US2821137A

US2821137A - Military rocket structure

Info

Publication number: US2821137A
Application number: US281947A
Authority: US
Inventors: Lyon George Albert
Original assignee: Individual
Current assignee: Individual
Priority date: 1952-04-12
Filing date: 1952-04-12
Publication date: 1958-01-28
Anticipated expiration: 1975-01-28

Description

G. A. LYON MILITARY ROCKET STRUCTURE Jan. 28,- 1958 Filed April 12, 1952 G'earye A/berz Lyon States Pat lOf ce MILITARY ROCKET STRUCTURE George Albert Lyon, Detroit, Mich.

Application April 12, 1952, Serial No. 281,947 15 Claims. (Cl. 102-38) The present invention relates to improvements in rocket structures especially adapted for warfare uses.

An important object of the present invention is to provide an improved projectile unit of the rocket type.

Another object of the invention is to providein a projectile unit an improved rocket-type construction wherein a self-propelling projectile is supported in a cartridge container from which it is initially fired at comparatively low velocity.

A further object of the invention is to provide an improved rocket-type projectile assembly having novel means for cooperation with a container shell casing prior to firing and functioning after firing to cooperate with a rifled gun barrel.

Still another object of the invention is to provide .a novel rocket-type projectile having a unique tail structure of multi-function utility operable in several operative phases of the projectile.

According to the general features of the invention there is provided in a rocket-type projectile assembly, a projectile unit having a resilient radially expansible tail portion, and a supporting cartridge casing for the projectile having a recessed internal wall portion retainingly interengageable with said expansible tail portion.

In a projectile unit of the character described, a

projectile having a tail portion laterally movable relative to the body of the projectile, a shell casing for supporting the projectile having means therein inter-engageable with said movable tail portion for retaining the projectile in predetermined axial position within the shell casing, said movable tail portion having means thereon cooperable with rifling in the barrel of a gun through which the projectile may be fired. According to further features of the invention, there is provided in a rocket-type military projectile assembly, a shell casing having a laterally opening recess'in the internal side wall thereof, a rocket projectile housed within the casing, and a tail portion on said rocket projectile comprising an expansible spiral spring unit engageable within said wall recess of the casing for retaining the projectile in'position within the casing, said spiral spring structure having spirally directed vanes operable in the propelled movement of the projectile after leaving the casing to effect spinning of the projectile about its axis as the projectile moves through the air.

Other objects, features and advantages of the present invention will be readily apparent from the following detailed description of a preferred embodiment taken in conjunction with the accompanying drawing in which:

Figure 1 is a longitudinal diametrical sectional detail view through a military rocket structure according to the present invention;

Figure 2 is an enlarged fragmentary transverse sectional view taken through the tail portion of the rocket projectile substantially on the line IIII of Figure 1;

Figure 3 is a fragmentary sectional detail view taken substantially on the line HI-III of Figure 2;

Figure 4 is a fragmentary detail view of the tail portion 2,821,137 Patented Jan. 28, 119 5 8 of the projectile showing the same as it appears when traveling through a rifled gun barrel; and

Figure 5 is a fragmentary transverse sectional detail view taken substantially on the line VV of Figure 4.

As shown on the drawings:

The military projectile unit of the present invention is of the type which is made up as a self-contained unit within a protective and supporting metallic cartridge casing 10 which also supports a firing charge behind the projectile for propelling the projectile from the casing for either direct launching from the casing or for propelling the projectile into a gun barrel. To this end, the shell casing 10 is preferably an elongated generally cup-shaped metallic shell which may be a drawn shell'or a forging or a casting as preferred having a generally cylindrical internal wall and being of a length substantially greater than a projectile 11 supported within the casing.

One end of the casing 10 is preferably headed to provide a symmetrically tapered butt or end closure 12 having a centrally indented embossment 13 having a central aperture 14 and adapted to suppport a primer through the medium of which an explosive propellent charge within the bottom portion of the casing is fired in service. At its opposite end, the casing is preferably formed with an outwardly flaring mouth flange 15 defining an open mouth for the casing.

