US2421552A - Casing and nozzle construction for rocket motors - Google Patents

Description

)Gal JH BUVME? eso-253 June 3, 1947. c. l.. EKSERGIAN CASING AND NOZZLE CONSTRUCTION FOR ROCKET MOTORS Filed Dec. 27, 1945 I N VEN TOR Carolus L. E kserg ion.

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ATTORNEYY 4 Patented June 3, 1947 CASING AND NOZZLE CONSTRUCTION FOR ROCKET MOTORS Carolus L. Eksel-gian, Detroit, Mich., assgnor, by mesne assignments, to United States of America Application December 27, 1943, Serial No. 515,836

Claims.

This invention relates to rocket-propelled devices, particularly to rocket devices of the multijet type.

The primary object of the present invention is to provide a rocket-propelled device with a casing and jet arrangement which is of simplified and economical construction and which, for the most part is formed from a minimum number of parts, particularly parts which can be formed by simple machine turning operations.

Another object is to provide a rocket arrangement, the component parts of which are capable of being quickly and easily assembled, and which is particularly adaptable for rapid production in large quantities.

With the above and other objects in view which will be apparent from the following detailed description, to those skilled in the art to which the invention appertains, the present invention consists in certain features of construction and combinations of parts to be hereinafter described with reference to the accompanying drawing, and then claimed.

In the drawing which illustrates a suitable embodiment of the present invention;

Figure 1 is a side elevation of a rocket-propelled device in which the features of the present invention are incorporated; and

Figure 2 is an enlarged longitudinal section through the casing portion of the rocket-propelled device to which the present invention is directed.

Referring to the accompanying drawing, the rocket-propelled device embodies the device litself indicated in the outline by numeral 5, which may be in the form of an explosive projectile, a flare device, chemical device or any other device desired to be projected through space, and a trailing portion 6 secured to the device 5.

The trailing portion 6 to which the present invention is directed contains the propelling charge 'I, shown in dotted outline, of suitable combustible material and includes a plurality of axially spaced propulsion jets.

According to the present invention, the trailing portion 6 is constructed of a plurality of tubular sections, including forward and rearward sections 8 and 9, respectively, and intermediate sections I. The forward end of the forward section 8 is provided with internal threads I I for threaded attachment to the device 5. Similarly, the rearward end of the rearward section 9 is provided with internal threads I2 for threadably receiving a stabilizing element I3. The sections 8, 9 and I0 are so arranged and formed that ing or brazing. The discharge apertures I5 are provided in the forward ends of the sections 9 and I immediately adjacent the threaded connections I6. The rearward ends of the sections 8 and I0 are formed with skirt portions I1 extending rearwardly from the threaded connections IE, which skirt portions I1 surround in circumferentially spaced relation not only the apertured zones but also rearwardly adjacent zones I3 of the sections.

In order to provide the pressure developing jets or Venturi passages I4, the external faces I9 of the rearwardly adjacent zones I8 are formed to a conical contour, the taper being of least diameter adjacent the apertures I5, and those inner face portions 20 of the skirt portions I'I which surround the conical faces I9 are similarly contoured to conical shape but to a greater angularity so that the annular passages defined by the faces I9 and 20 will be of gradually increasing area in the rearward direction. In addition, the inner face portions 2| of the skirt portions I'I are continuously recessed to provide chambers surrounding the apertures I5 which are of greater external diameter than the entrance opening into the spaces between faces I9 and 20. There is thus provided between the overlapping but spaced rearward and forward ends of adjacent sections an annular Venturi passage I4 closed at its forward end and opening to the atmosphere at its rearward end in an axial direction, the walls of which passage are defined by the surfaces of such adjacent sections.

The gases resulting from the burning of the propelling charge 'I within the sections discharge through the apertures I5 into the surrounding enlarged chambers and thence under pressure through the passages between the faces I9 and 20.

While the number of tubular sections shown is such as to provide three axially spaced Venturi passages i4, it is obvious that, on the one hand,

JUGI bll IIUUME additional intermediate sections l may be added to provide any desired number of passages, and on the other hand, the elimination of one intermediate section IU will provide a two-jet device and the elimination of both intermediate sections will provide a single-jet device.

