elastic rocket case
US3032970 *Jan 25, 1957May 8, 1962Phillips Petroleum CoDisposable rocket motor
US3043221 *Jun 2, 1958Jul 10, 1962Swanser Frank HRocket propulsion method and means
US3067575 *Jan 2, 1959Dec 11, 1962Thompson Ramo Wooldridge IncDisposable rocket motor
US3122884 *May 19, 1961Mar 3, 1964Atlantic Res CorpRocket motor
US3137126 *Jan 11, 1961Jun 16, 1964North American Aviation IncMethod and means for forming a gaseous passage
US3142959 *Sep 11, 1959Aug 4, 1964Phillips Petroleum CoRange control of self propelled missile
US3151559 *Jun 12, 1962Oct 6, 1964Schermuly Pistol Rocket AppPyrotechnic propellant charge
US3172255 *Sep 26, 1961Mar 9, 1965United Aircraft CorpIgnition device
US3175497 *Feb 20, 1962Mar 30, 1965United Aircraft CorpSegmented rocket engine
US3199406 *Jun 21, 1961Aug 10, 1965Mb AssocIn-line launching
US3250216 *Jan 26, 1960May 10, 1966Zissimos A TypaldosAutophage rocket
US3292302 *Sep 14, 1964Dec 20, 1966Estes IndMultistage model rocket
US3319520 *Jun 23, 1965May 16, 1967Trw IncHigh speed low shock separation system
US3369365 *Oct 18, 1965Feb 20, 1968Henry A. OlsonSolid propellant rocket motor
US3397638 *Mar 8, 1961Aug 20, 1968Mb AssocRocket launcher
US3517615 *Jul 14, 1961Jun 30, 1970Us NavyExplosive wave shaper
US3554078 *Feb 10, 1969Jan 12, 1971Horvath Joseph SSpherical missile and launching means therefor
US3611935 *Oct 31, 1969Oct 12, 1971Us NavySmall caliber dual colored signal flare
US3811380 *Jan 23, 1968May 21, 1974Cava IndRocket and propellant therefor
US4723736 *Aug 18, 1986Feb 9, 1988Todd RiderRocket staging system
US4930421 *Jul 11, 1988Jun 5, 1990The Boeing CompanyPartitioned, fluid supported, high efficiency traveling charge for hyper-velocity guns
US5172875 *Mar 28, 1989Dec 22, 1992Israel FriedSpace launcher and method for launching objects into space
US6148610 *Jun 16, 1998Nov 21, 2000Aerospatiale Societe Nationale IndustrielleSolid propellant charge for a propulsion unit and propulsion unit equipped with such a charge
US7254936 *Apr 26, 2004Aug 14, 2007Knight Andrew FSimple solid propellant rocket engine and super-staged rocket
US8910576Jun 28, 2012Dec 16, 2014Mbda Uk LimitedBomb for deployment from an air vehicle
EP2602466A1 *Dec 7, 2011Jun 12, 2013MBDA UK LimitedA bomb for deployment from an air vehicle
WO2001038711A1 *Jun 20, 2000May 31, 2001Technanogy LlcEnd-burning rocket motor
WO2013001267A1 *Jun 28, 2012Jan 3, 2013Mbda Uk LimitedA bomb for deployment from an air vehicle
U.S. Classification60/225, 60/253, 102/378
International ClassificationF42B15/00
Cooperative ClassificationF42B15/00
European ClassificationF42B15/00