US2422720A - Rocket projectile - Google Patents

Description

June 24, 1947-, c. L. EKSERGIAN 2,422,720'- ROCKET PROJECTILE Filed Aug. 15, 1944 2 sheets-Sheet 1 i awww INVENTOR. Ca2 OZusL'iSergan/ .H T7 ORNE Y June 24r l947- c. l.. EKSERGIAN ROCKET PROJECTILE Filed Aug. 15. 1944 Illlllullllllglln -Y "Il," mi mi.

INVENTOR.

Patented June 24, 1947 ROCKET PRQJECTILE V(arolus L. Eksergfian, Detroit, Mich., assignor, by mesne assignments, to United States `of America Application August 15, 1944, Serial No. 549,543

(Cl. IIR-49) .6 QIaimS.

This invention relates to projectiles, more particularly to projectiles of the soecalled rocket type, it ibeing one 'of the objects to provide a rocket VDTDiec-til-e `casing capable of being expeditiously fabricated from a plurality of vltubuiar sections.

Another v'object is to provi-de a rocket projectile body fabricated from a plurality of tubular sections lin which the sections are performed and overlapped `in such manner -as to provide 'a plurality of axially spaced peripheral passages 'for the discharge of the gases resulting from the "burning of the rocket charge.

A further 'object is to provide a rocket projectile which can v'be easily manufactured and :assembled With the a'iooveand 'other obj-ects'in view, which will 'be apparent to those skilled in the art to which the invention appertains, the present invention lconsists of certain -features of construction and combinations of parts to be hereinafter described with reference to the accompanying drawings, and then claimed.

'In 'the drawings which Villustrate suitable embodiments of the present invention:

.Figure 'l is .a side 'elevation of one `form of the projectile;

Figure 2 is a-n enlarged `section taken substantially on line '2--2 of Figure 1;

'Figure '3 is an enlarged section taken substantially on line 3-13 of `Figure 1,;

vFigure 4 is an enlarged side elevation of one .of `the sections of the projectile casing;

Figure 5 is a fragmentary longitudinal'section through the connection of adjoining sections of modiiied formation;

Figure 6 is an enlarged 'transverse section taken .substantially on the line -B of Figure 5;

Figure 7 is a section similar te vFigure :5 ibut of a further modified construction.;

Figure 8 is an enlarged section 'taken substantially on line 8 8 of Figure 7 Figure A9 `is a perspective View of one 4of the 'button-like elements used in. the construct-ion of Figures 7 and 8;

Figure 10 is a section similar to Figures 5 and '7 but in which the sections are of a further modilied construction, and

Figure 1l is an enlarged section taken substantially on line I I--I I of Figure 10.

Referring to the accompanying drawings, the rocket projectile embodies, in general, a nose portion or body l adapted to contain an explosive charge (not shown) a tail portion 2, forward and rearward sections 3 and 4, respectively, and a plurality of intermediate sections 5.

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'In the construction shown in Figures 2, 3, and 4, thetu'bular sections and 5 are of frusto-conical shape, the smaller diametered end o'f .theforward section 3 being threadably secured tothe trailing end o'f the leading section as 'indicated at '6 in Figure V3. The tail piece 2, which is of Venturi formation and carries a number of stabilizing varies .1J is threa'dably secured to the rearward end of the rearward section 4 as shown .in

lFigure `2. The forward ends of the .section 4 .and

the sections 5 are embossed to provide a plurality of circumferentially spaced Venturi-.forming portions 8, each of which is rounded .at its forward end and tapers rearwardly. The forward endsof these .sections are nested within the rearward ends of the adjoining sections, .the embossed .portions 8 seating firmly `against the 4inner surfaces of the adjoining sections and'being secured thereto by rivets lIl. The tapering sides of the embossed por-.tions B and .the .surrounding .surfaces of the adjoining sections thus form a number of .circumierentially spaced Venturi passages II) for the 4discharge Yof the propelling gases .resulting from the burning .of the rocket charge. The rocket charge as here shown is inthe .forni of a plurality vof annular powder sticks .I IV supported on rods i2. The rods .I2 are .carried by .suitable end plates I3 .as shown in Figures 2 and 3. The rocket charge .and its ,manner of support, however, .forms no part .of the present invention.

