US2422721A - Rocket projectile - Google Patents

Description

June 24, 1947.

W. W. FARR ROCKET PROJECTILE Filed Oct. 13, 1944 m w r R T a m N r IF A m ,a I m \H@ NN.

Patentccl June 24, 1947 William W. Farr,

Grosse Pointe, Mlch., assig'nor by mesne assignments, to United States of 7 America Application October 13, 1944, Serial N0. 558,582

I 1 Claim.

This invention relates to rocket projectiles, more particularly to rocket projectiles oi the rotational type.

The invention is specifically directed to a type of rocket projectile which includes an elongated casing for containing the propelling charge and having a rearwardly opening discharge passage at its trailing end. In certain devices of this type which have been proposed heretofore, the discharge or Venturi passage for the discharge of the gases resulting from the burning of the combustible propelling charge, was axially arranged at the trailing end of the casing.

One of the objects of the present invention is to provide an improved means associated with the casing in such manner as to provide a plurality of Venturi passages located adjacent the inner wall surface of the casing whereby the gases will have a substantially straight flow toward the Venturi passages. I

Another object is to provide a rocket casing with an end closure means which provides with he casing wall, a plurality of circum'ferentially spaced Venturi passage in which the passages are so disposed as to impart rotation to the rocket projectile.

A further object is to so form the entrance end of the portions of the closure member which form the Venturi passages as to permit smooth flow of the gases into the Venturi passages.

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 combination 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 an elevational view of the rocket projectile, portions of the same being in section to show the entire rocket in detail;

Figure 2 is a rear end view of the projectile shown in Figure '1; and,

Figure 3 is a flattened section taken approximately on the circumferential line 3-3 of Figure 2, showing the contour of the portions which form the angularly disposed Venturi passages.

Referring to the accompanying drawing, the rocket projectile of the present invention includes an elongated casing I secured at its forward end to the main chambered projectile portion 2 which is arranged-"to contain the explosive charge (not shown). The propelling charge is 55 in the form of annular sticks 3 of combustible material which 'are supported by a cage member 4. The cage member is supported by a shoulder 5 disposed at the forward end of the casing I.

The open trailing end of the casing I is provided with a cup shaped end closure member 6, the walls of which are radially outwardly offset to provide a plurality of circumferentialLv spaced projecting portions 1 which are engaged with the inner wall surface of the casing I. The radial walls 8 and 9 or each portion 1 converge toward each other in a rearward .direction as shown in Figure 3. The straight portion of the wall 8 is of lesser length than the wall-9 and is joined to the wall 9 in a sweeping curve l0 whereby to provide a restricted throat ll between the wall 8 and the longer wall 9 of the next adjacent portion 1, thus forming an elongated Venturi passage. The closure member 6 is rigidly secured to the casin l preferably by rivets 12 extending through the casing l and the portion 1, there being two such rivets extending through each portion 1 as indicated in the drawing.

As will be seen in Figure 3, the portions 1 are so arranged that the axis of each Venturi passage is at an angle with respect to the axis of the casing l. Due to this angular disposition of the Venturi passages, the gases which result from the burning of the combustible charge sticks 3 flow through the Venturi passages under high pressure, and impart rotation to the projectile. 'I'heangular relationship of these passages is such as to give the desired speed of rotation to the projectile.

The closure member 1 may be formed in any suitable manner such as, for example, by die casting or'stamping the same from sheet metal.

The element I3 shown at the central portion of the closure member 1 functions to permit the .escape of gases in the event excessive pressures This element howare developed in the casing I. ever forms no part of the present invention.

The construction described can be economically manufactured and in operation the gases travel in a substantially straight path toward the Venturl passages and enter the passages with a smooth flow.

It is to be understood that various changes may be made in the detailed construction and arrangement of parts without departing from the spirit and substance of the present invention, the

' scope of which is defined by the appended claim.

What'is claimed is: In a rotational rocket projectile having an elonsite ends of said portions, the inner wall surface g of said casing together with the adjacent radial 5053747 walls of adjacent radially extendin portions and 15 51 365 the portions of said end closure between and 731340 joining said radially extending walls defining a 114144 plurality of circumferentially spaced Venturi passages, the axes or said passages being non-parallel with respect to the axis of said. casing, and means ior rigidly securing said and closure to said casins.

WILLIAM W. FARR.

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

FOREIGN PATENTS Country Date Great Britain 1877 Great Britain May 10, 1939 Great Britain Jan. 12, 1940 Germany Mar. 9, 1894 Australia Oct. 28, 1941

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