The projectile 11 comprises as principal components a tapered head shell 17 and a motor shell 18 assembled with the head shell. The head shell 17 may be formed as a drawn metallic unit and has at its tip end an inturned integral generally cylindrical flange 19 defining a fuse receiving and assembly opening in the tip of the head shell. At its rear end, the shell 17 is open and is assembled fixedly about a bulkhead crown portion 20 on the forward end of the motor shell 18 which may also be formed as a drawn shell of generally inverted cupshape. The bulkhead 20 is preferably dome-shaped and has a peripheral inset annular groove 21 providing a shoulder with which the lower end margin of the head shell 17 is engaged fixedly in suitable manner as in brazed or welded relation or in threaded inter-engagement if preferred. Beyond the shoulder groove 21, the external wall of the motor shell 18 is preferably of a diameter slightly less than the internal diameter of the casing 10, and the tail, or lower end portion of the head shell 17, is also of substantially the same diameter as the motor shell so as to clear the internal wall of the casing 15.

For supporting the projectile unit 11 in predetermined intermediate relation within the casing 10, the motor shell 18 is provided with a tail piece or flange 22 formed as an expansible, resilient spring structure which is laterally movable relative to the remainder of the projectile for retaining inter-engagement within a radially out wardly bulged intermediate annular portion 23 of the casing shell 10 providing an inwardly opening recess in the internal wall of the shell casing. The tail piece 22 is provided with a uniform series of parallel co-extensive spirally extending slots 24 extending a predetermined dis-j stance generally longitudinally of the tail portion of the shell 18 and short of the distal or lower end extremity of the shell, and which extremity is preferably of the same outside diameter as the main body of the motor shell. The slotted area of the tail portion 22 is exthrough the open mouth of the casing 10 and sliding the tail piece under compressed tension through the length of the casing 10 from the mouth to the recess bulge 23;

until the spring portion of the tail piece 22, or more properly the set of expansible spring ribs 25 intervening between the slots 24, snap into the annular retaining recess in the casing and thus hold the projectile 11 in retained relation intermediately within the casing 10.

It will be understood, of course, that before assembly of the projectile 11 within the casing 10 is effected, the projectile is loaded with an explosive charge within the head shell 17 and with a propellent charge in the motor shell 18, while the butt end portion of the casing 10 is loaded with an initial firing propellent charge.

Upon firing of the initial propellent or ejector charge in the butt end portion of the shell casing 10, propellent force is built up against a tail bulkhead 27 assembled with the motor casing 18 immediately forwardly or upwardly from the ends of the bowed spring ribs 25. In a preferred form, the bulkhead member 27 comprises a generally cup-shaped disk having an annular peripheral cylindrical wall 28 secured to the internal wall of the casing 18.

Ignition of the propellent charge within the motor casing 18 occurs as a result of burning of the initial propellent charge within the casing 10 by way of a nozzle 29 which preferably opens centrally rearwardly from the bulkhead member 27 and may, as shown, be formed as an integrally stamped portion of the bulkhead member. The nozzle is preferably of generally venturi shape flaring rearwardly and having an intermediate restricted acceleration promoting throat 30.

Propulsion of the projectile 11 from the casing 10 causes the spring ribs 25 to compress and release the tail portion 22 from the retaining recess or groove in the casing 10, and projection of the projectile from the mouth of the casing 10 whence it may be directly projected into flight toward a target, continuous forward motion being accelerated by the force of the burning propellent charge within the motor casing 18 from which the products of combustion issue through the restricted orifice 29.

Since for accuracy of flight, it is desirable that the projectile 11 spin about its axis, means are provided for cooperation with the air through which the projectile moves to assure the spinning motion. To this end, the spring ribs 25 of the tail piece of the projectile are preferably provided with vanes 31 which project inwardly on the forward portions of the spring ribs. Through this arrangement, when the spring ribs 25 expand after leaving the confines of the shell casing 10, the forward portions of the spring ribs carrying the vanes 31 extend into the slipstream of air through which the projectile is moving and the vanes 31 react to the slipstream to impart whirling motion to the projectile. It will be ob served, of course, that the slots 24 are of ample Width to permit substantial volume of slipstream air to pass therethrough toward the interior of the tail piece 22. Moreover, the high velocity stream of gases issuing from the nozzle 29 will induce a generally inward deflection of slipstream air passed and into operative engagement with the generally spirally directed vanes 31. By having the vanes formed only in the forward half portion of the ribs 25, interference with flexing of the ribs is avoided.