The longitudinal .axes .of the embossedportions 8 Aare inclined relative to the axis of the sections whereby .the Adischargl-ng gases `will impart rotation -to the projectile. Ii, however, rotation is not desired, the longitudinal axes .of the embossed portions may 1be lparallel to the .axis .of the sections. l

Whereas in .Figures 2 and the radial walls of the Venturi passages I=Il are substantially par- 40 allel and the Venturi .throat is produced circuiti- .ferentially only, the modified construction of Figures 10 and 11 provides Venturi passages M having throat produced both circumierentially and radially, In this case, that portion I5 of a section 5 which lies within an adjoining section is made substantially cylindrical and the embossed portions I6 are so formed that the passages I4 increase in area both circumferentially and radially.

In some cases it may be desirable, as in a step rocket, to employ straight tubular sections I'I of gradually reduced diameters, as illustrated in Figures 5 and '7, in lieu of the frusto-conical sections of Figures 1 to 4, 10 and 11. In Figures 5 and 6, in order to provide Venturi passages I8 of 3 greater area, the overlapping ends of adjoining sections l1 are both embossed, the inner section having outwardly projecting embossed portions I9 and the outer section having correspondingly shaped inwardly projecting embossed portions 20. The embossed portions I 9 and 20 rmly abut each other and are secured together as in Figures 2 and 3 by rivets 2l. The embossedv portions I9 and 2U may be inclined, if desired, as in Figure 4, so that the discharging gases will impart rotation to the projectile.

By arranging the parts and Venturi passages in the manner described it is possible for a given diameter of projectile to use a mass of the rocket charge greater than has been heretofore possible with the result that greater velocity and, hence, greater range and striking power are attainable.

Depending on the length of the projectile or the amount of rocket charge desired any number of sections may be utilized.

Various changes may be made in the detailed construction and arrangement of the parts described Without departing from the spirit and substance of the invention, vthe scope of which is defined by the appended claims,

What is claimed is:

l. In a rocket projectile, a plurality of tubular sections, the adjacent ends of adjoining sections being overlapped with each other, one of said sections at its overlapped region having a plurality of circumferentially spaced embossed portions radially abutting the adjacent section, said embossed portions being contoured to dene a plurality of circumferentially spaced Venturi passages With the overlapped regions of said sections, and means securing the adjoining sections together through said embossed portions.

2. In a rocket projectile, a plurality of tubular sections, the adjacent ends of adjoining sections being overlapped with each other, one of said sections at its overlapped region having a plurality of circumferentially spaced embossed portions radially abutting the adjacent section, said embossed portions being contoured to denne a plurality of circumferentially spaced Venturi passages with the overlapped regions of said sections, and means securing the adjoining sections together through said embossed portions, the walls of each of said passages being divergent in an axial direction.

3. In a rocket projectile7 a plurality of tubular sections, th'e adjacent ends of adjoining sections being overlapped with each other, one of said sections at its overlapped region having a plurality of circumferentially spaced embossed portions radially abutting the adjacent section, said embossed portions being contoured to define a plurality of circumferentially spaced Venturi passageswith the overlapped regions of said sections, and means securing the adjoining sections together through said embossed portions, the walls of each of said passages being divergent both in an axial and a radial direction.

. 4. In a rocket projectile, a plurality of tubular sections, the adjacent ends of adjoining sections being of different diameters and the smaller diametered end extending within th'e larger diametered end, said smaller diametered end having a plurality of circumferentially spaced embossed portions extending outwardly toward and abutting the surrounding section, and means securing said embossed portions to the surrounding section, said embossed portions being contoured to define Venturi passages with the adjoining embossed portions and the surrounding section.

5. In a rocket projectile, a, plurality of tubular sections, the adjacent ends of adjoining sections being of different diameters and the smaller diametered end extending within the larger diametered end, said smaller diametered end having a plurality of circumferentially spaced embossed portions extending outwardly toward the surrounding section and the surrounding section having a, corresponding number of correspondingly shaped circumferentially embossed portions abutting the embossed portions of th'e surrounded section, and means securing said sections together through said embossed portions, said embossed portions being contoured and cooperating with each other to define a plurality of Venturi passages.

6. In a rocket projectile, a plurality of frustoconical hollow sections having a common axis, each section having its smaller diametered end surrounded by the larger diametered end of an adjacent section, at least one of the surrounded and surrounding ends having a plurality of circumferentially spaced embossed portions radially abutting the other, and means securing said sections together through said embossed portions, said embossed portions being contoured to deine Venturi passages leading from the interior of said sections.

CAROLUS L. EKSERGIAN.

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

FOREIGN PATENTS Number Country Date 73,840 Germany June 7, 1893 516,865 Great Britain Jan. 12, 1940

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