US2412134A - Projectile - Google Patents

Description

"TCU-Z400 Dec. 3, 1946. c. L. EKsERGIAN 2,412,134

PROJECTILE Filed F'Fb. 12. 1944 7 l JNVENTOR CaroluS LrELerq Lan.

BY l ATTORNEY Adrical elements 9 of combustible material.

Patented Dec. 3, 1946 PROJ ECTILE Carolus L. Eksergian, Detroit, Mich., assgnor, by mesne assignments, to the United States of America, as represented by the Secretary of War Application February 12, 1944, Serial No. 522,037

This invention relates to reaction propulsion devices, more particularly to projectiles and the like of the so-called rocket type.

Projectiles embodying a casing which encloses a reaction propulsion charge that discharges peripherally from the casing have previously been proposed, and the present invention is ydirected primarily to this type of projectile.

One of the objects of the present invention is to provide an improved nozzle or jet arrangement in a rocket type projectile which is economical to manufacture and in which means is provided for adjusting the area of the nozzle passage to provide for desired ranges of the projectile through Variation in the propelling pressure of the exhausting gases.

Another object is to provide an improved multijet rocket device in which separate propelling charges may be utilized.

With the above and other objects in View which will be 'apparent from the following 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 invention:

Figure 1 is a side elevation of the projectile to I" which the arrangement of the present invention is applied;

Figure 2 is an enlarged section of that portion of the projectile which is disposed within broken outline 2 of Figure 1, and

Figures 3 and 4 are transverse sections respectively taken substantially on the lines 3-3 and 4-4 of Figure 2.

Referring to the drawing, the projectile selected for illustration comprises a rearward tubular casing 5, a forward tubular casing v6 of greater diameter than the rearward casing 5 and a nose portion 'I which may contain an explosive charge, or are or chemical charge and the like (not shown). Suitable stabilizing fins 8 are carried by the trailing end of the casing 5.

Each of the casings contains a reaction propulsion charge in the form of a number of cylilr- T e elements '9 are supported in circumferentially spaced relation on a suitable cage Il) concentrically arranged within the casing. The particular manner of supporting the cage I forms no part of the present invention and therefore is not shown in detail.

Claims. (Cl. 60-35.6)

Extending axially within the casings 5 and 6 is a tubular member II supported at its forward end by the nose portion 'I and at its rearward end by the rearward end of the casing 5, as indicated in dotted outline in Figure 1.

In accordance with the present invention, a separate jet or Venturi passage is provided for each reaction propulsion charge comprised of the cylindrical elements 9. To this end, a tubular sleeve I2 surrounds the tube II, and surrounds the sleeve I2 and secured thereto by silver solder I3 or by any other suitable method, are forward and rearward annular elements I4 and I5, respectively, the element I4 being peripherally threaded to the internal wall of casing 6 and the element I5 being peripherally threaded to the internal wall of casing 5. The radial walls or webs of the elements I4 and I5 are of spider formation to provide the element I4 with openings |6 and the element|5 with openings I'I.

Interposed between the annular elements I4 and I5 and surrounding the sleeve I2 is an annular member I8 having an integral circumferential rearwardly and outwardly extending wall I9. As will be seen in Figure 2, this wall is of conical formation and projects rearwardly and outwardly between the adjacent spaced ends of the casings `5 and 6.

Threaded to the end of the casing 5 is an annular ring 20, and similarly threaded to the end of the casing 6 is an annular ring 2|. ward end of the ring 20 is tapered at 22, as shown in Figure 22, and this tapered surface 2 together with the inner surface 23 of the wall IES provides .a Venturi passage 2-4 communicating with the easing i5 through the openings I1 for the exhaust of the products of combustion of the reaction propulsion charge comprised of the rearward elements 9. The inner surface of the ring 2| is also contoured at 25 `to provide with the outer surface 26 of the conical wall I9 a Venturi passage 2'I in communication with the casing 6 through the openings I6 for the exhaust of the products of combustion of the reaction propulsion charge located within the casing 6.

