US2412173A

US2412173A - Projectile

Info

Publication number: US2412173A
Application number: US523415A
Authority: US
Inventors: Winslow B Pope
Original assignee: Individual
Current assignee: Individual
Priority date: 1944-02-22
Filing date: 1944-02-22
Publication date: 1946-12-03
Anticipated expiration: 1963-12-03

Description

ecu 3, W. B. PROJECTILE Filed Feb. 22;. 1944 INVENTOR. Wznslow 19. P

flTTORNEY Patented Dec. 3, 1 946 PROJECTILE Winslow B. Pope, Detroit, Mich., assignor, by mesne assignments, to United States of America 2 Claims. 1

This invention relates to projectiles and devices of the type adapted to be projected through space by the reaction propulsion principle.

Various devices of the reaction propulsion or rocket type have been heretofore proposed, among which there is one type which embodies a tubular casing secured to the rearward end of the projectile proper for housing the propelling charge and having its trailing end contoured to provide an axially opening Venturi passage. In such a device, the gases flowing through the Venturi passage, due to uneven burning of the charge, or for other reasons, may flow slightly off center through the Venturi passage. Such ofi-center flow or shifting of the flow of gases from truly axial flow during the flight of the projectile will cause the projectile to deviate from a true predetermined course.

The object of the present invention is to provide a new and novel arrangement whereby to insure an even flow of gases from a rocket type projectile.

Another object is to provide a rocket type projectile with a rotary gas discharging device adapted to provide for uniform axial flow of the propelling gases.

A further object is to provide a novel arrangement for preventing premature bursting of the casing which houses the propelling charge.

With the above and other objects in view, which will be apparent from the following descriptions to those skilled in the art to which the invention appertains, the present invention consists of 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, partially in section, of the rocket projectile,

Figure 2 is an enlarged rear end view of the projectile shown in Figure 1, and

Figure 3 is a transverse section taken approximately on line 3--3 of Figure 2.

Referring to the accompanying drawing, the rocket device selected for illustration includes a main projectile body 5 having a chamber 6 for the reception of an explosive or other charge. A tubular casing l is threadably or otherwise suitably secured to the rearward end of the body 5, the casing having an internal shoulder B which supports a. plate-like member 9. The platelike member 9 supports a cage, composed of the rods Ill and interconnecting end ring I I, which carries the propelling charge, which as shown in the drawing may be in the form of sticks I 2 of slow-burning powder or other suitable combustible material.

In accordance with the present invention, the conventional single axially opening Venturi passage, such as shown in the copending application, Serial No. 487,689, filed by Warren H. Farr on May 20, 1943, has been replaced by a multi-jet rotary device l3.

To this end, the rearward end of the casing 5 is slightly reduced in diameter and provided with an internal shoulder l4. Inserted from the rearward end of the casing and seated against the shoulder M is an annular ball thrust bearing 15. The cylindrical rotary dc /ice l3 seats against the outer race of the bearing I5 and is mounted within the rearward end of the casing for free rotation by means of circumferentially surrounding rollers l6, commonly known as needle bearings, the bearings I6 engaging with the inner wall of the rear end of the casing 5 and being seated in a circumferential recess l1 formed in the peripheral wall of the rotary device IS.

The device I3 is retained within the casing by means of a radially inwardly flanged ring 22 externally threaded to the end of the casing as shown in the drawing.

The rotary device I3 is provided with a plurality of uniformly circumferentially spaced Venturi passages I8 arranged therein at an angle to the axis of the device I3. The passages It may be formed by drilling and then taper reaming the drilled openings from the opposite sides of the rotary device to provide the restriction ill in the passages l8.

It will be obvious that the flow through the passages l8 of the products of combustion of the combustible propelling charge will, by reason of the angularly arranged passages I8, cause the device l3 to rotate. Since the device I3 is coaxial with the casing 5 and the gases discharge through the equally spaced jets, each the same distance from the axis of rotation, the gases will leave the device in an annular rotating stream truly coaxial with the casing thus insuring a uniform annular propelling pressure at all times.

In order to prevent the building up of a pressure within the casing prematurely which might tend to rupture the casing before the'device has left the projector and thereby cause serious damage, the rotary device I3 is provided with a central passage 20 which is counterbored at its inner end to receive a plate 2| having a press fit therewith. The plate 2| is of less yield strength than the casing wall and is oi such predetermined strength that in the event of the building up of abnormal or excessive pressures within the casing, it will rupture or blow out to relieve the pressure within the casing before it can reach a value which will rupture the casing.

The present invention is applicable to any re action propulsion device whether it be for an explosive projectile, a chemical device or any other arrangement adapted to be projected through space.

Various changes may be made in the detailed an annular end thrust bearing within said end in advance oi. said member and engaged therewith, and means secured to said end for retaining said member in said end, said member having a plurality of discharge passages extending 1ongitudinaliy therethrough, said passages being inclined relative to the axis of rotation of said member and said axis oi rotation being coincident with the axis of said casing.

2. In a reaction propulsion device, a casing for housing a combustible propelling charge, a cylindrical member within one end of said casing and having a plurality of circumferentiaily spaced Jet passages extending therethrough into communication with the interior of said casing, said memher having an axial opening therein, and a plate closing said opening at the end adjacent the interior of said casing, said plate being or a material having a yield strength less than the yield strength of said casing whereby incident to excessive pressures within said casing said plate will rupture prior to said casing.

WINSLOW B. POPE.