Where it is found desirable to fire the projectile 1?. through a gun barrel 32 (Figs. 4 and the ribs 25 and the slots 24 cooperate to guide the projectile through the gun barrel and the expansible spring ribs 25 afford braking resistance for build up of propellent pressure hehind the projectile. In addition, where the gun barrel 32 is provided with spiral rifling ribs 33, the spring ribs 25 engage within the grooves between the rifling ribs and the rifling ribs engage through the slots 24. As a result, the long forwardly directed edges of the ribs 25 ride along the sides of the respective rifiing ribs 33 and guide the projectile to impart spining motion thereto as it travels through the gun barrel 32. It will be observed that the vanes 31 provide smooth faces opposing and slidably engaging with the riding ribs 33. i

When the projectile leaves the gun barrel, spinning as impelled by inter-engagement of the rifling ribs with the spring ribs 25, the spring ribs, of course, snap into expanded position and the vanes 31 acted upon by the slipstream continue the forced spinning of the projectile about its axis as it travels its trajectory toward the target.

It will be understood that modifications and variations may be effected without departing from the scope of the novel concepts of the present invention.

I claim as my invention:

1. A projectile having a tail portion including expansible generally longitudinally extending outwardly bowed spring strips laterally movable relative tothe body of the projectile, and a shell casing for supporting the projectile having means therein inter-engageable with said spring strips for retaining the projectile in predetermined axial position within the shell casing, said spring strips having elongated generally helically angled peripherally directed edges thereon cooperable with rifling in the barrel of a gun through which the projectile may be fired.

2. In a rocket-type military projectile assembly, a shell casing having a laterally opening recess in the internal side wall thereof, a rocket projectile housed within the casing, and a tail portion on said rocket projectile comprising an expansible spiral spring structure engageable within said wall recess of the casing for retaining the projectile in position within the casing, said spiral spring structure having spirally directed vanes operable in the propelled movement of. the projectile after leaving the casing to effect spinning of the projectile about its axis as the projectile moves through the air.

3. A projectile unit comprising an elongated internally generally cylindrical shell casing having a tapered end closure providing a primer support and an opposite open mouth defined by an outwardly flaring funnel-like solid cam flange, a rocket-type projectile having a tapering forward portion and an elongated motor casing portion, said motor casing portion having a rear bulkhead provided with an exhaust nozzle, a laterally expansible spring tail structure on said projectile, and internal shoulder means in said shell casing spaced from said end closure and inter-engaged by said spring tail structure to hold the projectile in predetermined longitudinal position within said shell casing, said cam flange at the mouth of the shell casing being engageable by said spring tail portion to compress the same during assembly of the tail portion into the casing.

4. In a shell casing for use in a projectile assembly, an elongated shell, one end of the shell being substantially closed by a tapering butt structure having an inset primer boss, and the opposite end of the shell casing having an outwardly flaring substantially frus'to-conical bell mouth flange.-

5. In a projectile structure, a projectile body member having thereon a tail piece comprising therein a series of slots of limited length extending short of the terminal margin of the tail piece and defining therebetween a series of generally longitudinally extending ribs, said ribs extending laterally beyond the normal diameter of said body portion, said terminal margin providing a fixed diameter continuous annulus.

6. In a projectile structure of the character described, a projectile body memberhaving a tail piece provided with a series of parallel spiral slots extending short of the terminus of the tail piece, said slots defining therebetween a series of spiral ribs, said r'ibs being resilient and bowed outwardly, said tail piece terminus providing a ring projecting rearwardly' beyond the adjacent ends of said ribs.

7. In a projectile structure of the character described, a projectile body member having a tail piece provided with a series ofparallel spiral slots extending short of the terminus of the tail piece, said slots defining'therebetween a series of spiral ribs, said ribs being resilient and bowed outwardly, said ribs having vanes thereon extending angularly relative to the ribs.

