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Dee-10, 1946. 2,412,266 R. W. HOAGLAND REACTION PROPELLED DEVICE Filed Feb. '22, 1944 ‘ mmvrox Reginald W?oagland BY ' Patented Dec. 10, 1946 ' 2,412,266 Fries UNlTED - STATS rig _ 2,412,266 REACTION PROPELLED DEVICE Reginald W. Hoagland, Detroit, Mich". assignor, by mesne assignments, to United States of ' America ‘ Application February 22, 1944, Serial No. 523,412 2 Claims. (Cl. 102-49) . invention relates to reaction propelled ‘devices, such as, for example, _explosive.projecr tiles, smoke or chemicalshells, ?ares andthe, like. \ . . Various devices of this type, commonly known as “rocket shells,” have been proposed heretofore, among which is. one‘ that embodies a tubular casing secured to the rearward end of the pro jectile body and having its rearward end swaged , 2 ‘o , which is in the form of sticks I! of slow burning powder or other suitable combustible material is ‘ carried by the cage ll.’ The rearward end of the casing 8 is swaged ' down or otherwise reduced in diameter to provide an axially opening Ventu‘ri passage I5, which from its throat l8 ?ares rearwardly and out‘ wardly in gradually increasing diameter, the wall thickness of the casing remaining substantially or otherwise reduced in diameter to provide an 10 the same throughout theulength of the casing. axially opening Venturi passage, the wall of the As is well known, the expansion of the gases casing being of substantially uniform thickness resulting‘ from the burning of the propelling throughout. As a__ result of the reduction in charge and flowing through the Venturi passage diameter of the rearwardv end of the casing, a l5 creates the propelling pressure. circumferential pocket is formed which, due to 15 In accordance with ‘the present invention, a I the vacuum produced therein during ?ight, tends number ‘of vanes l8 are secured by weld material to slow up the speed of travel of the projectile. I‘! to the rearward end of the casing as shown One of the objects of the present invention is in the drawing, the same following the‘contour to provide a novel means for relieving a rocket of the region of reduced diameter." These vanes shell of the above type of the vacuum produced 20 are arranged at an angle to *the axis of the pro- - by the circumferential rocket whereby to de crease its ?ight resistance. jectile and each pair form with the external sur- _ ' face of the reduced end region a pocket or chan Another object is to provide a rocket shell with nel l9 open at its rearward end. The wall of the a novel arrangement for utilizing a portion of casing where the latter starts to reduce in diam the propelling medium to rotate the shell con 25 eter is provided with a numberiof circumferen tinuously during ?ight whereby to stabilize the shell to. insure truer ?ight and to eliminate the necessity of providing stabilizing ?ns extending V outwardly from the body of the projectile. 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 of cer tially spaced apertures 20, there being one such aperture for each such channel. Each aperturew 20 is closelyadjacent to the forward end of one‘ vane of each pair. A'portiomof the gases re sulting from the burning of the propellant thus ?ow under pressure through the apertures 20 and by reason of the angularrelation of the vanes - with respect to the axis of the projectile im tain features of construction and combinations" pinge upon the vanes 18 and thus cause- the of parts to be hereinafter described with reference 35 projectile to rotate during its ?ight whereby to to the accompanying drawing, and then claimed. stabilize itself for true ?ight. The axially rear In the drawing which illustrates a suitable wardly ?aring external surface of the reduced embodiment of the present invention: end portion and the vanes provide in effect chan Figure 1. is a side elevation of the projectile, ' partially in section to show the interior arrange 40 nels for the smooth evenly distributed ?ow of the products of combustion. discharging from the ment of the same, and apertures 20. ' Figure 2 is an enlarged section taken‘approxi Although the invention has been described in ' mately on the line 2-2 of Figure 1. connection with an explosive projectile it is to Referring to the accompanying drawing, the reaction propulsion device shown for illustration 45 be understood that the .same is equally as ap plicable to any device of the rocket type adapted includes a main projectile body 5 having a cham to be projected through space, and that the vanes , ber liltherein for the reception of an explosive l8 and apertures 20 may be arranged at locations charge, not shown, and a rearwardly extending burster tube ‘I. ‘ I other than at the rearward end of the casing. Threadedly or-otherwise suitably secured to the 50' It is to be understood that various changes base end of the body 5 is a tubular casing 8 hav may be‘ made in' the detailed construction and ing anintemal shoulder 9 at its forward end arrangement of the parts described without de which supports a plate Ill. The plate In supports parting from the spirit and substance of the in a cage Ii composed of rods I2 and an intercon vention, the scope of which is de?ned by the ap necting end ring l3. The propulsion charge 55 pended claims. . ’ 2,412,868 3 What is claimed is; a . ' 1. In a reaction propulsion device, a tubul casing adapted to contain a combustible pro pelling charge, one end oi’ said casing being of 4 . Products of combustion of said charge from said casing, the external surface of said reduced and ' ?aring outwardly and axially away from the body of said casing, said casing having a plurality of. apertures through the wall thereof adjacent reduced cross-section and providing an axially said reduced end for discharging a portion oi’ said opening Venturi passage for the discharge oi the products of combustion about said reduced end, products of combustion of said charge from said and a plurality of circumferentially'spaced out casing, the external surface 01’ said reduced end wardly extending vanes joined to the external ?aring outwardly and axially away from the body of said casing, said casing having a plurality of 10 wall of said reduced end and providing a plu rality of channels, said apertures being disposed apertures through the wall thereof adjacent said to discharge products of combustion into said reduced end for discharging a portion of said. said vanes being angularly disposed products of combustion about said reduced-end. - channels, relative to the axis of said casing and in the 2. In a reaction propulsion device. a tubular path of discharge of the products of combustion casing adapted to contain a combustible pro from said apertures whereby to impart rotation‘ pelling charge, one end of said casing being of to said device.‘ reduced cross-section and providing an axially opening Venturi passage for the discharge of the REGINALD W. HOAGLAND. _'