US2409427A

US2409427A - Equilibrated rocket shell

Info

Publication number: US2409427A
Application number: US493023A
Authority: US
Inventors: Fonberg Zygmunt
Original assignee: Individual
Current assignee: Individual
Priority date: 1943-07-01
Filing date: 1943-07-01
Publication date: 1946-10-15
Anticipated expiration: 1963-10-15

Description

@et i5, E946.- z FONBERG l 2,409,427

; EQUILIBRATED ROCKET SHELL` Filed July il.,l

IN1/Emol;

Patented Oct. 15, y1946 UNITED STATES PATENT OFFICE Claims.

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 of aerial bomb.

Figure 1 is a vertical sectional View of Figure 3.

Figure 2 is a vertical sectional View of Figure 4.

Figure 3 is a fragmentary longitudinal sectional view of an embodiment of the invention.

Figure 4 is a fragmentary longitudinal secL tional view of another embodiment of the invention.

The present equilibrated rocket shell can be made in several slightly different types. The principle of its action is as follows: the propulsive material ignites in chamber A4, see Figure 3, and generates high pressure gases which are emitted through the choke H4 giving, by the law of reaction, propulsive motion to the shell. A portion of the gases escapes through the choke E4, giving the shell a rotative movement which gives the advantage of maintaining it on a straight trajectory regardless of imperfections and the defects in its manufacture. This rotative movement provides the possibility of maintaining propulsive action after the shell has started on its course of travel without the danger of affecting the direction of the shells initial movement.

It is known that up to now rocket shells have been very inaccurate if the action of propulsion has been maintained after the shell has left the slide or barrel which has directed the Yshells initial movement. The present arrangement of giving a rocket shell a rotative movement eliminates the above mentioned inconvenience. The shells rotative movement can be produced by spades K4 placed at a proper angle as shown in Figure 1 and the initial direction can be given by a well known barrel (not shown) inside of which the shell moves. The shell has to be given sufficient propulsion and rotative movement while in said barrel to maintain its direction.

Figure 1 represents the arrangement of rotative choke H4 which can be used with special advantage in aerial bombs. It action is as following: After the bomb leaves the racks of the aircraft, propulsive material in chamber A4 is ignited with sufficient delay and gases escaping by the rotative choke H4 and acting in conjunction With force of gravity give propulsive motion to the bomb. Part of those gases acts movement 'to the principal choke H4, which rotates on the ball bearing M4. This rotative action is of major importance because it eliminates imperfectness of choke and propulsive action does lnot affect the bombing accuracy. Slight gyroscopic effect given by the chokes rotation can be eliminated by steering wings K4 which will turn the bomb in opposite direction of the rotation of choke H4.

Figure 2 represents shell or bomb in action similar to that represented in Figure 1 but mounted on slide D5.

For the purpose of avoiding needless repetition, the second embodiment of the invention shown in Figures 2 and 4, has parts thereof which correspond to the first embodiment of the invention given the same reference character with the addition of the exponent 5 as a suffix. Its action is as following: The propulsive material generated in chamber A5 gives propulsive motion to the shell without delayed action and at the same time rotates choke H5 by means of spades C5 placed at that choke. This shell can be used both as aerial bomb placed vertically on the racks of aircrafts or can be red from the slide D5 in any direction.

It is claimed and desired to secure by Letters Patent:

1. A rocket shell comprising: a chamber having propulsive material therein adapted to produce gas at high pressure; a principal choke 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 emit a portion of said gas to cause rotation of said principal choke; and means to rotate said chamber in a direction opposite to the direction of rotation of the principal choke wherebyv the gyroscopic action of the rotative principal choke is compensated for.

2. A rocket shell comprising: a chamber having propulsive material therein adapted to produce gas at high pressure; a choke rotatably mounted on said chamber and through which said gas is emitted; first means to rotate said choke in one direction and second means to rotate said chamber in an opposite direction; whereby the gyroscopic effect of said rotative choke in rotating is counter-acted by the counter rotation of the chamber.

3. A rocket device comprising: a chamber having propulsive material therein adapted to produce gas at high pressure; a choke rotatably mounted on said chamber and through which said gas is emitted; first means to rotate said choke in one direction; and second means including 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 having 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 secondary choke angularly disposed with respect toY the aXis of rotation of the principal choke and adapted to emit a portion of said gas to cause rotation of said principal choke; anda steering wing connected to said chamber and in the path of gas emitted by the secondary choke, whereby said wing and hence the chamber is caused to rotate in a direction opposite to the direction of rotation of the principal choke, so that the gyroscopic effect of the principal choke is counteracted.

Vportion of said steering wing being arranged at an angle to the line of flight of the rocket shell, whereby the gas emitted by the secondary choke and the air through which the rocket shell takes flight cause the wing to rotate and hence the chamberto rotate in the same direction and oppositely to the direction of rotation of the said principal choke, so that the gyroscopic effect of the rotation of the principal choke is reduced.

ZYGMLUN T FONBERG.