Патент USA US2412173код для вставки
ecu 3,‘ W. PROJECTILE B. ’ Filed Feb. 22;. 1944 5 6 M 14 16 22 INVENTOR. "18"” 17 Wznslow 19. Pope BY% ?TTORNEY Patented Dec. 3, 1.946 _ 2,412,173 2,412,173 PROJECTILE Winslow B. Pope, Detroit, Mich., assignor, by mesne assignments, to United _States of America Application February 22, 1944, Serial No. 523,415 2 Claims. (Cl. (ill-35.6) ' 1 2 This invention relates to projectiles and devices of the type adapted to be projected through space ring I I‘, which carries the propelling charge, 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 pro jectile proper for housing the propelling charge and having its trailing end contoured to provide an axially opening Venturi passage. 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 pas sage, such as shown in the copending application, Serial No. 487,689, ?led by Warren H. Farr on May 20, 1943, has been replaced by a multi-jet In such a 10 rotary device l3. device, the gases ?owing through the Venturi To this end, the rearward end of the casing 5 is slightly reduced in diameter and provided with an internal shoulder l4. Inserted from through the Venturi passage. Such o?-center the rearward end of the casing and seated against ?ow or shifting of the flow of gases from truly 15 the shoulder M is an annular ball thrust bearing passage, due to uneven burning of the charge, or for other reasons, may ?ow slightly off center axial ?ow during the ?ight of the projectile 15. The cylindrical rotary dc /ice l3 seats against will cause the projectile to deviate from a true pre the outer race of the bearing I5 and is mounted within the rearward end of the casing for free rotation by means of circumferentially surround determined course. The object of the present invention is to pro vide a new and novel arrangement whereby to 20 ing rollers l6, commonly known as needle bear insure an even ?ow of gases from a rocket type ings, the bearings I6 engaging with the inner projectile. wall of the rear end of the casing 5 and being Another object is to provide a rocket type seated in a circumferential recess l1 formed in the projectile with a rotary gas discharging device peripheral wall of the rotary device IS. adapted to provide for uniform axial ?ow of the 25 The device I3 is retained within the casing propelling gases. ‘ ’ by means of a radially inwardly ?anged ring 22 A further object is to provide a novel arrange externally threaded to the end of the casing as ment for preventing premature bursting of the shown in the drawing. casing which houses the propelling charge. The rotary device I3 is provided with a plurality With the above and other objects in view, which 30 of uniformly circumferentially spaced Venturi will be apparent from the following descriptions passages I8 arranged therein at an angle to the to those skilled in the art to which the axis of the device I3. The passages It may be invention appertains, the present invention formed by drilling and then taper reaming the consists of certain features of construction and drilled openings from the opposite sides of the combinations of parts to be hereinafter described 35 rotary device to provide the restriction ill in the with reference to the accompanying drawing, and passages l8. ' then claimed. It will be obvious that the flow. through the pas In the drawing which illustrates a suitable em sages l8 of the products of combustion of the bodiment of the present invention: combustible propelling charge will, by reason of Figure 1 is a side elevation, partially in section, 40 the angularly arranged passages I8, cause the of the rocket projectile, device l3 to rotate. Since the device I3 is coaxial Figure 2 is an enlarged rear end view of the with the casing 5 and the gases discharge through projectile shown in Figure 1, and the equally spaced jets, each the same distance Figure 3 is a transverse section taken approxi from the axis of rotation, the gases will leave the mately on line 3-—-3 of Figure 2. ’ 45 device in an annular rotating stream truly coaxial Referring to the accompanying drawing, the with the casing thus insuring a uniform annular rocket device selected for illustration includes a propelling pressure at all times. ' main projectile body 5 having a chamber 6 for In order to prevent the building up of a pres the reception of an explosive or other charge. A sure within the casing prematurely which might tubular casing l is threadably or otherwise suit 50 tend to rupture the casing before the'device has ably secured to the rearward end of the body 5, left the projector and thereby cause serious dam the casing having an internal shoulder B which age, the rotary device I3 is provided with a cen supports a. plate-like member 9. ‘ The plate tral passage 20 which is counterbored at its inner like member 9 supports a cage, composed end to receive a plate 2| having a press ?t there of the rods Ill and interconnecting end 55 with. The plate 2| is of less yield strength than 2,419,178 the casing wall and is oi’ such predetermined strength that in the event of the building up of abnormal or excessive pressures within the cas ing, 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 4 an annular end thrust bearing within said end in advance oi.’ said member and engaged there with, and means secured to said end for retain ing said member in said end, said member having a plurality of discharge passages extending 1on gitudinaliy therethrough, said passages being in clined relative to " the axis of rotation of said member and said axis oi rotation being coinci other arrangement adapted to be projected 10 ~ dent with the axis of said casing. 2. In a reaction propulsion device, a casing for ‘ housing a combustible propelling charge, a cylin Various changes may be made in the detailed ‘drical member within one end of said casing and construction and arrangement of the parts de having a plurality of circumferentiaily spaced Jet scribed without departing from the spirit and substance of the invention, the scope of which 1-5 passages extending therethrough into communi cation with the interior of said casing, said mem is de?ned by the appended claims. ' her having an axial opening therein, and a plate What is claimed is: closing said opening at the end adjacent the in 1. In a reaction propulsion device, a casing for terior of said casing, said plate being or a mate housing a combustible propelling charge, a cylin drical member within one end of said casing, 20 rial having a yield strength less than the yield strength of said casing whereby incident to ex anti-friction bearing means within said end in cessive pressures within said casing said plate will surrounding relation with respect to said mem rupture prior to said casing. her for supporting said member for free rotation, WINSLOW B. POPE. through space.