8. In a projectile construction, a tail piece comprising a series of spaced parallel bowed elongated elements angled in spiral relation to the axis of the projectile and bowed radially outwardly, the forward portions of the spiral elements having inwardly directed vanes on the forwardly directed edges thereof for reaction to slipstream air in flight of the projectile to impart spin to the projectile about its axis.

9. In a rocket projectile, a body structure including a rear motor chamber portion having a rear bulkhead provided with a central exhaust nozzle, and a guiding tail piece projecting rearwardly from said motor chamber portion in spaced surrounding relation to said nozzle and having a series of spaced generally spiral ribs defined by substantial intermediate spaces, each of said ribs having on the forward portion of the forwardly directed edge thereof an inwardly directed air vane for reacting to slipstream air as induced to deflect inwardly by suction of exhaust from said nozzle to impart axial spin to the projectile in flight.

10. In a projectile construction, a shell having longitudinally spaced annular solid portions separated by a laterally outwardly bowed section, said bowed section being sub-divided into a symmetrical series of resilient bowed generally longitudinally extending spring ribs expansible and contractible in radial direction with corresponding relative axial movement of said annular portions.

11. In a projectile construction, a thin wall shell member having an annulus section thereof provided with radially outwardly bowed resilient rib springs constructed and arranged to engage within rifling grooves of a gun barrel and follow the same for imparting axial spin to the projectile upon firing, said springs having turned edges for smoothly engaging the gun barrel rifling.

12. In a projectile construction, a tail piece comprising a series of spaced parallel bowed elongated elements angled in spiral relation to the axis of the projectile and bowed radially outwardly, the forward portions of the spiral elements having turned edges for smoothly engaging the rifling of a gun barrel through which the projectile may be fired, to impart spin to the projectile about its axis.

13. In a rocket projectile, a body structure including a rear motor chamber portion having a rear bulkhead provided with a central exhaust nozzle, and a guiding tail piece projecting rearwardly from said motor chamber portion in spaced surrounding relation to said nozzle and having a series of spaced generally spiral ribs defined by 6 substantial intermediate spaces, said ribs having on the forward portion thereof vane surfaces for reacting to slipstream air as induced to deflect inwardly by suction of exhaust from said nozzle to impart axial spin to the projectile in flight.

14. In a projectile assembly comprising a tapered head portion, a motor casing secured to the rear end portion of the head portion, said motor casing comprising a shell having a tail portion integral in one piece therewith and sub-divided into a plurality of generally longitudinally extending radially expansible bowed resilient ribs, with the maximum arched portions thereof normally projecting radially beyond the diameter of the motor casing and with the ends of the ribs directed inwardly relative to the perimeter of the motor casing and connected together by a terminal extremity portion of the casing.

15. In a projectile structure including a body shell mem ber with a nozzle structure directed from the tail end of the body member, and said body member having thereon a tail piece provided with a series of slots of limited length extending short of the terminal margin of the tail piece and defining therebetween a series of generally longitudinally extending ribs, said ribs intermediately thereof extending laterally beyond the normal diameter of the body portion, said terminal margin projecting beyond the tail portion of said body member and beyond the nozzle structure and providing a fixed diameter continuous annulus alfording a rearward opening for discharge from said nozzle structure.

References Cited in the file of this patent UNITED STATES PATENTS 7,147 Perry Mar. 5, 1850 27,791 Foster Apr. 10, 1860 36,001 Goodrem July 29, 1862 511,418 Gathman Dec. 26, 1893 1,417,460 Driggs May 23, 1922 2,029,490 Lane Feb. 4, 1936 2,397,144 Anzalone Mar. 26, 1946 2,421,752 Jones June 10, 1947 2,470,489 Hopkins May 17, 1949 2,496,316 Skinner et al Feb. 7, 1950 FOREIGN PATENTS 2,826 Great Britain of 1856 446 Great Britain of 1863 347 Great Britain of 1878 306,404 Germany 1920 118,924 Sweden 1947