There is thus provided continuously annular Venturi passagesy 24 and 2'I separated by the single wall |9,the one communicating with one casing and the other with the other casing.

The annular rings 20 and 2| are threadedly adjustable on the ends of the casings so that the areas of the Venturi passages 24 and 26, respectively, may be adjusted to provide for a predetermined propelling pressure. Suitable set The for- 3 screws 28 may be provided to lock the rings 20 and 2| in adjusted position.

It is to be noted that through the medium of the annular rings I4 and I5 and the annular sleeve I2 a rigid connection is provided between the adjacent ends of the two casings, despite the fact that these ends are completely separated. In fact the forward end of the rearward casing is rigidly supported from the rearward end of the forward casing.

The connection between the twol casings and the particular construction of the Venturi passage provides an arrangement which, although simple in construction, can be economically manufactured.

Various changes may be made in the arrangement and detailed construction of the parts 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. In a reaction propulsion device, a pair of coaxial tubular casings having their adjacent ends in spaced apart relation, each being arranged to \contain agninbnvstuilgleq reaction propulsion charge each having an axially apertured elementedwithin the end thereof 4which is adjacent the other casing, rigid means within said casings rigidly secured to said apertured elements, whereby to supportv ne casing from the other, and an annular wall extending at an acute angle to the axis of said casing through the space between said adjacent ends in spaced relation with respect to each of said `ends, said wall providng with each of said ends a peripherally continuous discharge passage.

2. In a reaction propulsion device, a pair of coaxial tubular casings having their adjacent ends in spacemapart relation, each being arranged to contain a combustible reaction :propulsion charge each having an axially apertured element secured within the end thereof which is adjacent the other casing,vmeans within said casings rigidly secured vto said apertured elements to support one casing from the other, and an annular wall extending at an acute angle to the axis of said casing through the space between said adjacent ends in spaced relation with respect to each of said ends, said wall providing with each of said ends a peripherally continuous discharge passage, said wall extending from between said apertured elements and preventing the ow of the products of combustion of the charge in each casing from entering the other casing.

3. In a reaction propulsion device, a pair of coaxial tubular casings having their adjacent ends in sgacednapart relation, each being arranged to contain La combustible reaction propulsion charge, each casing having an axially apertured element secured within the end thereof which is adjacent an end of the other casing, rigid means within said casings rigidly secured to said apertured elements, whereby .to support one casing from the other, and an annular wall extending at an acute angle to the axis of said casing through the space between said adjacent ends in spaced relation with respect to each of said ends, each of said ends and the adjacent surface of said wall being contoured to dene a circumferentially continuous Venturi passage,

4. In a reaction propulsion device, a pair of coaxial tubular casings having their adjacent ends in sp ed apartmrelation, each being arranged to con`a'n'cninbustible reaction propulsion @haargg each having" an axially apertured elementI :secured within the end thereof which is adjacent the other casing, rigid means within said casings rigidly secured to said apertured elements, whereby to support one casing from the other, and an annular wall extending at an acute angle to the axis of said casing through the space between said adjacent ends in spaced relation with respect to each of said ends, each of said adjacent ends having an annular ring threaded thereto, each of said rings and the adjacent surface of said wall being contoured to define a Venturi passag and said rings being threadably adjustable on said casings to alter the areas of said Venturi passages whereby to vary the pressures at which the gases resulting from the burning of the propulsion charges will exhaust from said Venturi passages.

5. In a reactionv propulsion device, a pair of coaxial tubular casings having their adjacent ends in space part-relation, each being arranged to contain a combustible reaction propulsion charge, each casing having an axially apertured element secured within the end thereof which is adjacent an end of the other casing, a member extending between said elements and being rigidly secured thereto, and a sleeve-like member surrounding said first mentioned member and extending between said elements, said sleeve-like member having a circumferential annular wall outwardly therefrom at an acute angle between said adjacent ends, said wall being spaced from both said ends and providing continuous annular passages therewith, the one for the discharge of the products of combustion of the charge in one'casing and the other for the discharge of the products of combustion of the charge in the other casing.

CAROLUS L. EKSERGIAN.

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