Патент USA US2409428код для вставки
@et i5, E946.- ; _ z_ FONBERG l _ ` ` ï >2,409,427 EQUILIBRATED ROCKET SHELL` Filed July il.,l ' A4 / Il, IN1/Emol; Patented Oct. 15, y1946 2,409,427 UNITED STATES PATENT OFFICE 2,409,427 EQUILIBRATED ROCKET SHELL Zygmunt Fonberg, New York, N. Y. Application July 1, 1943, Serial No. 493,023 5 Claims. (Cl. 102-49) 1 2 This invention relates to a special type of ' equilibrated rocket-shell which is to be used as an effective recoilless weapon in form of shell similar in effect to ordinary gun shells or in form rotates on the ball bearing M4. This rotative action is of major importance because it elimi nates imperfectness of choke and propulsive action does lnot affect the bombing accuracy. of aerial bomb. ` 5 Slight gyroscopic effect given by the choke’s rota Figure 1 is a vertical sectional View of Figure 3. tion can be eliminated by steering wings K4 which Figure 2 is a vertical sectional View of Figure 4. will turn the bomb in opposite direction of the Figure 3 is a fragmentary longitudinal sec rotation of choke H4. tional view of an embodiment of the invention. Figure 2 represents shell or bomb in action Figure 4 is a fragmentary longitudinal secL 10 similar to that represented in Figure 1 but tional view of another embodiment of the in mounted on slide D5. vention. ' For the purpose of avoiding needless repeti The present equilibrated rocket shell can be tion, the second embodiment of the invention made in several slightly different types. The shown in Figures 2 and 4, has parts thereof which principle of its action is as follows: the pro 15 correspond to the first embodiment of the inven pulsive material ignites in chamber A4, see Figure tion given the same reference character with 3, and generates high pressure gases which are the addition of the exponent 5 as a suffix. Its emitted through the choke H4 giving, by the action is as following: The propulsive material law of reaction, propulsive motion to the shell. generated in chamber A5 gives propulsive motion A portion of the gases escapes through the choke 20 to the shell without delayed action and at the E4, giving the shell a rotative movement which same time rotates choke H5 by means of spades gives the advantage of >maintaining it on a C5 placed at that choke. This shell can be used straight trajectory regardless of imperfections both as aerial bomb placed vertically on the and the defects in its manufacture. This rota racks of aircrafts or can be ñred from the slide tive movement provides the possibility of main 25 D5 in any direction. . taining propulsive action after the shell has It is claimed and desired to secure by Letters started on its course of travel without the danger Patent: of affecting the direction of the shell’s initial 1. A rocket shell comprising: a chamber hav movement. ing propulsive material therein adapted to pro 30 It is known that up to now rocket shells have duce gas at high pressure; a principal choke been very inaccurate if the action of propul sion has been maintained after the shell has left the slide or barrel which has directed the Yshell’s initial movement. The present arrange ment of giving a rocket shell a rotative move rotatably mounted on said chamber and through which said gas is emitted; a secondary choke angularly disposed with respect to the axis of rotation of the primary choke and adapted to 35 emit a portion of said gas to cause rotation of ment eliminates the above mentioned incon said principal choke; and means to rotate said venience. The shell’s rotative movement can be chamber in a direction opposite to the direction produced by spades K4 placed at a proper angle of rotation of the principal choke wherebyv the as shown in Figure 1 and the initial direction gyroscopic action of the rotative principal choke can be given by a well known barrel (not shown) 40 is compensated for. inside of which the shell moves. The shell has 2. A rocket shell comprising: a chamber hav to be given sufficient propulsion and rotative ing propulsive material therein adapted to pro movement while in said barrel to maintain its duce gas at high pressure; a choke rotatably direction. Figure 1 represents the arrangement of rota 45 mounted on said chamber and through which said gas is emitted; first means to rotate said tive_ choke H4 which can be used with special choke in one direction and second means to advantage in aerial bombs. It action is as fol rotate said chamber in an opposite direction; lowing: After the bomb leaves the racks of the whereby the gyroscopic effect of said rotative aircraft, propulsive material in chamber A4 is ignited with sufficient delay and gases escaping 50 choke in rotating is counter-acted by the counter rotation of the chamber. by the rotative choke H4 and acting in con 3. A rocket device comprising: a chamber hav junction With force of gravity give propulsive ing propulsive material therein adapted to pro motion to the bomb. Part of those gases acts through chokes E4 which give a fast rotative ’ duce gas at high pressure; a choke rotatably movement 'to the principal choke H4, which 55 mounted on said chamber and through which 2,409,427 3 said gas is emitted; first means to rotate said choke in one direction; and second means in cluding steering wings, to rotate said chamber in an opposite direction; whereby the gyroscopic eifect of said rotative choke is counter-acted by the reverse rotation of the chamber. 4. A rocket shell comprising: a chamber hav ing propulsive material therein adapted to pro 4 5. A rocket shell comprising: a chamber hav ing a propulsive material therein adapted to produce gas at high pressure; a principal choke rotatably mounted on said chamber and through which a portion of said gas is emitted; a sec ondary choke angularly disposed with respect to the axis of rotation of the principal choke and adapted to emit a portion of said gas to cause rotation of saidrprincipalchoke; and a steering duce gas at high pressure; a principal choke rotatably mounted on said chamber and through 10 wing connected to said chamber and in the path of the gas emitted by the secondary choke, a which a portion of said gas is emitted; a sec ondary choke angularly disposed with respect toY Vportion of said steering wing being arranged at an angle to the line of flight of the rocket shell, the aXis of rotation of the principal choke and whereby the gas emitted by the secondary choke adapted to emit a portion of said gas to cause rotation of said principal choke; anda steering 15 and the air through which the rocket shell takes flight cause the wing to rotate and hence the wing connected to said chamber and in the path of gas emitted by the secondary choke, whereby `> chamber‘to >rotate in the same direction and oppositely to the direction of rotation of the said wing and hence the chamber is caused to said principal choke, so that the gyroscopic effect rotate in a direction opposite to the direction of rotation of the principal choke, so that the gyro 20 of the rotation of the principal choke is reduced. scopic effect of the principal choke is counter ZYGMLUN T FONBERG. acted.