The stabilizing device i3 comprises a plug 22 threaded into the end of section 9, to which plug a plurality of rearwardly extending vanes 23 are secured, the vanes 23 being surrounded by a sheet metal band 24. Any suitable type of stabilizing vanes may be employed, however.

Various means of supporting the rocket or propelling charge 1 may be employed. The charge illustrated in broken outline may, for example, be supported on a rod 25 having a head 26 at one end and being threaded at its other end into the plug 22.

It is thus seen that the trailing portion 6 constituting the rocket motor is of extremely simple construction and that the tubular sections may be formed from tube stock and machined by simple lathe or automatic machine turning operations. Such operations tend toward the provision of true concentricity and proper balance of the structure.

It is obvious that the operations of assembly are reduced to averitable minimum, which is extremely advantageous from the standpoint of quantity production during wartimes when manpower is at a premium.

Obviously, various changes may be made in the detailed construction and arrangement of the parts shown and described without departing from the spirit and substance of the invention, the scope of which is defined by the appended claims.

What is claimed is:

1. A rocket motor for rocket-propelled devices, comprising axially aligned, forward and rearward tubular sections adapted to contain a combustible propelling charge, the forward end of the rearward section being secured within the rearward end of the forward section, said forward section having an annular skirt portion surrounding the rearward section in circumferentially spaced relation and extending rearwardly from the region of securement of the forward and rearward sections to provide a rearwardly opening chamber, at least one aperture through the comprising axially aligned, forward and rearward tubular sections adapted to contain a combustible propelling charge, the forward end of the rearward section being secured within the rearward end of the forward section, said forward section having an annular skirt portion surrounding the rearward section in circumferentially spaced relation and extending rearwardly from the region of securement of the forward and rearward sections toprovide a rearwardly opening annular chamber, the rearward section having at least one aperture through the wall thereof opening directly into said chamber, the adjacent spaced wall surfaces of said sections which are rearwardly adjacent the aperture being conical and of greater spacing rearwardly of the aperture than adjacent the aperture.

3. A multi-jet rocket motor for rocket-propelled devices, comprising a, plurality of axially aligned tubular sections adapted to contain a combustible propelling charge, the ends of adjacent sections fitting one within the other and being secured together in circumferentially sealed engagement, the outer sections having integral annular skirt lportions extending axially from the regions of securement with and surrounding the inner sections in circumferentially spaced relation to provide annular chambers axially open at one end, said chambers being axially spaced apart, said inner sections having apertures-through the walls thereof opening into said chambers, and the spaced walls of the sections which dene said chambers being circumferentially contoured to provide prgpulsiondjets.

4. A't'bular structure for rocket-'propelled devices, comprising three or more tubular sections adapted to contain a combustible propelling charge, each section having forward and rearward ends and having its forward end threaded into the next forward section and each section having an integral annular skirt portion at its rearward end extending rearwardly beyond its threaded connection with the next adjacent rearward section in circumferential spaced relation with said last-named section to provide an annular rearwardly opening chamber, each section having circumferentially spaced apertures in its forward end opening into the surrounding chamber for the discharge of gases resulting from the burning of the propelling charge into said chamber, the spaced walls of each said chamber being contoured to dene a propulsion jet.

5. In a tubular structure for rocket-propelled devices and adapted to contain a combustible propellingucharge, a pair of axially aligned tublf' sections, one being tlmekadablyggglflfl@,YYIn the other, said other haiian integral annular skirt portion extending axially beyond the threaded connection in surrounding circumferentially spaced relation with said one section to define an annular chamber open at one end, said one section having a plurality of circumferentially spaced apertures through the wall thereof, opening into said chamber, and the spaced Walls of the sections rearwardly of said chamber being of conical shape to provide with said chamber a Venturi passage for the gases resulting from the burning of the propelling charge entering said chamber through said apertures.

CAROLUS L. EKSERGIAN.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 2,206,809 Denoix July 2, 1940 1,732,955 Swendeman Oct. 22, 1929 FOREIGN PATENTS Number Country Date 126,325 Great Britain May 15, 1919 166,583 Great Britain July 11, 1921 2,497 Great Britain Nov. 8, 1858

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